2082 S.R.M. Airbus A320 [PDF]

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ATP INDEX COPYRIGHT

2003

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ATP Grid Index to Manufacturer’s Publications:

Learjet Corp. 20, 30 Series Structural Section General

Repair Manual

TopiC Information

Title Page

Safety Advisory Manufacturer’s Introduction

Temporary

Revision No.

51-7

Source of Materials

Record of Revisions Record of

Temporary

Revisions

Letter of transmittal List of Effective

(Highlights of Changes)

Pages

Structures

51.00.00

Standard Practices

51.00.00

List of Effective

51.00.00

Structures

Pages

General

51.00.00

Aircraft Structural

51.00.00

Structural

51.00.00

Repairing

51.00.00

Loading Secondary Structure Primary Aircraft Master Repair Index Major Structural Member Locations (23/24 Series) Major Structural Member Locations (25 Series) Major Structural Member Locations (28/29 Series) Major Structural Member Locations (31 Series) Major Structural Member Locations (35/36 Series) ID Aicraft Measurement System A/C Measurement System (23/24 Series)

51.00.00

51.00.00 51.00.00

51.00.00 51.00.00 51.00.00 51.00.00

51.00.01 51.00.01

06/11/2003

Description Design Concept

Safe-Life Structure

Structure

Copyright

Aircraft Technical

GL

0020

R3)

Publishers

Page

1 of

7

Section

Topic

51.00.01

A/C Measurement System (25 Series)

51.00.01

A/C Measurement System (28/29 Series)

51.00.01

A/C Measurement System (31 Series)

51.00.01

A/C Measurement System (35/36 Series)

51.00.02

Restricted Ares

51.00.03

Access Doors

ID ID

Panels

51.00.03

Access Doors

Panels (23 Series)

51.00.03

Access Doors

Panels (24/24A Series)

51.00.03

Access Doors

Panels (248 Series)

51.00.03

Access Doors

Panels (24D/E/F Series)

51.00.03

Access Doors

Panels (25/25A Series)

51.00.03

Access Doors

Panels (25/B/C/D/F Series)

51.00.03

Access Doors

Panels (28/29 Series)

51.00.03

Access Doors

Panels (31 Series)

51.00.03

Access Doors

Panels (35/36 Series)

51.10.00

Aerodynamic Smoothness Investigation Investigation Materials Inspection Airframe Allowable Damage Repair Temporary Revision No. 51-1

51.30.00

Materials

51.10.00

51.10.00 51.10.00 51.10.00 51.10.00

51.30.00

Constuction Metals

51.30.00

Extrusion

51.30.01

Metal

51.30.01

Heat Treatment of Aluminum

51.30.02

Sealing Metals

51.30.03

Charts

51.30.04

Protective Treatment

51.40.00

Formed Sections Protection

Parts-Repair

Structural

Tables

51.40.02

Rivets

51.40.03

Fastener Substitution

51.50.00 51.50.00 51.50.00 51.50.00 51.70,00 51.70.01

06/11/2003

ID

Fasteners

Threaded Fasteners

51.50.00

Alloys

Repair

Structural

51.40.01

51.40.04

Steel

Blind Fasteners

Countersinking Structural Repair Support For Alignment Symetry Inspection Alignment Surface Alignment Inspection Elevation Inspection Procedures Level Support Equipment for Aircraft Repair Repairs

ID

Aircraft Skin Dents

Copyright

Aircraft Technical GL

0020

R3)

Publishers

Page

2 of

7

Secti on

Topic

Temporary Revision No. 51-2

51.70.01 51.70.02

Aircraft Skin

51.70.02

Temporary

Revision No.

51.70.03

Formed Section

51.70.04

Extruded Section

51.70.05

Fiberglass Structures

51.70.06

Corrosion

51.70.07

Honeycom Insert

51.70.08

Seat Rail

51-6

51.71.10

Repair Data Wing-To-Fuselage Fittings Flap Fittings Spoiler Fittings Aileron System Tip Tank Fittings Landing Gear Fittings Engine Mount Fitting Rudder Fittings Horizontal Stabilizer Fittings Elevator System

51.71.11

Keelbeam Assemblies

51.71.12

Mach Trim System

51.71.13

Control Column Assembly

51.71.14

51.71.18

Passenger/Crew Upper Passenger/Crew Lower Passenger/Crew Upper Passenger/Crew Lower Quadrant Assembly

51.71.19

MLG Power Brake Valve

51.71.20

Main Gear Door

51.71.21

Main Gear Shock Strut

51.71.22

Nose Gear Shock Strut

51.71.23

Main Gear Actuator

51.71.24

Main Door

51.71.25

Nose Gear Actuator

51.71.26

Nose Gear

51.71.27

Nose Gear Door Mechanism

51.71.28

Flap Peselect Assembly

51.71.00 51.71.01 51.71.02

51.71.03 51.71.04 51.71.05 51.71.06 51.71.07 51.71.08 51.71.09

51.71.15 51.71.16 51.71.17

Allowable Wear

Door

Door

Linkage

Uplatch

Uplatch

Mechanism

Uplatch

52.00.00

Doors

52.00.00

List of Effective Pages

06/11/2003

Door

Door

Copyright

Aircraft Technical Publishers GL

0020

R3)

Page

3 of

7

Section

Topic

52.00.00

General

52.10.00

52.20.00

Passenger/Crew ID Passenger/Crew Upper Door (24 IN.) ID Passenger/Crew Upper Door (36 IN.) Passenger/Crew Upper Door-Allowable Damage ID Passenger/Crew Lower Door (24 IN.) ID Passenger/Crew Lower Door (36 IN.) Passenger/Crew Lower Door-Allowable Damage Emergency Exit Structural Identification-Damage and Repair

52.40.00

Service

52.10.00 52.10.00 52.10.00

52.10.10 52.10.10

52.10.10 52.20.00

52.40.00

Tailcone Access door

52.40.05

Nose

52.40.10

Oil

52.40.15

Oxygen Bottle Access Door

52.80.00

52.80.00 52.80.10 52.80.20 52.81.00

Compartment

Access Doors

Filter Access Door

Single-Point Pressure Refuel Door Landing Gear Main Landing Gear Doors Main Landing Gear Inboard Door Main Landing Gear Outboard Door Nose Landing Gear Door

53.00.00

Fuselage

53.00.00

List of Effective

Pages

53.00.00

General

53.10.00

Nose

53.10.00

(23 Repair Index (Late Model Repair Index Allowable Damage Repair Fuselage Assembly Fuselage Assembly Fuselage Frames Fuselage Stringers

53.10.00 53.10.00 53.20.00 53.20.00 53.21.00 53.22.05

Assembly Early Model 24

Windshield Structure

53.25.00

Fuselage Instrument Panel Support Structure Fuselage circuit Breaker Panel Structure Fuselage Skins

53.28.00 53.28.00 53.28.00 53.28.00

06/11/2003

Repair Index Repair Index Repair Index Copyright

24 Series)

25/28/29/31/35/36)

53.24.00

53.26.00

Repair

Service Doors

52.40.01

52.40.20

Repair

(23/24 Series

(25/28/29 SRS.W/24IN.Psngr/Crw Door) (25/28/29 SRS.W/36IN.Psngr/Crw Door)

Aircraft Technical GL

0020

R3)

Publishers

Page

4 of

7

Section

Topic

53.28.00

Repair

53.28.00

Allowable Damage

53.28.00 53.29.00 53.30.00 53.30.00

Index

(31/35/36 Series)

Temporary Revision No. 53-1 Baggage Floor Structure Fuselage Seat Tailcone Assembly Temporary Revision No. 53-4

53.31.00

Tailcone Bulkhead (Frame)

53.32.00

Tailcone

53.33.00

Tailcone Ventral Fin

53.33.00 53.33.00

Stringers Stringer

Index

(35/36 Series)

Repair Repair Index

(31 Series)

53.34.00

Tailcone Dorsal Assembly

53.35.00

Tailcone Skins

53.36.00

Delta Fins

53.36.00

53.40.05

Temporary Revision No. 53-2 Fuselage Fuel Cell Fuselage Fuel Cell Structure

53.50.00

Keelbeam Assemblies

53.40.00

53.51.00

Forward Keelbeam

53.53.00

Underwing Keelbeam

53.55.00

Aft Keelbeam

54.00.00

Nacelles/Pylons

54.00.00

List of Effective Pages

54.00.00

General

54.10.00

Nacelles

54.10.10 54.20.00

Nacelle Firewall Cowls

54.20.10

Upper Cowl

54.20.20

Lower Cowl

54.30.00 54.30.10

54.30.10 54.30.20 54.30.30

54.30.40 54.50.00 54.50.00

Engine Nacelle Engine Inlet Assembly Temporary Revision No. 54-1 Duct Assy, Fan and Inner Wall Engine Nacelle Afterbody Engine Exhaust Nozzle Assembly Pylons Structural Identification-Damage

55.00.00

Stabilizers

55.00.00

List of Effective Pages

06/11/2003

Copyright

Repair

Aircraft Technical Publishers GL

0020

R3)

Page

5 of

7

Section

Topic

55.00.00

General

55.10.00

Horizontal Stabilizer

or

(23/24/25/28/29/31 Series) (35/36 Series)

55.10.00

Repair Index Repair Index

55.10.00

Allowable Damage and

55.10.00

Canard

Repair

Structural ID

55.20.00

Elevator

55.20.00 55.20.00

Repair Repair

55.20.00

Allowable Damage

55.30.00

Vertical Stabilizer

Index

(23/24/25 Series)

Index

(28/29/31/35/36 Series)

Repair Structural ID

55.30.00

Repair Index

(23/24/25 Series)

55.30.00

(28/29/31 Series)

55.30.00

Repair Index Repair Index

55.30.00

Allowable Damages

55.35.00

55.35.00 55.35.00

55.35.00 55.40.00 55.40.00

Tip Temporary Revision No. 55-2 Repair Index Allowable Damage Repair Trim Tab

Rudder

Temporary Revision Windows

56.00.00

List of Effective Pages

56.20.00 56.20.00

Windshield

Passenger Compartment Cabine Window

56.20.00

56.20.00

Allowable Damage

Index

57.00.00

Wings

57.00.00

List of Effective Pages

57.00.00 57.10.00

57.11.00 57.11.10 57.11.20

06/11/2003

Early Mode: 24 Series) 25/28/29/31/35/36) (Late Model 24 (23

Index

Repair Repair

57.00.00

No. 55-1

Flight Compartment

56.20.00

57.00.00

(28/29/31 Series)

Rudder

56.00.00

56.10.00

Repair

Fin

55.40.00

56.10.00

(35/36 Series)

Repair

General

Temporary Revision Temporary Revision

No. 57-1 No. 57-4

Center Wing

Wing

Structural ID

(23/34/35 Series) (28/29/31 Series)

Repair Index Repair Index

Copyright

Aircraft Technical GL

0020

R3

Publishers

Page

6 of

7

Section

Topic

57.50.00

(35/36 Series) Repair Index Wing Tip Winglet (Inner) Winglet (Outer) Tip Tank Trailing Edge and Trailing Edge Devices Structural Identification Flap (23 Early Model 24/25/35/36 Series) Repair Index 28/29/31 Ser) Repair Index (Late Mod 24/25/35/36 Ser Allowable Damage Repair

57.60.00

Aileron

57.11.30 57.30.00 57.30.10 57.30.20

57.31.00 57.50.00 57.50.00

57.50.00 57.50.00

57.60.00 57.60.00 57.60.00

57.60.00 57.60.00 57.60.00

57.60.10 57.60.10

57.60.10 57.60.10 57.60.20 57.60.20 57.60.20

57.60.20 57.60.20 57.70.00 57.70.00 57.70.00

Aileron

Repair Repair Repair Repair

Structural

Identification

Index

(23 Series)

Index

(Early Model 24 Series) (Early Model 25 Series)

Index Index

Allowable Damage Aileron Balance Tab

Repair Index Repair Index Allowable Damage Aileron Trim Tab

(Late 24/25

All 28/29/31/35/36)

Repair Structural

Identification

(23 Series)

(24/25/28/29/31/35/36

Series)

Repair Structural

Identification

(23 Series) Repair Index (24/25/28/29/31/35/36 Series) Repair Index Allowable Damage Repair No. 57-3 Revision Temporary Spoilers Repair Index Allowable Damage Repair

End of Index

06/11/2003

Copyright

Aircraft Technical Publishers GL

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R3)

Page

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NI FG

I

INTRO

~Learjet Strwctwral

Repair Manual

Learj et 20/30

Series Aircraft

P.O. BOX 7707, MID-CONTINENT AIRPORT, WICHITA, KANSAS 67277-7707

May 15, 1992 SRM-4

Revised

Tuly 10,

1998 (Rev. No. 4)

STRUCTURAL REPAIR MANUAL 1.

Safety Advisory WARNING:

BEFORE USING ANY OF THE MATERIALS CALLED OUT IN THIS PUBLICATION, BE AWARE OF ALL HANDLING, STORAGE AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO COMPLY WITH THE MANUFACTURERS OR SUPPLIERS RECOMMENDATIONS MAY

RESULT IN PERSONAL

INJURY

OR DISEASE.

This

publication describes physical and chemical processes which may require the use of chemicals, solvents, paints, and other commercially available materials. The user of this publication should obtain the Material Safety Data Sheets (OSHA Form 20 or equivalent) from the manufacturers or suppliers of the materials to be used. The user must become completely familiar with the manufacturer/supplier information and adhere to the

procedures, recommendations, warnings handling, storage, and disposal of the materials.

and cautions set forth for the safe use,

Safety Advisory Page 1 SRM~

Jan 15/93

RECORD OF REVISIONS

MFG REV NO 4

DESCRIPTION

ISee Highlights

ISSUEDATE 7/10/98

ATPREVDAT

10/1/98

INSERTED BY ATP/KS

jet Record of Revisions

Record of Revisions

Date of

Issue

Insertion

By

Date

1

Jan 15/93

05/19/931ATP/P

2

Jun 1/95

08/24/951ATP/JX

3

Jun 6/98

4

Jul 10/98

Record of

Date of

Insertion

Revisions

Issue

Date

By

07/23/98(ATP/ES

10/01/981ATP/KS

Record of Revisions SRM-4

Page

1

Jul 10/98

RECORD OF TEMPORARY REVISIONS

ATP REV

INSERT

DATE

REV

REMOVE

ISSUE DATE

DATE

BY

REMOVED

INCOR

BY

TEMP REV NO

DESCRIPTION

57-3

57-60-20:201

3/30/98

6/11/98

ATP/ES

53-1

53-36-00:102

7/1999

9116/99

ATPIVM

54-1

54-30-10:4

8/1 3/99

10/28/99

ATPIKS

57-4

57-00-00:205

8/31 /00

1 1 /9/00

ATPIM B

55-2

55-35-00:1

10/30/00

311 5101

ATP/IB

51-6

51-70-02:201

1/15/01

4/1 2/01

ATPIMG

53-1

53-28-00:101

6/1 5/01

8/1 6/01

ATP/MG

53-2

53-36-00:102

7/1/01

8/1 6/01

ATP/MG

53-4

53-30-00:201

1/18/02

4/25/02

ATP/MG

51-7

Manufacture’s Intro

4118/03

6/19/03

ATP/VDR

Page

1

8/16/01

TR

53-

ATP/MG

Learjet Ledrjei( Record of Temporary Revisions

Rev. No.

51-1

Issue Date

8/15/97

51-3

9/18/97

9/12/97

ATP/tIIB

ATP/XS

11

1(

Ir

2/13/98 11

5/14/98

/ES

53-1

7/01/99

9/16/99

/VM

54-1

08/13/99

10/28/99

ATP/KS

57-4

8/31/200

11/9/200

ATPI~B

03/14/01

ATP/IB

53-2

08/30/00 1/15/01

4/12/01

ATP/MC´•

6/15/01

8/16/01

ATPIMC~

7/1/01

II

,1

II

I~

Ir

1~

II

II

II

6/11/98

53-1

/,Me

7/23/98

/HP

3/30/98

51-6

6/6/98

3

1~

57-3

55-2

By

Insertion Date

Issue Date

~1

11/27/97

51-5

57-2

No.

11

51-4

55-1

Rev.

By

Date

11

51-2

57-1

Insertion

n

TR

53-

7/1/01

8/16/01

ATPI~"C-

n

Record of

Temporary Revisions Page 1 Aug 13/99

SRM-J

Learjet Record of

REV.

DATE

DATE

NO.

INSERTED

REMOVED

51-1

Aug 15/97

PAGE NUMBER

REV.

DATE

NO.

INSERTED

Temporary Revisions

DATE REMOVED

PAGE NUMBER

51-10-00

Page 202 51-2

51-70-01

Aug 15/97

Page 51-3

51-4

51-5

Sep 12/97

Sep 12/97

Sep 12/97

201

Jun 6/98

51-71-10

Rev 3

Page 8

Jun 6/98

51-71-10

Rev 3

Page

Jun 6/98

51-71-10

Rev 3

Page

16

20

51 SILM--I

Record of

Temporary

Revisions

Page

1

jun 19/95

I)OM~ARDKR

BOMBARDIER AEROSPACE Learjet

Inc.

P.O. Box 7707

Wichita, KS 67277-7707 United States Telephone 1(316) 946-2000 http://www.aerospace.bombardier.com

July 10,

1998

Holders of

TO:

Learjet 20/30

Revision No. 4, dated

SUBJECT:

Revision No. 4 consists of

a

Series Aircraft Structural

Repair Manual

July 10,.1998

total reissue of the List of Effective

Pages (LOEP)

for

chapter

51.

Revise the LOEP

After

by inserting revised

inserting this revision,

pages and

removing superseded

note necessary information

on

LOEP pages.

the "Record of Revisions" in

the front of the manual. Direct any

questions concerning distribution (change in address, quantities, etc.)

Learjet Inc., P.O. Box 7707, Wichita, Kansas 67277-7707. Attn: Technical Telephone (316) 946-2393. FAX (316) 946-2580.

Center (MS 71).

Jack Kramer

Manager, Technical Publications

to

Data Control

BOMBARDIER

BOMBARDIER AEROSPACE Learjet

Inc.

P.O. Box 7707

Wichita, KS 67277-7707 United States

Telephone 1(3161 946-2000 htto.//www.aerosoace .bombardier. corn

Date:

June 19, 1998

To:

Holders of

Subject:

Correction to Record of

Description:

During development of

Learjet 20/30 Series Structural Repair

Temporary

Manual

(SRM4).

Revisions.

Revision 3 to the 20/30 Series Structural

Repair

Manual

dated June 6, 1998, incorporation of Temporary Revisions 51-1 and 51omitted, Please retain TR 51-1 and TR 51-2, both dated Aug 15/97, to

(SRM-4), 2 were

maintain the SRM-LF to the latest

Temporary Note:

configuration.

Notate the TR’s in the Record of

Revision.

Temporary

Revisions TR-51-3, TR 51-4 and TR-51-5

were

incorporated

in Revision 3.

Additional

copies

of TR 51-1 and TR 51-2

are

available

through Learjet Inc.,

P.O.

Box 7707, Wichita, Kansas 67277-7707, Technical Data Control Center (MS 71), Telephone (316) 946-2393. FAX (316) 946-2580. We at

Learjet apologize for any inconvenience.

LEARJET\NC. Customer

Support

Learjet

STRUCTURAL REPAIR IIRANUAL Chapter

Chapter I

Section

Subject

Page

.TITLE

Date

Section

Subject

Page

Date

Jul 10/98

Squawk Sheet Rec. of Revs.

1

Safety Advisory

1

Jul 10/98 Jan 15/93

1

Jul 10/98

1

May 15/92 May 15/92 May 15/92 May 15/92 May 15/92

*INTRODUCTIONList of Eff.

Pgs.

INTRODUCTION Contents INTRODUCTION

1

INTRODUCTION

2

INTRODUCTION

3

INTRODUCTION

4

Insert Latest Revised

Pages; Destroy Superseded or Deleted Pages. Asterisk indicates pages revised, deleted, or added by current revision. The portion of the text affected by the current revision is indicated by a vertical line in the outer

margin of the

page´•

INTRODUCTION SRM-4

List of Effective

Pages Pagel

Jul 10/98

Learjet

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject

INTRODUCTION

INTRODUCTION

Page

Scope

INTRODUCTION

1

Format

TNTRODUCTION

1

Repairs

INTRODUCTION

1

Part Numbers

1

Revisions

INTRODUCTION INTRODUCTiON

Page Numbering System.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

INTRODUCTION

2

Source of Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

INTRODUCTION

3

1

~TRODUCTION- Contents

SRM-II

Pagel May 15/92

LEARJET 20/30 SERIES

STRUCTURAL REPAIR MANUAL

TEMPORARY REVISION NO. 51-7 MANUAL AFFECTED:

Learjet

20/30 Series Structural

adjacent

Insert

FILING INSTRUCTIONS:

to the

Repair

Manual

(SRM-4).

Introduction, page 1,dated May 15/92 and retain until fur-

ther notice.

REASON:

1.

Revise

2.

Add

INSIRUCTIONS:

1. 2.

paragraph A. under 1. SCOPE. paragraph C. under 3. REPAIRS.

new

Update paragraph A. to read as follows: new paragraph C. to read as follows:

Add

INTRODUCTION 1.

SCOPE A.

repair manual is to acquaint maintenance personnel with the acceptable repairs of the Learjet and to direct them in the proper procedures for maintaining the aircraft in an airworthy condition. The ability of maintenance personnel is recognized, and procedures that are considered common to all aircraft have been briefly referenced or omitted.

The function of this structural

structural

B.

(No changes)

2.

FORMAT(No changes)

3.

REPAIRS(Nochanges) A.

(Nochanges)

B.

(Nochanges)

C.

provided in this Structural Repair Manual may be considered "data acceptable to the administrator" per CFR 14, Part 43. Ultimately it is the responsibility of the person returning the aircraft to service to determine the state of any repair made using this information with regard to the requirement for FAA approval and obtain FAA approval if required. With this in mind, it is

The data

early contact be made with Learjet may be provided in a timely manner.

recommended that

appropriate data

Field

Support Engineering

so

that the

provided by Field Support Engineering is based on information developed by the cognizant engineer. Verbal information provided in person or by telephone is considered advisory and does not carry any status relative to FAA approval. Written information provided by fax, memo, or email is used when required to address "Minor" repairs or deviations to published data. "Major" repairs or alterations are addressed by released engineering drawings and are FAA approved when accomplished by a DER’s 8110-3 form. All technical data

(Nochanges)

4.

PARTNUMBERS

5.

REVISIONS

6.

PAGE NUMBERING SYSTEM

(Nochanges) (No changes)

TEMPORARY REVISION NO. 51-7

SRM-4

Page

1 of 1

Apr

18/03

Leariet i Learjet

STRUCTURAL REPAIR MANUAL INTRODUCTION i.

SCOPE

A.

The function of this structural

repair manual is to acquaint maintenance personnel with the approved repairs of the Leajet and to direct them in the proper procedures for maintaining the aircraft in an airworthy condition. The ability of maintenance personnel is recognized, and procedures that are considered common to ail aircraft have been briefly referenced or omitted. This manual is to be used in conjunction with the applicable maintenance manual. structural

B. 2

FORMAT A.

This manual has been as a

3.

format to

prepared using the Air Transport Association (ATA) Specification Number guide repair personnel in the inspection and repair of Learjets.

100

REPAIRS A.

B.

Chapter 51 covers repairs that are common to more than one airframe structural section. These repairs are divided into "typical" and "special" classes. The typical repair section provides that data necessary for the repair person to develop his own repairs. The special repairs are located in their respective chapter and provide that data necessary to accomplish the repairs. Repair coverage for Chapters 52 through 57 is found in the repair indexes for each chapter. These indexes consist of master repair indexes or component repair indexes as applicable. Repair indexes give the Learjet drawing number, descriptive nomenclature, material data, and figure/reference number(s) for each item illustrated.

4.

PART NUMBERS

A.

This manual must not be used for

identifying spare parts by number. Consult the appropriate Leajet for this information. Part numbers are used in this manual only as a means of identification when the nomenclature alone is inadequate. The numbers are often incomplete. Illustrated Parts

5.

Catalog

REVISIONS

A.

The "List of Effective

Pages" (LOEP)

with each

chapter

tool for maintaining the manual. chapter is revised. When revision pages are received, the list should be used as a cross reference for inserting the new/revised material and deleting the obsolete material. This ensures that all obsolete material is destroyed and the manual is kept current. Revisions to text are indicated by change bars (vertical lines) in the outer margin of the page adjacent to the revised material. Revisions to illustrations may be indicated by change bars or pointing hands. serves as a

The LOEP will be revised whenever the material in the affected

EFFECTIVITY:

ALL

NOTE: Please

see

the

TEMPORARY

SRM-4

REv,s,on,

’I

that revises this page.

INTRODUCTION

Pagel May 15/92

Learjet STRUCTURAL REPAIR MANUAL 6.

PAGENUMBERING SYSTEM A.

Page

numbers used in this manual consist of three element numbers

which the page number and date

B.

C. D.

are

separated by dashes,

under

printed.

I

5lliPO1

Chapter/System

Section/Subsystem

Subject/Unit

(Structures General)

(Fasteners)

(Fastener Types)

I

chapter/system element number is followed by zeros in the section/subsystem and subject/unit positions (51-00-00), the information is applicable to the entire system. Whe~ver the sec~tion/subsystem element number is followed by zeros in the subject/unit position (51-40-00), the information is applicable to the subsystems within the system. The subject/unit element number is used to identify information applicable to units within. The subject/unit element number progresses from the number -01 in accordance with the number of subsysWhenever the

tem/units covered. E.

system/subsystem/unit data is separated into specific types ofinformation. bers are used to identify the type of information as follows: All

Blocks of page

num-

Structural Identification Ithrough 99 AllowableDamage throughl99 201 through299 -Repairs

Pages Pages Pages

101

F.

Some units may not require all the information listed in these three blocks of those blocks of numbers are omitted.

G.

The

numbers, in which

case

following is a breakdown of a typical page number: Structures General

Fasteners

1

51~001

Second

Pageof Fastener Type Structural

Page 2 May15/92

Fastener

Types

1 Date of Issue/Revision

Identification

H.

Illustrations ure

use

the

same

figure number as the page block in which they appear. As an example, Figappearing in the structural identification section.

2, will be the second illustration

EFFECTIVITY:

ALL

INTRODUCTION

Page 2 SRM4

May 15/92

STRUCTURAL REPAIR MANUAL 7

SOURCE OFMATERIALS A.

by federal Figure 1.

Manufacturers shown in numerical order in

VENDOR

I

CODE"

I

01022

vendor codes in tools and

I MANUFACTURER

I

I

Phillips Screw

MANUFACTURER

B.F. Goodrich

i

1

92663

Co.

Akron, OH 44318 29666

Huck

6 Thomas

Gloucester, MA 01930

INine, CA 92714

Cherry/Textron Inc.

30655

I

I

Amerace

I

Corp.

2330 Vauxhall Road

Santa Ana, CA 92707

Union, NJ 07083

Dynatron/Bondo Corp.

Magnaflux Corp.

37676

I

I

1

7300 W. Lawrence Ave.

Chicago, IL

Martin-Senour Co., The

Corp.

ESNA Division

P.O. Box 2157

47695

60656-3811

Div. of Sherwin-WilIiams Co.

PPG Industries, Inc. One Gateway Center

2500 S. Senour Ave.

Pittsburgh,

Chicago,IL

PA 15222

60608 60883

Ametek Inc.

Deutsch Fastener

Heat Transfer Division

Corp. Imperial Highway Los Angeles, CA 90045-3643 7001 W.

17431

Co.

One Kondelin Road

Atlanta, GA 30318

17419

Mfg.

Sub. of Federal-Mogul

2160 Hills Ave. N.W,

16772

500 S. Main

Div. of Rule Industries

Fasteners Products Division

16522

I VENDOR I CODE*

25472

Newport Beach, CA

11815

I

Lok-Fast, Inc. 864 W. 16th St.

05755

equipments lists in the chapters are listed

2300 W. Marshall Drive

Grand Prairie, TX 75051

DeVilbiss Co.

I

1

P.O. Box 913

1

I

61102

Purer

I

Toledo, OH 43692

Corp.

Turco Products Division P.O. Box 6200

Carson, CA 90749 24210

Leajet Inc. P.O. Box 7707

1

1

71286

Rexnard Inc.

Specialty Fastener Div.

Wichita, KS 67277-7707

601 Rt. 46 West Hasbrouck

Vendor code numbers

correspond

to those referenced in tools and

Heights, N~

equipment lists throughout

07604

the manual.

Source of Materials

Figure EFFECTIVITY:

AU

1

(Sheet 1 of 2)

INTRODUCTION

Pa~e 3 May 15/92

Lear ~el

STRUCTURAL REPAIR MANUAL VENDOR

CODE

1

I

Y

73197

MAN~ACTURER

1

I

I VENDOR I CODE

MANUFACTURER

Hi-Shear 2600

Corp. Skypark Drive

Torrance, CA 90509 76689

Monogram Industries, Inc. Sub. of Nortex Inc. 1299 Ocean Ave. Santa Monica, CA 90401

82748

Ruger Equipment

Inc.

P.O. Box 724

Uhrichsville, OH 44683 83324

Rosan Inc.

2901 West Coast

Highway Newport Beach, CA 92663 83574

Products Research and Chemical

Corp.

5430 San Femando Road

Glendale, CA 91203 94961

Minnesota 3M Center

Mining Mfg. Building

Co.

St. Paul, MN 55144 99384

M and T

Chemicals,

Inc.

Furane Products Division 5121 San Fernando Rd. W. Los

Angeles, CA

Vendor code numbers

correspond

90039

to those

referenced in tools and

equipment lists throughout the manual.

Source of Materials

Figure EFFECTIVITY: SRM~

ALL

1

(Sheet 2 of 2)

INTRODUCTION

Page 4 May 15/92

CHAPTER

STANDARD PRACTICESSTRUCTURES

Learjet I

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject AIRCRAFT- STRUCTURAL IDENTIFICATION

Page

.................................................................51-00-00

Aircraft Structural

Description Structural Design Concept Repairing Safe-Life Structure Structure Loading Primary and Secondary Structure.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aircraft Master Repair Index Major Structural Member Locations (Model 23/24 Series Aircraft) Major Structural Member Locations (Model 25 Series Aircraft) Major Structural Member Locations (Model 28/29 Series Aircraft).......... Major Structural Member Locations (Model 31 Series Aircraft) Major Structural Member Locations (Model 35/36 Series Aircraft) Aircraft Measurement System Structural Identification Aircraft Measurement System Description Aircraft Measurement System (Model 23/24 Series Aircraft) Aircraft Measurement System (Model 25 Series Aircraft)....... Aircraft Measurement System (Model 28/29 Series Aircraft)..... Aircraft Measurement System (Model 31 Series Aircraft) Aircraft Measurement System (Model 35/36 Series Aircraft)

51-00-00

1 2

................................................................................................51-00-00

51-00-00

3

51-00-00

3

51-00-00

3

51-00-00

4

51-00-00

6

1

8

...........................51-00-00

51-00-00

10 12

...........................51-00-00

51-00-00

13

............................................51-00-01

51-00-01

1

51-00-01

2

51-00-01

15

....51-00-01

28

51-00-01

54

51-00-02

1

41

..............................51-00-01

Restricted Areas

Structural Identification

....................................................................51-00-02

Restricted Areas Description Access Doors and Panels Structural Identification Access Doors and Panels

Description

51-00-03 1

......................................................................51-00-03

(Model 23 Series Aircraft).... Access Doors and Panels (Model 24/24A Series Aircraft).......... Access Doors and Panels -(Model 24B Series Aircraft)..................................... Access Doors and Panels (Model 24DIEIF Series Aircraft) Access Doors and Panels (Model 25/25A Series Aircraft)

51-00-03

1

51-00-03

4

51-00-03

7

Access Doors and Panels

51-00-03

12

51-00-03

15

Access Doors and Panels -(Model 25B1CIDIF Series Aircraft)

51-00-03

19

(Model 28/29 Series Aircraft) Access Doors and Panels (Model 31 Series Aircraft) Access Doors and Panels -(Model 35136 Series Aircraft)

51-00-03

24

51-00-03

29

51-00-03

34

Access Doors and Panels

INVESTIGATION AND AERODYNAMIC

SMOOTHNESS- STRUCTURAL IDENTIFICATION......................................................51-10-00

Investigation

51-10-00

1

Airframe and Materials Inspection Airframe Inspection

51-10-00

1 1

....................................................................................................51-10-00

Overpressurization or Hard Landing Inspection Overheat Inspection Structural Joint Wear Inspection Investigation and Aerodynamic Smoothness Allowable Damage Damage Classifications.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Causes and Types of Damage.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Investigation and Aerodynamic Smoothness Repair. . . . . . . . . . . . . . . . . . . . . . . . . 51-10-00 Aerodynamic Smoothness

2

...................................................51-10-00

51-10-00

3

51-10-00

4

51-10-00 51-10-00

101

51-10-00

101

51-10-00

201

51-Contents

Page~ SRM-4

Jun 1/95

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject

MATERIALS- STRUCTURAL IDENTIFICATION

51-30-00 51-30-00

Construction Materials Metal Parts

Repair and

51-30-01

Alloy Alloys.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51-30-01 Repair

Sealing Description Tools and Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51-30-02 Preparation of Faying Surfaces Prior to Sealing Types and Classes Used for Sealing Sealing Requirements Sealing Application for Structural Repairs.......... Method of Application Fillet Sealing Injection Sealing.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Faying Surface Sealing.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pre-Pack Sealing Hole Sealing

51-30-02 51-30-02

1

.........51-30-02 51-30-02

5

51-30-02

5

51-30-02

8

51-30-02

9

51-30-02

12 12

51-30-02

Structural Identification

Specifications and Code Number..................................................................51-30-04 Vapor Degreasing.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Solvent Cleaning.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Abrasive Cleaning of Metals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Primer

51-30-04

7

51-30-04

8

51-30-04

8

51-30-04

9

51-30-04

11 12

Applying Epoxy Applying Solid Dry Film Lubricant. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51-30-04 Applying Fuel Resistant and Corrosion Protection Finish....................................51-30-04 .............................................................................................51-30-04

Protection for Dissimilar Metal Contact...................................................................

1 1

Finish

Chemical Film Treatment of Aluminum and Aluminum Alloys................ Applying Sanding Surfacer to Laminated Fiberglass Parts

201

51-30-04 51-30-04

General

12

51-30-03

51-30-03

Charts and Tables Protective Treatment of Structural Materials

4

51-30-02

.................................................................................................................51-30-02

Sealing

4

4

.................................................................................................51-30-02

Charts and Tables

1

2

.....................................................51-30-02

Fastener

201 201

Heat Treatment of Steel

Structural

1

51-30-01

Protection

Heat Treatment of Aluminum

Metal

Page

13 14

51-30-04

16

51-40-00

1

FASTENERS- GENERAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51-40-00

General Threaded Fasteners

............................................................................................................51-40-01

Torquing Threaded Fasteners.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51-40-01 Installing Threaded Fasteners and Washers Inspecting Threaded Fasteners.................................................................................. Using Torque Wrenches Rivets and Blind Fasteners

1

51-40-01

1

51-40-01

2

51-40-01

2

................................................................................................51-40-02

51-40-02

1

Rivet Failures

51-40-02

1

Rivet

51-40-02

1

Description Inspection

51-Contents

SRM-4

Page 2 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject

Page

51’40-03

Fastener Substi ution. ,. . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•

General

51-40-03

Countersinking

51-40-04 51-40-04

General AIRCRAFI~ SUPPORT FOR ALIGNMENT AND REPAIR STRUCTURAL IDENTIFICATION

Symmetry Inspectio, Alignment Surface Alignment Inspection Level and Elevation Inspection Procedures.. . . . . . . . . . . . ´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•. .51-50-00 Support Equipment for Aircraft Repair

51-50-00 51-50-00

and

1 1

1 2

....................51-50-00

3 30

......................´•...´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•51-5MH)

51’70-00

REPAIRS- GENERAL.. . . . . . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• General Classification of Repairs

51-70-00

1

51-70-00

1

51-70-00

2

51-70-00

2

Typical Repair Procedure....................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•51-70-00 51-70-00 Structural Loading 51-70-00 and Limitations Inspections

2

Support of Structure During Repair Checking Alignment

Materials and Proces es. . . . . . ´•~´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• 51’70-0 Maintenance Practices. . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• 51-70-0O

Application of Loctite Applying Loctie. . . . . . .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• -´• ´• ´•-´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•51~70-0O Installing Oversized Fasteners Installing Bushings in Oversized Holes Application and Use of Structural Adhesive Aircraft Skin Dents Typical Repair Minor Dent Repair Major Dent Repair Application of Aerodynamic Fairing Compound Aircraft Skin Typical Repairs. . . . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• . 51-70-02 Skin Repairs. . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• Formed Section Typical Repairs.. Severed or Damaged Formed Section Repair Extruded Section Typical Repairs...................... Extruded Section Repair Fiberglass Structures

51-70-00

3 3 3

201 201 203

.........´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•51~70-00

51-70-00

209 212

..................´•..´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•...51-70-00

51-70-01

51-70-01

201

51-70-01

201

51-70-01

202

51-70-02

201

51-70-03 51-70´•03

201

51-70-04 .......51-70-04

201

.........51-70-05

201

Approved Repairs 51-70-05 Dorsal Inlet Approved Repairs 51-70-06 Corrosion- Repair 51-70-06 Approved Repairs .....51-70-07 Honeycomb Insert- Repair ...........................´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•...................51-70-07 Approved Repairs ..........,51-70-08 Seat Rail Repair. Approved Repairs

201

Description Radome

................-....-..´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•-´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•51-70-05

205 201

201 201

................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•51-70-08

51 -Contents

Page 3 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject ALLOWABLE WEAR AND REPAIR DATA

General

Page

51-71-00

GENERAL........

1

..............................................................................................................................51-71-00

Wing-to-Fuselage Fittings Allowable Wear and Repair Data. Flap Fittings Allowable Wear and Repair Data Spoiler Fittings Allowable Wear and Repair Data............... Aileron System Allowable Wear and Repair Data............... Tip Tank Fittings Allowable Wear and Repair Data............ Landing Gear Fittings Allowable Wear and Repair Landing Gear Fittings Repair

Data

51-71-01

1

51-71-02

1

51-71-03

1

51-71-04

1

....51-71-05

1

51-71-06

1

51-71-06 201

General

51-71-06

Limitations and

51-71-06

201

Materials and Processes

51-71-06

201

Repair Frocedures......

51-71-06

202

51-71-06

202

Inspec~ions.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fitting Repair (PINs 2322146-1 thru -8, 2822159-21 b -22, and 540000V5-1 6 -2)..............................................

Forward Trunnion Mount

Allowable Wear and

Mount

Fittings Engine Engine Mount Fittings Repair General

Repair

Data

1

....................~.............51-71-07

51-71-07

201

..................................................................................................................51-71-07

Limitations and

201

Inspections.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51-71-07 51-71-07

201

51-71-07 Repair Procedures Forward Engine Mount (PINs 2651034-1 thru -3) 51-71-07 and Support Fitting (PINs 2612042-5 thru -14) Repair 51-71-08 Rudder Fittings Allowable Wear and Repair Data............... 51-71-09 Horizontal Stabilizer Fittings Allowable Wear and Repair Data 51-71-10 Elevator System Allowable Wear and Repair Data 51-71-11 Keelbeam Assemblies Allowable Wear and Repair Data Mach Trim System Allowable Wear and Repair Data.........................................51-71-12 51-71-13 Control Column Assembly Allowable Wear and Repair Data Passenger/Crew Upper Door Allowable Wear and Repair Data (36-Inch)..... 51-71-14 Passenger/Crew Lower Door Allowable Wear and Repair Data (36-Inch)..... 51-71-15 Passenger/Crew Upper Door Allowable Wear and Repair Data (24-Inch)..... 51-71-16 Passenger/Crew Lower Door Allowable Wear and Repair Data (2PInch)..... 51-71-17 51-71-18 Quadrant Assembly Allowable Wear and Repair Data 51-71-19 Allowable Wear and Data............... Valve Brake MLG Power Repair Linkage 51-71-20 Main Gear Door and Uplatch Allowable Wear and Repair Data 51-71-21 Main Gear Shock Strut Allowable Wear and Repair Data 51-71-22 Nose Gear Shock Strut Allowable Wear and Repair Data 51-71-23 Main Gear Actuator Allowable Wear and Repair Data 51-71-24 Main Door Uplatch Mechanism Allowable Wear and Repair Data 51-71-25 Nose Gear Actuator Allowable Wear and Repair Data....................................... 51-71-26 Nose Gear Uplatch- Allowable Wear and Repair Data 51-71-27 Nose Gear Door Mechanism Allowable Wear and Repair Data................. 51-71-28 Flap Preselect Assembly Allowable Wear and Repair Data

202

Materials and Processes

202 1 1 1 1 1

1 1 1

1 1

1 1 1 1 1 1 1 1 1 1 1

51-Contents

Page 4 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL Chapter

Chapter

Section

Section

Subject

Page

Date

51-TITLE 51-List of Eff. 51-List of Eff.

Pgs. Pgs. 51-List of Eff. Pgs. 51-List of Eff. Pgs. 51-List of Eff. Pgs. 51-List of Eff. Pgs. 51-List of Eff. Pgs. 51-List of Ef~. Pgs.

Jul 10/98 Jul 10/98 Jul 10/98 Jul 10/98

1 2 3 4

Jul 10/98 Jul 10/98 Jul 10/98 Jul 10/98

5 6 7

s

51-Contents

1

51-Contents

2

51-Contents

3

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List of Effective

Pages Page 7 Ju110/98

Learjet I Learjet

STRUCTURAL REPAIR MANUAL Chapter

Chapter Section

Subject

Page

I

Section

Date

I

Subject

1

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51

SRM-I

Date

List of Effective

Pages Page 8 Ju110/98

STRUCTURAL REPAIR MANUAL AIRCRAFT- STRUCTURAL IDENTIFICATION

1.

AIRCRAFTSTRUCTURAL DESCRIPTION

DRILLING, MODIFICATIONS, OR ANY TYPE OF WORK THAT CREATES A

WARNING:

BREAK 1N THE PRESSURE SECTION iS THE RESPONSIBILITY OF THE OWNER OR FACILITY PERFORMING THE WORK. OBTAINING APPROVAL OF THE WORK IS, THEREFORE, THEIR RESPONSIBILITY.

NOTE:

The

the

following structural data covers the basic non-modified aircraft. When applicable, refer to appropriate kit drawing for additions, modifications and changes to the structural compo-

nents and assemblies.

A.

B.

C.

MajorStructural Groups (1) The major structural groups windows, and wings.

of the aircraft

are

the doors,

fuselage, naceiles/pylons, stabilizers,

Major Structural Members (1) The major structural members of the aircraft are the forward and aft pressure bulkheads, floorboards, forward and ah engine beams, baggage compartment floor, under wing keelbeam, fuselage keelbeam, and the landing gear. Type of Construction (1) This is an all-metal aircraft with full cantilever wing and horizontal stabilizer. The fuselage is of semimonocoque construction and supports an engine nacelle on each side in the area above and ah of the wing. (2) A two-piece passenger/crew door (upper and lower) is located on the fuselage left side. The doors are hinged to the fuselage by piano-type hinges. The lower door incorporates the steps for entering and exiting the aircraft. Additionally, there is an emergency exit, several service doors, and the landing gear doors. (3) The fuselage basic structure consists of a stressed skin structure with transverse frames and longerons. The fuselage is comprised of four basic sections: the nose section, the pressurized section (cockpit and cabin), the fuel section, and the tailcone section. (4) The pressurized section houses the crew, passenger, and baggage areas. Drilling, modifications, or any type of work that creates a break in the pressure section is the responsibility of the owner or facility performing the work. Obtaining approval of the work is, therefore, their responsibility. (5) The principle structure of the engine nacelles consists of the nose section, upper and lower cowls and the aft section. The complete nacelle assembly is cantilevered from the pylon by engine support fittings, and structural carry-through fittings that extend inboard from the nacelle, through the pylon, and attach to the fuselage assembly. (6) The horizontal stabilizer is a fully cantilevered one-piece construction consisting of a forward and aft spar, transverse ribs, stringers, and skins. (7) The vertical stabilizer is a fully cantilevered structure consisting of spars, transverse ribs, and skins.

(8) The elevator and rudder consist of a forward spar and

EFFECTIVITY:

ALL

transverse ribs and skins.

51-00-00

Pagel SRM-4

Jun 1/95

STRUCTURAL REPAIR MANUAL (9) The

flight compartment

windows consist of the

pilot’s

and

copilot’s

windshield halves. On Model

23 Series Aircraft each windshield half is made up of separate, removable, inner and outer panes. On Model 24/25/28/29 Series Aircvaft each windshield half is made up of three laminated layers of

acrylic plastic. Both outer layers are made of stretched acrylic and the middle layer is cast in place acrylic. On Aircraft 31-001 thru 31-029. 35-001 thru 35-670 and 36-001 thru 36-063 eauitlt~ed with a standard, non-heated windshield, the windshield is made up of three laminated layers of acrylic plastic. Both outer layers are made of stretched acrylic and the middle layer is cast in place acrylic. On Aircraft 31-030 and Subseauenf, 35-671 and Subseauent, and 36-064 and Subseauent and prior air-

craft eauip~ed with

an

layers

of

layers. er

Two

electricallu heated windshield, the windshield is made up of four laminated polycarbonate are sandwiched between two outer layers of acrylic. A spac-

is bonded to the interior side of the windshield. The windshield has

and heat

The electric

element consists of

integral electric heater layer gold laminated into the yellow or gold color cast. The func-

thin

an

of

heating gold layer, the windshield has a tion of the heater is to provide windshield defogging. Terminal blocks are embedded in the windshield and provide the means for wiring the electric heater to the aircraft wiring. The windshield is secured to the fuselage with screws and retainers. (10) The cabin windows consist of two panes of stretched acrylic with dead air space between them. The cabin windows are secured to the fuselage structure. The right rear window is removable sensors.

windshield. Because of the

and

serves as

a

the emergency exit.

fully-cantilevered single-unit consisting of the leading edge, wing box section, ailewing rons, flaps, spoilers, and tip tanks or winglets. The multicellular-type wing structure consists of spars and ribs in each wing half. The upper and lower wing skins are taper-milled so the trailing edge is thinner than the leading edge. Splice plates join the wing skin halves at the aircraft centerline. The winglets are built in two sections. The inboard section is conventional built-up construction and the outboard section is a bonded assembly consisting of aluminum skins and a fulldepth aluminum honeycomb core. The flaps, ailerons, and spoilers are constructed primarily of

(11) The

is

a

spars, transverse ribs, and skins. 2.

STRUCTURAL DESIGNCONCEPT A.

Basic

Design Approach

(1) There

are

two basic

design approaches

integrity of an aircraft during of the Learjet incorporates both design concepts. two basic approaches, definitions are presented in the

for

its service life: the "safe-life" and "fail-safe"

clarify the following paragraphs. Safe-Life Concept concepts.

B.

To

differences in the

ensuring

the structural

The

as being capable of withstanding, without failure, the reduring the defined service life of the aircraft. Safemagnitudes expected peated life is proved by either analysis or tests that include all scatter factors on material and load spectrums. Because of the proof of safe-life, alternate load paths are not necessarily deliberately pro-

(1) A safe-life aircraft

structure is defined

loads of variable

vided. C.

Fail-Safe

Concept

(1) The concept of fail-safe design differs in that alternate load paths methods for

EFFECTIVITY:

ALL

are

specifically provided

and

limiting crack propagation are employed.

51-00-00

Page 2 sRM-a

Tun 1/95

~j Leariet STRUCTURAL REPAIR MANUAL 3.

REPAIRING SAFE -LIFE STRUCTURE A.

Safe-LifeStructure

Repair

provide for alternate load paths or methods of limiting crack propagation, it is mandatory that all damage to primary and secondary structure (other than allowable damage) be repaired upon discovery. (2) Repairs in this manual are designed to restore the capability of the material in order to ensure the safe-life characteristics of the structure. It is emphasized that other repairs, designed for a specific "fix," must follow the same concept, i.e., that the ultimate allowable strength must be maintained, to maintain structural integrity for the life of the aircraft.

(1) Since safe-life

4.

structure does not

STRUCTURE LOADING A.

Structural

Loading

(1) Caps and flanges of spars, ribs, frames and beams are considered to be in tension or compression. (2) Skin panels, together with spar, rib, frame and beam webs, are assumed to be in shear. Addition-

ally, skins may carry tension or compression loads. In the case of compression, loads are assumed to be carried only by a small width of skin along the line of fasteners attaching skin to substructure.

(3) Stringers may be in tension or compression. 5.

PRIMARYAND SECONDARY STRUCTURE A.

B.

Primary structure is considered to be that structure that is essential to continued safe flight and landing. Examples of this would be wing (spars, skins, ribs, fittings, etc.), fuselage, empennage, control structure systems/support and mechanisms, engine mounts and pylon structure, landing gear and actuator including attachment fittings, main cabin door and attachments, windshield, cabin windows, escape hatch, and underwing keel beam. Secondary structure is that not considered essential for continued safe flight and landing. Examples of this would include fairings (wing-ta-body etc.), gear doors, nose access doors, dorsal fin, upper tail fairing, parts of pylon fairvertical fin mailbox fairing, tailcone access door, horizontal-to-vertical ing and nacelle covers.

EFFECTNTTY:

ALL

51-00-00

Page SRM-4

3

lun 1/95

5PrF~

F=

I

Item

No.

Section Title

(n

Chapter

1

Doors

52

2

I~uselage Nacelles/PyIons

53

3 4

Stabilizers

55

5

Windows

56

6

Wings

57

=D C

0,

C)

54

~3

0 O

t

b

q~

I rp,

^B

~X1 m IC~

n~

b ~II

d

P

C] ;3~1p9

OQOO r

a

r"

P,

a

´•Z~h; b

6

u,

,__,,

r--

I I

I

I

I

,_’____J

C) ~CI

r

n

h3~

F

m

a

o hi

~JY v=l

I

vl NUI

Laarjet I Learjet STRUCTURAL REPAIR MANUAL

Forward Pressure Bulkhead FS 60.04

Forward Edge of Door FS 119.66

Aft

Edge of Door

FS 146.51 (24" Door) FS 158.48 (36" Door)

Aft Pressure Bulkhead F5272.44

Engine Beam Floorboards FS 90.74 to FS 196.65

WL 5.875 Constant

FS 51.89 (Extended)

j

FS 52.90 (Static)

FS 308.86

WL 42.83

FS 246.06 (Extended) FS 246.85 (Static)

(TYPICAL) 14-6M: blOD)

EFFECTTVITY:

Major Structural Member Locations Figure 2 (Sheet 1 of 2) MODEL23/24 SERIESAIRCRA~T

51-00-00

Page 6 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Baggage Compartment Floor FS 196.65 to FS 272.44 WL 24.80

Aft Keel Beam

Keel Beam (Under Wing) FS 196.65 to FS 271.39

FS 271.39 to FS 308.86

WL 0.00 at Forward End WL 7.58 at Aft End

WL 10.31 at Aft End

WL 7.58 at Forward End

(TYPICAL) 14-214B (MOD)

EFFECTJVITY:

Major Structural Member Locations Figure 2 (Sheet 2 of 2) MODEL23/24 SERIESAIRCRAFT

51-00-00

Page 7 SRM-4

May ’15/92

Learjet STRUCTURAL REPAIR MANUAL

Forward Pressure Bulkhead r

FS 174.01

Aft Pressure Bulkhead FS381.79 (25C/25FAircraft)

Forward

Edge of Door

FS 233.69 Aft

Edge of Door

Aft Pressure Bulkhead FS 421.41 (25/25A/25B/25D Aircraft)

FS 260.48 (24" Door) FS 272.41 (36" Door)

ooo

ol

Floorboards FS 184.78 to FS 346.63 WL 5.875 Constant

Engine Beam FS 458.84 Nac Sta 52.35

FS 165.87 (Extended) FS 166.87 (Static) FS 167.13 (Deflated)

FS 396.03 (Extended) FS 396.83 (Static) FS 397.00 (with Nose Deflated)

(TYPICAL) Repro

EFFECTIVITY: SRM-4

Major Structural Member Locations Figure 3 (Sheet 1 of 2) MODEL 25 SERIES AIRCRAFT

51-00-00

Page 8 May15/92

Leariet

STRUCTURAL REPAIR MANUAL

Baggage Compartment WL 24.80 Constant FS 346.62 to FS 421.42 FS 346.62 to FS 381.79

Floor

(25/25A/25B/25D Aircraft) (25C/25F Aircraft)

0000

it,

J

Aft Keel Beam FS 421.42 to FS 458.84

Keel Beam (Under Wing) FS 346.63 to FS 421.42

WL 7.58 at Forward End WL 12.97 at Aft End

--J

WL 0.00 at Forward End WL 758 at Aft End

(TYPICAL) Repn,

EFFECTIVITY: SRM4

Major Structural Member Locations Figure 3 (Sheet 2 of 2) MODEL 25 SERIESAIRCRAF~

51-00-00

Page 9 May 15/92

L9arjet I

STRUCTURAL REPAIR MANUAL

Forward

Edge of Door

FS 233.69 Aft

Edge of Door

FS 260.48 (24" Door) FS 272.41 (36" Door)

Aft Pressure Bulkhead FS 381.79 (29 Aircraft)

Forward Pressure Bulkhead FS 174.01

Aft Pressure Bulkhead FS 402.42 (28 Aircraft)

I

00001

Engine Beam FS 458.84 Nac Sta 52.35

Floorboards

FS 184.78

to FS

346.63

WL 5.875 Constant

FS 165.87 (Extended)

FS 166.87 (Static)

Repro

EFFECTIVITY: SRM-4

FS 396.03 (Extendcd) FS 396.82 (Static)

Major Structural Member Locations Figure 4 (Sheet 1 of 2) MODEL 28/29 SERIESAIRCRAFI~

51-00-00

Page 10 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Baggage Compartment

Floor WL 24.80 Constant FS 346.62 to FS 402.42 (28 Aircraft) FS 346.62 to FS 381.79 (29 Aircraft)

0000

Keel Beam (Under Wing) FS 346.63 to FS 421.42 WL 0.00 at Forward End

EFFECTIVITY: SRM´•I

Aft Keel Beam FS 421.42 to FS 458.84 WL 7.58 at Forward End WL 12.97 at Aft End

WL 7.58 at Aft End

Repro

i

Major Structural Member Locations Figure 4 (Sheet 2 of 2) MODEL 28/29 SERIES AIRCRAFT

51-00-00

Page 11 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Keel Beam (Under Wing) FS 346.63 to FS 421.42 WL 0.00 at Forward End

Baggage Compartment Floor WL 24.80

rAft Pressure Bulkhead

i

FS 346.62 to FS 421.42 FS 346.62 to FS 381.79

FS421.42

Forward Pressure Bulkhead FS 160.77

0000

Aft

Engine Beam

WL 39.82 at Aircraft 473.00

SFenilretneC

Floorboards FS 184.78 to 346.63 WL 5.87 Constant

I\

~Forward Engine WL 40.00

at

Beam

Aircraft Centerline

FS 443.23 FS 152.62 (Extended)

Aft Keel Beam FS 421.42 to FS 458.84 WL 7.58 at Forward End WL 12.97 at Aft End

FS 153.63 (Static) FS 153.88 (Deflated)

FS 396.03 (Extended) FS 396.82 (Static) FS 396.83 (Deflated)

Repro

EFFECTIVITY: SRM´•I

Major Structural Member Figure 5 MODEL31 SERIESAIRCRAFT

Locations

51-00-00

Page 12 May 15/92

Learjet

STRUCTURAL REPA\R NIANUAL

A~t Pressure Bulkhead FS 381.79 (36/36A Aircraft) Aft kessune Bulkhead FS 421.41

(35/35A Aircraft)

Forward Pressure Bulkhead FS 160.77

0000

1

1

I

Aft Engine Beam FS 473.00

FloorboaTds FS 184.78

to

FS 346.63

WL 5.875 Constant

FS 152.62 (Extended)

FS 153.63 (Static) FS 153.88 (Deflated)

I~pro

EFFECTNITY: SRM~

j

Fonuard Engine Beam FS 443.23

FS 3%.03 (Extended) FS 396.82 (Static) FS 3%.83 (Deflated)

Major Structural Member Locations Figure 6 (Sheet 1 of 2) MODEL35/36SERIES ATR~RAFT

51-00-00

rage 13 May 15/92

Learjet Leariet i STRUCTURAL REPAIR MANUAL

Aft

Engine Beam

WL 39.82

Aircraft Centerline

Forward Engine Beam Aircraft Centerline WL 40.00

Baggage Compartment Floor WL 24.80 Constant FS 346.62 to FS 421.42 (35/35A Aircraft) FS 346.62 to FS 381.79 (36/36A Aircraft)

g

0000

1

II-~- ~t--_

Aft Keel Beam Keel Beam (Under

FS 346.63

to

Wing)

---´•r

FS 421.42

WL 0.00 at Forward End WL 7.58 at Aft End

Repro

EFFECTn7ITY: SRM-4

FS 421.42 to FS 458.84 WL 758 at Forward End WL 12.97 at Aft End

Major Structural Member Locations Figure 6 (Sheet 2 of 2) MODEL 35/36SERIES AIRCRAFT

51-00-00

Page 14 May 15/92

~li´•t I

STRUCTURAL REPAIR MANUAL AIRCRAFT MEASUREMENT SYSTEM

i.

STRUCTURAL IDENTIFICATION

AIRCRAFTMEASUREMENT SYSTEM DESCRIPTION A.

This section

B.

presents

The dimensions of the aircraft and the for reference

areas

of the control surfaces

are

carried to the nearest full inch.

not for

are only inspection purposes. points along three axes and are measured in inches. These reference points provide a means of quickly identifying the location of a bulkhead, component, etc. (I) Fuselage station (FS), water line (WL), and buttock line (BL) measurements used in this manual

These dimensions C.

the aircraft dimensions, control surface areas, water lines, buttock lines, and sta-

designations.

tion

are

and

The aircraft is divided into reference

are

rounded to the nearest inch. points may be converted to metric measurement (millimeters)

D.

All reference

E.

The

by multiplying

the refer-

point tin inches) by 25.4. following terms are used for reference points.

ence

Fuselage

FS

ence

line

station is on or near

Water line is

WL

a

a

vertical reference

the

nose

plane

measured

horizontally

from

a

vertical refer-

of the aircraft.

horizontal reference

plane measured vertically

from the horizontal reference

line of the aircraft. vertical reference

plane measured horizontally

from the aircraft centerline.

BL

Buttock line is

WS

Right or left is added to indicate the direction from aircraft centerline (RBL Wing station is a vertical reference plane measured horizontally from the

a

LBL).

wing

centerline

and

perpendicularly along wing datum. Centerline is the center reference point of the aircraft or component.

CL

Reference

NACSTA

points that apply to

the

engine nacelle.

NAC WL NAC BL TIP TANK STA

Reference

points that apply to

Reference

points that apply to the winglet.

the

tip tank.

?T WL TI BL

WINGLET STA OML

Outside Mold Line is that line

IML

formed part. Inside Mold Line is that line formed

EFFECTIVITY:

ALL

corresponding corresponding

to the outside contour of

to the inside contour of

a

a

fuselage

skin

or

fuselage

skin

or

part.

51-00-01

Pagel SRM-4

Jun 1/95

Learjet I STRUCTURAL REPAIR MANUAL

14 ft. 8 in.

12

Q

1 fti3

in.

43 ft. 3 in.

O

O

34 ft. 1 in.

Repro

Aircraft Measurement

System

Dimensions

Figure 1(Sheet 1 of 13) EFFECTIVITY: SRM~

MODEL 23/24SERIESAIRCRAFT

51-00-01

Page 2 May 15/92

STRUCTURAL REPAIR NIANUAL Subject

Dimensions

Aircraft

Span (overal ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Span (excluding tip tank fins) Length (overall) Height (overall)

35 ft. 7 in. 34 ft. 1 in. 43 ft. 3 in. 12 ft. 3 in.

Wing Root Chord

fuselage centerline)

9 ft. 0 in.

Chord WS 181) Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 1 in. 2" 30’

Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

13"

Incidence

+lo

Aileron

Span (nominal)

4 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 5 in.

Tip Chord Trim Tab Span (LH only). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Balance Tab Span (RH LH). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 1 in. 1 ft. 3 in. 1 ft. 9 in.

Flaps

Type Span(nominal)

Single Slotted 9 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 ft. 4 in.

Tip Chord

1 ft. 8 in.

Horizontal Stabilizer

Span

14 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 0 in.

Tip Chord Sweepback (c/4 chord)

2 ft. 4 in. 25"

Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

O"

EIevators

Span (per side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 ft. 4 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

I ft. 4 in.

Tip Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 in.

Aircraft Measurement

Figure EFFECTIVITY:

System

Dimensions

1 (Sheet 2 of 13)

MODEL 23/24 SERIESAIRCRAFT

51-00-01

Page SRM-4

3

May 15/92

Leariet I STRUCTURAL REPAIR MANUAL Vertical Stabilizer 5 ft. 6 in.

Span

g ft´• 11 in.

Root Chord. . . . . . . . . . . . . . . ´•. ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•

Tip Chord Sweepback

5 ft. 1 in. 35" 36’

leading edge)

Fuselage Fuselage Constant Section Outside diameter

5 ft´• 3 in.

Inside diameter

4 ft. 9 in.

8 ft´• 8 in.

Length of passenger area.....................................´•´•´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• Height (floor to ceilng). . . . . . . . . . . . . . . . . . . . . ´•.-´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•-´• ´• ´• ´• ´• ´•

4 ft´• 4 in.

Miscellaneous Areas 231.90 ft.

Wing (WS 0.0 to WS ~81.10) Aileron (per side, aft of hinge line) Aileron Trim Tab (LH only) Aileron Balance Tab (LH

5´•854 ft. 0.335 ft. 1´•25 ft.

RH)

7´•0 ft´• 54´•0 ft.

Horizontal Stabilizer (total)

(excluding elevator)

15´•94 ft.

Vertical Stabilizer (total)

37´•48 it.

Vertical Stabilizer

2

30´•63 ft.

(excluding rudder)

Rudder

6.85 ft.

Rudder Trim Tab

0´•69 ft.

Aircraft Measurement

Figure

SRM-4

2

38.06 ft.

...............................................i...................................................................

Elevator

EFFECTnTITY:

2

36´•85 ft.

Flaps (total) Spoilers (total) Stabilizer

2

System

2

Dimensions

1 (Sheet 3 of 13)

MODEL23/24 SERIESAIRCRAFT

51-00-01

Page 4 May 15/92

Leariet

S~RUCTURAL REPAIR MANUAL

25% Chord

Fuselage Vertical Centerline

25% Chord

RBL

Buttock Lines

Wing Stations

(BL 0.00)

cws o.oo,

LBL

Fuselage Stations

(FS -13.976)

Waterlines (WL 0.00)

BL 43.70

WL 42.83

Nacelle CL --/I

Fuselage Vertical Centerline

Aircraft Measurement

Figure EFFECTIVITY: SRM-II

System

Reference roints

1 (Sheet 4 of 13)

MODEL23/24 SERTESAIRCRAFT

51-00-01

Page 5 May 15/92

Learjet Learjet 1 STRU CTU RA L R EPAIR MAN UA L I

sta. 474. 60

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Aircraft Measurement

Figure EFFECTIVITY: SRM-P

1

MODEL 23/24 SERIES AIRCRAFT

System

Fuselage Stations

(Sheet 5 of 13)

51-00-01

Page 6 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

WL 52.08 Door

Passenger/Crew

Hinge CL

Fuselage Cross Section

WL 24.80

WL 5.87 WL 0.82

WL 0.00

14-1318

Aircraft Measurement

Figure EFFECTTVITY:

System

Top of Baggage Floor

Top of Floorboard

Passenger/Crew Door Hinge CL (Typical Frame 9 to Frame 15)

Fuselage Stations

1 (Sheet 6 of 13)

MODEL 23/24 SERTESAIRCRAFT

51-00-01

Page SRM~

7

May 15/92

Learjet STRUCTURAL REPAIR MANUAL Stringere

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Stringer 13 Stringer 14

Stringer 14 Stringer 15

Stringer 16 Stringer 17 Stringer 18 Stringer 19

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Stringer 16 Stringer 17 Stringer 18 Stringer

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Stringer 21-~

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(FRAME 11 LOOKING AFT)

Aircraft Measurement

Figure EFFECTIVITY:

1

MODEL 23/24 SERIES AIRCRAF~

System

Fuselage Stations

(Sheet 7 of 13)

51-00-03

PageS SRM~

May 15/92

~earjet

STRUCTURAL REPAIR MANUAL B. L. D. 00

Stringer~

Stringer 2

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Stringer 3 Stringer 4

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Stringer Stringer 6 Stringer

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Stringer 9 Stringer 10

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Stringer 15 Stringer 16 Keel Beam Web

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Stringer 18 Stringer 19

Stringer

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Aircraft Measurement

Figure

EFFECTIVITY:

St’i"per 12

B. L. 0.00

13

Longeron

System Fuselage Stations

1 (Sheet 8 of 13)

MODEL 23/24 SERIES AIRCRAFT

51-00-01

Page SRM~

9

May 15/92

Learjet STRUCTURAL REPAIR MANUAL C~

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Aircraft Measurement

System Wing, Aileron and Flap Stations Figure 1 (Sheet 9 of 13)

EFFECTIVITY: SRM-b

MODEL 23/24 SERIES AIRCRAFT

51-00-01

Page 10 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL Tip Tank Sta. 0. 00

,Tip Tank 15.70

Sta.

Tip Tank Sta. 46.00

Tip Tank Sta. 83.85

Tank

-Tip

98.86

Sta.

Tip Tank Sta.

Tip

113.60

Tank

Sta. 149.94

Tip Tank Sta.

160.42

Tip Tank Sta.

113.30

TIP TANK STRUCT~RAL STATIONS

Aircraft Measurement

Figure EF~CTIVITY:

1

System

Tip

Tank Stations

(Sheet 10 of 13)

MODEL 23/24 SERIESAIRCRAFT

51-00-01

Page SRM-4

11

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

BL 0. 00 BL

9.512 1

BL 19. 40

BL 34. 80

HORIZONTAL STABILIZER

BL 50. 20

STRUCTURAL STATIONS

1

BL 65. 60 BL

I

.~r

81.00I,

a’

s

BL 88. 20

BL 4. 50

BL 13. 24

BL

54

BL 23. 17

BL 33. 11 BL 44. 10 BL 56. 23

BL 86. 215

BL 67. 79 BL 79. 35

i Ji;

CI

ELEVATOR

STRUCTURAL STATIONS

BL 1. 49

BL 81. 77

Aircraft Measurement

EFFECTIVITY: SRM4

System Horizontal Stabilizer and Elevator Stations Figure 1 (Sheet 11 of 13)

MODEL 23/24 SERIES AIRCRAFT

51-00-01

Page 12 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

BULLET STRUCTURAL STATIONS

P

STA 459. 350

STA

STA 423. 30

440.104

STA 423. 913

STA 500.023

RUDDER

STRUCTURAL

II)

VERTICAL STABILIZER STRUCTURAL STATIONS

UcL

STATIONS

I----WL 100. 33 WL 96. 00

WL 95.

i

WL 92. 83

WL 85. r

WL 75.

-C-- WL 72. 56

t

I’

WL 82. 70

f f’

f

WL 65.

i/’

i’

Aircraft Measurement

EFFECTIVITY: SRM~

System Figure

wt 61.96

Vertical Stabilizer and Rudder Stations 1 (Sheet 12 of 13)

MODEL23/24 SERIESAIRCRAI;T

51-00-01

Page 13 May 15/92

0~0\

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Aircraft Measurement

System Dimensions Figure 2 (Sheet 1 of 13)

EFFEC~IVITY: SRM~L

MODEL25 SERTESAIRCRAFT

51-00-01

Page 15 May 15/92

Learjet Learjetl STRUCTURAL REPAIR MANUAL Dimensions

Subject Aircraft

Span (overal ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Span (excluding tip tank fins) Length (overall) Height (overall)

35 ft. 7 in. 34 ft. 1 in. 47 ft. 7 in.

12 ft. 3 in.

Wing Root Chord

9 ft. 0 in.

(fuselage centerline)

5 ft. 1 in.

Chord (O WS 181)

2" 30’

Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

13"

Incidence

1"

Aileron

Span (nominal)

4 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 5 in.

Tip

Chord

I ft. 1 in.

Span (LH only) Balance Tab Span (RH LH). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Trim Tab

1 ft. 3 in. 1 ft. 9 in.

Flaps Type

Single Slotted

Span(nominal)

9 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 ft. 4 in.

Tip

Chord

1 ft. 8 in.

Horizontal Stabilizer

Span

14 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. O in.

Chord

Tip Sweepback (c/4 chord)

2 ft. 4 in. 25"

Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

O"

Elevators

Span (per side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 4 in.

Tip

Chord

7 in.

Aircraft Measurement

Figure EFFECTIVITY’: SRM-4

MODEL 25 SERIES AIRCRAI~T

2

System

Dimensions

(Sheet 2 of 13)

51-00-01

Page 16 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Vertical Stabilizer

Span

5 ft. 6 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8 ft. 11 in.

Tip Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 1 in. 35" 36’

Fuselage Fuselage Constant Section Outside diameter

5 ft. 3 in.

Inside diameter

4 ft. 9 in.

Length of passenger area.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Height (floor to ceil ng). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

11 ft. 4 in. 4 ft. 4 in.

Miscellaneous Areas

Wing Aileron

231.8 ft.

(per side)

5.854 ft.

Aileron Trim Tab (LH

only)

Aileron Balance Tab (LH

0.335 ft.

RH)

1.25 ft.

Flaps (total) Spoilers (total)

36.85 ft. 7.0 ft.

Horizontal Stabilizer (total)

54.0 ft.

Stabilizer

40.4 ft.

(excluding elevator)

Elevator

13.6 ft.

Vertical Stabilizer (total)

38.35 ft.

Vertical Stabilizer

31.80 ft.

(excluding rudder)

Rudder

6.55 ft.

Rudder Trim Tab

0.69 ft.

Aircraft Measurement

Figur~! EFFECTNITY: SRM~

MODEL 25 SERIES AIRCRAFT

System

2

2 2 2 2 2 2 2 2 2 2 2

2

Dimensions

2 (Sheet 3 of 13)

51-00-01

Page 17 May 15/92

Leariet STRUCTURAL REPAIR MANUAL

25% Chord

25% Chord

Fuselage Vertical Centerline

RBL

Buttock

Lines

LBL

Wing Stations

(BL 0.00)

(WS 0.00)

Fuselage Stations

(FS 100.00)

QOC1[3

Waterlines (WL 0.00)

BL 43.70 WL 42.8

Nacelle CL

Fuselage Vertical Centerline

Aircraft Measurement System

ReferencL´• Points

Figure 2 (Sheet 4 of 13) EFFECTNITY: sRM~

MODEL 25SERIESAIRCRAFT

51100-01

Page 18 May 15/92

Learjet I

STRUCTU RAL REPAIR MANUAL J(

Measured at OML of Bulkhead Intersection with Bottom ~of

fuselageskin,

99t~L*

Inside Mold Line (IML)

9’9:~;"\ eze\

1T

Outside Mold Line (OML)

~p’C

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9

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4*’

16RB1

Aircraft Measurement

Figur~! EFFECTIVITY: SRM~

MODEL25 SERIESAIRCRAF~

2

System Fuselage Stations (Sheet 5 of 13)

51MM1

Page 19 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

WL 52.08 Door

Passenger/Crew

Hinge CL

Fuselage Cross Section

WL 24.80

Top of Baggage Floor

WL 5.87 Top of Floorboard

WL 0.82 WL 0.00

14-131B

EFFECTIVITY: SRM-4

Passenger/Crew Door Hinge CL (Typical Frame 9 to Frame 15)

System Fuselage Stations Figure 2 (Sheet 6 of 13)

Aircraft Measurement

MODEL 25 SERIES AIRCRAFT

51-00-01

Page 20 May 15/92

Learjet Learjetl

STRUCTURAL REPAIR NIANUAL Stringer

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System Fuselage Stations Figure 2 (Sheet 7 of 13)

Aircraft Measurement

EFFECTIVITY:

MODEL25 SERIESAIRCRAFT

51-00-01

Page SRM-4

21

May 15/92

Learjet STRUCTURAL REPAIR MANUAL B. L. 0.00

Stringer 2 Stringer

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Stringer 18 Stringer 19

Stringer

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(FRAME 13 LOOKING AFT) Stringer 2 Stringer 3 Stringer Stringer 5 Stringer 6 Stringer 7

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MODEL 25SERIESAIRCRA~T

2

10

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12

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(FRAME 17 LOOKING AFT)

Figure

SRM~

0.00

\iM

Aircraft Measurement

EFFECTIVITY:

7

I

Longeron

System Fuselage Stations

(Sheet 8 of 13)

51-00-01

Page 22 May 15/92

Learjet STRUCTURAL REPAIR MANUAL CT

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System Wing, Aileron and Flap Stations figure 2 (Sheet 9 of 13)

Aircraft Measurement

EFFECTTVITY:

MODEL 25 SERIESAIRCRAFT

51-00-01

Page 23 S~M-4

May 15/92

Learjet STRUCTURAL REPAIR MANUAL Tip Tank Sta. 0.00

,Tip Tank Sta.

Tip

15.70

Tank

Sta. 46. 00

Tip Tank Sta.

83.85

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98.86

Tip Tank Sta.

113.60

Tip Tank Sta.

149.94

Tip Tank Sta.

160.42

Tip Tank Sta.

1?3.30

TIP TANK STRUCTURAL

STATIONS

Aircraft Measurement

Figure EFFECTIVITY: SRM~

MODEL 25 SERIES AIRCRAFT

System Tip Tank Stations

2 (Sheet 10 of 13)

51-00-01

Page 24 May 15/92

Learjet Leariet

STRUCTU RAL REPAIR MANUAL

BL 0. 00 BL

3.:2 1

BL 19. 40

B:L 34. 80

HORIZONTAL STABILIZER

BL 50. 20

STRUCTURAL STATIONS BL 65. 60 BL 81. 00 BL 88. 20

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1~79.

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67.

STATIONS

79Ji" i

BL 1. 49

BL 81. 77

Aircraft Measurement

EFFECTIVITY: SRM~

System Horizontal Stabilizer and Elevator Stations Figure 2 (Sheet 11 of 13)

MODEL 25SERIES AIRCRA~

51MM1

Page 25 May 15/92

Leariet

STROCTURAL REPAIR MANUAL

STA

STA

SI~A 644.89

STA

606.084

589.28

624.63

VERTICAL STABILIZER STRUCTURAL STATIONS ii

RUDDER

STRUCTURAL STATIONS

I/

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Aircraft Measurement

EFFECTIVITY: SRM-4

System Vertical Stabilizer and Rudder Stations Figure 2 (Sheet 22 of 13)

MODEL 25SERIESAIRCRAFT~

51-00-01

Page 2~ May 15/92

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STRUCTURAL REPAIR MANUAL

14 ft. 8 in.

I

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I I~ft.lin.

45 ft. O in. 47 ft. 7 in.

8 ft. 3 in. 43 ft. 8 in.

Aircraft Measurement

System Dimensions Figure 3 (Sheet 1 of 13)

EFFECTIVITY: SRM-4

MODEL 28/29 SERIES AIRCRAFT

51-00-01

Page 28 May 15/92

~Rariet

STRUCTURAL REPAIR MANUAL Subject

Dimensions

Airoaft

Span (overal ). . ., . . . . . . . . . . . . . . . . . . . . . . . . ., . . . . . . . . . . . . . . . . . . . . . Length (overall) Height (overall)

43 ft. 8 in. 47 ft. 7 in. 12 it. 1 in.

Wing Root Chord Chord

(fuselage centerline)

9 fc~ 0 in.

WS 181)

5 ft~ 1 in.

20 30’

Sweepback

13´•

Incidence

´•1´•

Aileron

Span (nominal)

4 ft. 8 in.

Root Tip Chord

1 ft. 5 in.

Span (LH only)........................................ Balance Tab Span (RH

1 ft. 3 in.

1 ft 1 in.

Trim Tab

1 ft. g in.

Flaps

Type Span(nominal)

Single Slotted g ft~ 2 in,

Root

2 ft. 4 in.

Tip

I ft. 8 in.

Horizontal Stabilizer

Span

14 ft. g in.

Root

5 ft. O in.

Tip Chord Sweepback (c/4 chord)

2 ft~ 4 in.

250 O´•

Elevators

Span (per

7 it. 2 in.

Root

1 ft. 4 in.

Tip

7 in.

Aircraft Measurement

System

Dimensions

Figure 3 (Sheet 2 of 13) EFFECTIVITY: SRM-L

MODEL28/29SERIES ATRCRAFT

51-00-01

Page 29 May 15/92

Learjet STRUCTURAL REPAIR MANUAL Vertical Stabilizer 5 ft. 6 in.

Span

8 ft. 11 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . ´•. ´•. . .´• ´• ´• ´•. .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•

Tip

5 ft. 1 in.

Chord

35" 36’

Sweepback (c/4). . . . . . . . . . . . . . . . . ´• ´• ´•. .´• ´• ´• ´• ´• .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• Fuselage

Fuselage Constant Section Outside diameter

5 ft. 3 in.

Inside diameter

4 ft. 9 in. 11 ft´• 4 in.

Length of passenger area Height (floor to ceilng). . . . . . . . . . . . . . . . ´•. .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•

4 ft´• 4 in.

Miscellaneous Areas 212.9 ft.

Wing Aileron

5´•854 ft.

(per side)

Aileron Trim Tab (LH

2 0´•335 ft.

only)

Aileron Balance Tab (LH

1.25 ft.

RH)

36´•85 ft.

Flaps (total) Spoilers ~total)

7´•0 ft.

40´•4 ft.

(excluding elevator)

2

2

2 13´•6 ft.

Elevator

38´•35 ft.

Vertical Stabilizer (total) Vertical Stabilizer

2

54´•0 ft.

Horizontal Stabilizer (total) Stabilizer

2

2

31.80 ft.

(excluding rudder)

Rudder

2 6´•55 ft.

Rudder Trim Tab

0´•69 ft.

Aircraft Measurement

Figure EFFECTIVITY: SRM-4

System

2

Dimensions

3 (Sheet 3 of 13)

MODEL28/29 SERIESAIRCRAFT

51-00-01

Page 30 May 15/92

STRUCTURAL REPAIR MANUAL

25% Chord

Fuselage Vertical

25% Chord

Centerline

RBL

Buttock Lines

(BL 0.00)

LBL

Wing: Stations (WS 0.00)

Fuselage Stations

(FS 100.00)

00[30

Waterlines

(WL 0.00)

8~43.70--\

Nacelle CL

(I

I

Wt 42.83

’’cFuselage Vertical Centerline

Aircraft Measurement

System Reference Points Figure 3 (Sheet 4 of 13)

EFFECTNITY:

MODEL28/29 SERIESAIRCRAFT

51-00-01

Page 31 sRM-a

Jun 1/95

STRUCTURAL REPAIR MANUAL Measured at OML of Bulkhead Intersection with Bottom ~pf

fuselage skin.

´•r\* 9’59P.

pp

~L

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Inside Mold Line (IML)

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Aircraft Measurement

Figure EFFECTTVITY: slM~

System Fuselage Stations

3 (Sheet 5 of 13)

MODEL 28/29SERIESAIRCRAFT

51MH)1

Page 32 May 15/92

Learjet Ledljet

STRUCTURAL. REPAIR MANUAL

Passenger/Crew Hinge CL

WL 52.08 Door

Fuselage Cross Section

WL 24.80

WL 5.87 WL 0.82

WL 0.00

14-1318

EFFECTIVITY: SRM-4

Top of Baggage Floor

Top of Floorboard

Passenger/Crew Door Hinge CL CTypical Frame 9 to Frame 15)

System Fuselage Stations Figure 3 (Sheet 6 of 13)

Aircraft Measurem~,nt

MODEL 28/29 SERIES AIRCRAFT

51-00-01

Page 33 May 15/92

Learjet I STRUCTURAL REPAIR MANUAL Stringer 9

Stringer 9

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Stringer 10

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111

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6

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11

Stringer

12

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Aircraft Measurement

Figure EFFECTTVITY: SRM4

System

Fuselage Stations

3 (Sheet 7 of 13)

MODEL 28/29SERIESAIRCRAFT

51-00-01

Page 34 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL B.L. 0.00

Stringer

Stringer 2 Stringer 3 stringer 4 Stringer 5 Stringer 6

2

Stringer 3 Stringer

4o

Stringer 5 Stringer 6 Stringer 7

1

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Stringer

9

Stringer 10

Stringer 11 Door Frame

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Stringer 13

Seat Track

Stringer 14

Stringer 15 Stringer I

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Keel Beam Web

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21

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(FRAMIE 13 LOOKING AFT) Stringer

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Stringef~cStringer 2 r

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Stringer 9

Stringer 10

I Support

Support

Stringer 11

~B.L.

Stringer 12 Stringer 13

Longeron

St ringer 6

Stringer 7

Splice

Stringer 8

StringerlO

3

Stringer 4

\itl

0´•00

(FRAME 17 LOOKING AFT) Aircraft Measurement

Stringer 11

Stringer 12 13

Longeron

System Fuselage Stations

3 (Sheet 8 of 13)

EFFECTNITY: SRM-4

MODEL 28/29 SERIES AIRCRAF~

51-OM)1

Page 35 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL dLO$r P: WING STRUCTURAL

STATIONS

-W. S. 244. 102 W.S. 233.102

w. s.

213. 602

AILERON STRUCTURAL STATIONS

59.46~ 51.40’

i

~51.10

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W´• S´•

Isl´• 02

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42. 66~

66---1 le ~--29. 35

34’

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125. 00

117.10’

108.10

106.15

104´•

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86.50

dj j

77.70 69.

60.05’

i

51.10C

24.8542.

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W.S. 53.04

00

j

37.85 31.35

i

15. 81e Lj~L-L---U

W. S~ 0. 00

FLAP STRUCTURAL

STATIONS

System Wing, Aileron and Flap Stations Figure 3 (Sheet 9 of 13)

Aircraft Measurement

EFFECTIVITY: SRM-L

MODEL28/29 SERIESAIRCRAFT

51MHll Page 36

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Winglet STA 44.87

Winglet STA 44.87

Winglet S7;4

17.91

Winglet STA 17.91

Wing Reference Plane

Winglet STA 0..00

Winglet STA 0

Winglet Datum Plane

(VIEW LOOKING AFII)

(LH SHC)WN, RH TYPICAL)

4~ss

Aircraft Measurement

System W´•inglet Stations Figur~!3(SheetlOofl3)

EFFECTIVITT"Y: SRM~

MODEL 28/29 SERIESAIRCRAFT

5’1-0001

Page 37 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

BL 0. 00 BL

9.:2 1

BL 19. 40

BL 34. 80

HORIZONTAL STABILIZER

BL 50. 20

STRUCTURAL STATIONS BL 65. 60

P

d

b-I

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BL 4. 50

BL 13. 24

BL

i?´•54

BL 23. 17

BL 44.

10BL

BL 56. 23

BL 86. 215

rilBLBL 79. 35

67. 79

i’

33. 11

1

ELEVATOR STRUCTURAL STATIONS

BL 1. 49

BL 81. 77

Aircraft Measurement

EFFECTIVITY: srun~

System Horizontal Stabilizer and Elevator Stations Figure 3 (Sheet 11 of 13)

MODEL 28/29 SERIES AIRCRAFT

51-00-01

Page 38 May 15/92

I

Lear Lealjet

STRUCTURAL REPAIR MANUAL

STA 589. 28

STA

STA

STA

606. 084

624. 63

64C 89

VERTICAL STABILIZER STRUCTURAL STATIONS

RUDDER STRUCTURAL

STATIONS

II

JI

81

I

II

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II

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Aircraft Measurement

EFFECTTVITY: SRM-4

System Vertical Stabilizer and Figure 3 (Sheet 12 of 13)

MODEL 28/29SERIESAIRCRAFT

Rudder Stations

51-00-0)

Page 39 May 15/92

~30

b~Q\

8 %b=; 56

E

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Learjet Ledrjet STRUCTURAL REPAIR MANUAL

14 ft. 8 in.

8 ft. 2 in.

12 ft. 3

n

00

C1

O O

20 ft. 2 in. 48 ft. 7

8 ft. 3 in. 43 ft. 8 in.

System Dimensions Figure 4 (Sheet I of 13)

Aircraft Measurement

EFFECTIV~TY: SRM~

MODEL31 SERTESAIRCRAFT

51-00-01

Page 41 May 15/92

Learjet i STRUCTURAL REPAIR MANUAL Subject

Dimensions

Aircraft

Span (overal ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Length (overall).......... Height (overall)

43 ft. 8 in.

48 ft. 7 in. 12 ft. 3 in.

Wing Root Chord

Chord

(fuselage centerline)

9 ft. 0 in.

WS 181.1)

5 ft. 1 in. 20 30’

Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

13´

Incidence

lo

Aileron

Span (nominal)

qft. gin.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 5 in.

Tip

Chord

1 ft. 1 in.

Trim Tab

Span (LH only) Balance Tab Span (RH LH). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 3 in. 1 ft. 9 in.

Flaps Type Span(nominal)

Single Slotted 9 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Tip

2 ft. 4 in.

Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 8 in.

Horizontal Stabilizer

Span

14 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 0 in.

Chord

Tip Sweepback (c/4 chord)

2 ft. 4 in.

250 O´•

Elevators

Span (per side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 4 in.

Tip

Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 in.

Aircraft Measurement

Figure EFFECTIVITY: SRM-4

MODEL31 SERIESAIRCRAF~

4

System

Dimensions

(Sheet 2 of 13)

51-00-01

Page 42 May 15/92

Learjet STRUCTURAL REPAIR MANUAL Vertical Stabilizer 5 ft. 6 in.

Span

8 ft. 11 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 1 in.

Tip Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .´• . ´• ´•.´• . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• .´• ´• ´• ´• ´• ´• ´• ´• ´• Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . .´• .´• ´• ´• ´• ´• ´•.´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•

35" 36’

Fuselage Fuselage Constant Section Outside diameter

5 ft. 3 in.

inside diameter Length of passenger area Height (floor to ceil ng). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 ft. 9 in. 11 ft. 4 in. 4 ft. 4 in.

Miscellaneous Areas 2 264.5 ft.

Wing (excluding winglets) Wing (total) Aileron

(per

12.0 ft.

5.854 ft.

side)

Aileron Trim Tab (LH

0.335 ft.

only)

Aileron Balance Tab (LH

1.28 ft.

RH)

36.85 it.

Flaps (total)

7.0 it.

Spoilers (total) Horizontal Stabilizer (total)

54.0 ft.

Stabilizer

40.4 ft.

(excluding

elevator)

13.6 ft.

Elevator

3835~t.

Vertical Stabilizer (total) Vertical Stabilizer

31.80 ft.

(excluding rudder)

6.55 ft

Rudder

0.69 ft.

Rudder Trim Tab

26.34 ft.

Delta Fins (totai). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Aircraft Measurement

Figure

EFFECTIVITY: SRM-4

2

MODEL31 SERIESAIRCRAFT

System

2

2 2 2

2 2 2

Dimensions

4 (Sheet 3 of 13)

51-00-01

Page 43 May 15/92

STRUCTURAL REPAIR MANUAL 25% Chord

25% Chord

Fuselage Vertical Centerline

RBL

L LBL

Buttock Lines

wi"s Stations

(BL 0.00)

1 I

cws o.oo,

Fuselage Stations

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I

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Aircraft Measurement

System I~eference Points Figure 4 (Sheet 4 of 13)

EFFECTIVITY: SRM-4

MODEL31 SERIESAIRCRAF~

51-00-01

Page 44 May 15/92

Learjet I Leariet

STRUCTURAL REPAIR MANUAL Measured at OML of Bulkhead Intersection with Bottom Bpf

CX ,e~s c

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aS

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Aircraft Measurement

Figure EFFECTIVITY:

SRM-4

MODEL31 SERIESAIRCRAFT

4

System

Fuselage Stations

(Sheet 5 of 13)

51-00-01

Page 45 Jun1/95

Learjet STRUCTURAL REPAIR MANUAL

Passenger/Crew Hinge CL

WL 5208 Door

Fuselage Cross Section

WL 24.80

Top of Baggage Floor

WL 5.87 Top of Floorboard

WL 0.82 WL 0.00

14-1318

Aircraft Measurement

Figure EFFECTIVITY: saM~

MODELS1 SERTESAIRCRAFT

4

Passenger/Crew Door Hinge CL (Typicai Frame 9 to Frame 15)

System Fuselage Stations (Sheet 6 of 13)

51-00-01

Page 46 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

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System Fuselage Stations Figure 4 (Sheet 7 of 13)

Aircraft Measurement

EFFEC~VITY: S~M4

MODEL31 SERIESAIRCRAFT

51-00-01

Fage47 May 15/92

Learjet

STRU%TURAL REPAIR MANUAL B.L. 0.00

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MODEL31 SERIESAIRCRAFT

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EFFECTIVITY:

3

Stringer 4

Stations

51-00-01

Page 48 May 15/92

Learjet STRUCTU RAL REPAIR MANUAL es~,

"4%%%% I

AILERONSTRUCTURAL

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STA~IONS

WING STRUCTURAL

STATIONS

59.46 ~W.S. 244.102 51.40 ----1---

51.10

34.6624.92

W.S. 233. 102

j

42.66

-----1 11--l

29.35

W.S. 213.602

20.98 15.47

9.59

------\~-w.s. 181.020

w.s. 179.11

W.S. 157.480

126.17 W.S.

117.10

137.61

108.10 104.20

106.15 W.S. 125.000

95.30 86.50 77.70

I-------Y

69.00

IZ\T

w.s. 92.520

60.05 51.10 4215 37.85 31.35

----1-------~

40.00 W.S. 53.040

24.85 15.87

I FLAP STRUCTURAL

STATIONS

W.S. 0.000

System Wing, Aileron and Flap Stations Figure 4 (Sheet 9 of 13)

Aircraft Measurement

EFFECTIVITY: SRM-b

MODEL31 SERIESAIRCRAFT

51-00-01

Page 49 May 15/92

STRUCTURAL REPAIR MANUAL

Wingiet STA 44.87

Winglet STA 44.87

Winglet STA 17.91

Winglet SI~A 17.91

~--Winglet STA Oa0

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Winglet

STA ~.00

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(VIEW LOOKING AFT)

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a-san

Aircraft Measurement

System Winglet Stations

Figure 4 (Sheet

EFFECT~VITY: SRM~

MODEL31 SERIESAIRCRAF~

10 of 13)

51-00-01

Page 50 May 15/92

Leariet STRUCTURAL REPAIR MANUAL

BL 0.00 BL 3.52 BL 19.40

BL 34.80

HORIZONTAL STABILIZER STRUCTURAL STATIONS

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1

I

BL 65.60

BL 81.00

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B

9

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BL

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1

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STRUCTURAL STATIONS

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BL 81.77

Aircraft Measurement

EFFECTIVITY: SRM~

System Horizontal Stabilizer and Elevator Stations Figure 4 (Sheet 11 of 13)

MODEL31 SERIESAIRCRAFT

51-00-01

Page 51 May 15/92

Leartet

STRUCTURAL REPAIR MANUAL

STA.

STA.

589.28

606.084

STA.

STA.

624.63

644.89

VERTICAL STABILIZER STRUCTURAL. STATIONS

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RUDDER STRUCTURAL

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N

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I

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Aircraft Measurement

EFFECTIVZTY: SRM-Q

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MODEL31 SERIESAIRCRAFT

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51-00-01

Page 52 May 15/92

Learie~] STRUCTURAL REPAIR MANUAL

NAC BL 100.00 Nac Sta. 259,10

NAC WL 100.00

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Figure EFFECTIVITY: sRM-4

MODEL31 SERIESAIRCRAFT

System

Nacelle Stations

4 (Sheet 13 of 13)

51-00-01

Page 53 May 15/92

fear ~Learjet

STRUCTURAL REPAIR MANUAL

14 ft. 8 in. 8 ft. 2 in.

12 ft. 3 in.

R F---

000

20 R. 2

C3

in.--------l 48 ft. 7 in.

8 ft. 3 in.

ft. 1 in.

39 ft. 6 in.

Aircraft Measurement

Figure EFFECTIVITY: sRM-4

System

Dimensions

5 (Sheet 1 of 13)

MODEL 35/36SERIESAIRCRAF~

51-00-01

Page 54 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Dimensions

Subject Airoraft

39 ft. 7 in.

Span (overal ). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Span (excluding tip tank fins) Length (overall) Height (overall)

38 ft. 1 in. 48 ft. 7 in. 12 ft. 3 in.

Wing

(fuselage centerline) Tip Chord (8 WS 229)

9 ft. 0 in.

Chord

5 ft. 1 in.

Root Chord

5 ft. 0 in.

WS 181)

Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sweepback (c/4) Sweepback (c/4)

2" 30’

panel (WS 0.0 to 181). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Outer panel (WS 181 to 229) Inner

Incidence

130 20 1"

Aileron

Span (nominal)

4 ft. 9 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 5 in.

Tip Chord Trim Tab Span (LH only). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Balance Tab Span (RH LH). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 1 in. 1 ft. 9 in. 1 ft. 9 in.

Flaps Type

Single Slotted

Span(nominal)

9 ft. 2 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 ft. 4 in.

Tip Chord

1 ft. 8 in.

Horizontal Stabilizer

Span

14 ft. 8 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 ft. 0 in.

Tip Chord Sweepback (c/4 chord)

2 ft. 4 in. 25"

Dihedral. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

O"

Elevators

Span (per side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 ft. 4 in.

Root Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 ft. 4 in.

Tip Chord. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 in.

Aircraft Measurement

System Dimensions Figure 5 (Sheet 2 of 13)

EFFECTIVITY: SRM~

MODEL 35/36SERIESAIRCRAFT

51-00-01

Page 55 May 15/92

E~ STRUCTURAL REPAIR MANUAL Vertical Stabilizer

Span

5 ft. 6 in.

Root Chord. . . . . . . . . . . . . . . . .~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8 ft. 11 in.

Tip Chord Sweepback (c/4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuselage Fuselage Constant

5 ft. 1 in. 35" 36’

Section

Outside diameter

5 ft. 3 in.

Inside diameter

4 ft. 9 in.

Length of passenger area.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Height (floor to ceil ng). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

11 ft. 4 in. 4 ft. 4 in.

Miscellaneous Areas

Wing panel (WS 0.0 to WS 181) Outer panel (WS 181 to WS 229). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

212.9 ft.

Total reference

253.3 ft.

Inner

Aileron

40.4 ft.

area

(per side)

5.854 ft.

Aileron Trim Tab (LH

only)

Aileron Balance Tab (LH

0.335 ft.

RH)

1.28 ft.

maps (total) Spoilers (total)

36.85 ft. 7.0 ft.

Horizontal Stabilizer (total)

54.0 ft.

Stabilizer

40.4 ft.

(excluding elevator)

Elevator

14.13 ft.

Vertical Stabilizer (total)

38.35 ft.

Vertical Stabilizer

31.80 ft.

(excluding rudder)

Rudder

6.55 ft.

Rudder Trim Tab

0.69 ft.

Aircraft Measurement

Figure EFFECTIVITY: SRM~

System

2 2 2

2

2 2 2

2

2 2 2 2 2

2 2

Dimensions

5 (Sheet 3 of 13)

MODEL 35/36SERIES AIRCRAFT

51-00-01

Page 56 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL

25% Chord 25% Chord

Fuselage Vertical

RBL

Centerline

Buttock Lines

LBL

Wing Stations

(BL 0.00)

cwS 0.00)

Fuselage Stations

(FS 87.00)

0000

Waterlines

(WL 0.00~ BL 48.0

WL 49.0

Nacelle CL

Fuselage Vertical Centerline

Aircraft Measurement

System Reference Points Figure 5 (Sheet 4 of 13)

EFFECTNITY: SRM~

MODEL 35/36SERIES AIRCRAFI~

51M)-01

Page 57 May 15/92

STRUCTURAL REPAIR MANUAL 9( 14\

at OML of Bulkhead Intersection with Bottom ~pf

Measured

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Aircraft Measurement

Figure

EFFECTIVITY: SRM~

System

Fuselage

Stations

5 (Sheet 5 of 13)

MODEL 35/36SERIESAIRCRAFT

51-00-01

Page 58 May 15/92

Learjet ~tl STRUCTURAL REPAIR MANUAL

WL 52.08 Door

Passenger/Crew

Hinge CL

Fuselage Cross Section

WL 24.80

Top

of

Baggage Floor

WL 5.87 Top of Floorboard

WL 0.82 WL 0.00

14-1318

EFFECTIVITY: SRM-4

Passenger/Crew Door Hinge CL (Typical Frame 9 to Frame 15)

System Fuselage Stations Figure 5 (Sheet 6 of 13)

Aircraft Measurement

MODEL35/36SERIES AIRCRAFT

51-OM)1

Page 59 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Stringer 9 Stringer 10

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Aircraft Measurement

System Fuselage Figure 5 (Sheet 7 of 13)

EFFECT7VITY: SRM4

MODEL35/36SERIESAIRCRAF;.

Stations

51-00-01

Page 60 May 15/92

L~aljet Learjet

STRUCTURAL REPAIR MANUAL B. L. 0. 00

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Aircraft Measurement

System Fuselage Stations Figure 5 (Sheet 8 of 13)

EFFECTIVITY: SI~M-4

MODEL 35/3CjSERIES AIRCRAFT

51-OM)1

Page 61 May 15/92

Learjet f~

STRUCTURAL REPAIR MANUAL g

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I

86.50 77.70--

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69.00

I

60.05 51.10

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4

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-1

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Aircraft Measurement

System

Figure EFFECTIVITY: SRM4

Wing,

Aileron and

0.00

Flap Stations

5 (Sheet 9 of 13)

MODEL 35/36SERIES AIRCRAFT

51-00-01

Page 62

May15/92

Leariet STRUCTURAL REPAIR MANUAL Tip Tank Sta. 0.00

,Tip Tank Sin.

t5.70

Tip Tank Sta. 46. 00

Tip Tank Sta.

83.85

Tip Tank Sta.

98.86

Tip Tank Sta.

113.60

Tip Tank Sta.

149.94

Tip Tank Sta.

160.42

Tip Tank SCa. 1’13.30

TIP TANK STRUCTURAL STATIONS

Aircraft Measurement System Tip Tank Stations Figure 5 (Sheet 10 of 13)

EFFEeTIVTTY: SRM~L

MODEL 35/36SERIES AIRCRAFT

51-00-01

Page 63 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL

BL 0. 00

BL 19. 40

BL 34. 80

HORIZONTAL STABILIZER

BL 50. 20

STRUCTURAL STATIONS BL 65. 60 BL 8~.00 BL 88. 20

--9

P’

88

I-

1

BL 4´• 50

BL

13:24

BL

54

BL, 23. 17

BL 44. l0 BL 86. 215 BL

35BL,

67.

-iJ97

i;

7

1

Ct

ELEVATOR STRUCTURAL STATIONS

BL L. 49

BL 81. 77

Aircraft Measurement

EFFECTIVITY: SRM~

MODEL

System Horizontal Stabilizer and Elevator Stations Figure 5 (Sheet 11 of 13)

35/36SERIESAIRCRA~T

51-00-01

Page 64 May 15/92

Learjet Learjet STRUCTURAL REPAIR MANUAL

STA

589.28

STA

STA

STA

606.084

624.63

644.89

VERTICAL STABILIZER STRUCTURAL STATIONS ’i

RUDDER

STRUCTURAL STATIONS

r

I I

II

II~

/L-~,

II

/I,

Il

Wt 92. 83

I

I,

WL 100. 33

I

II

WL 85.

I/ I

P

I

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I

I

WL 75. 00 I/

I

I

I’

~WL 82. 70

I

’I II

I´•

I

I

i I

I

(WL 72. 56

I

II

I

II I

/I

WLgg.00

N

/I I

Il ’I

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Aircraft Measurement

EFFE(-TIVITY:

a

czl

I

/I I I

I/ I

.’I

WL 61.96

a

I Il

System Vertical Stabilizer and Rudder Stations Figure 5 (Sheet 12 of 13)

MODEL 35/36SERIES AIRCRAFT

51-00-01

Fage S(M-4

65

May 15/92

STRUCTURAL REPAIR MANUAL

NAC BL 100.00 Nac Sta. 259.10

NAC WL 100.00

a

oa

(LH SmB LDDKING ATT)

p O

P,

Ny O

00

Q)

M

00

DJ

8

o"

(LH SIDE LOOKING INBOARD)

14-1438-2

Aircraft Measurement

Figure EFFECTIVITY: SRM4

System

Nacelle Stations

5 (Sheet 13 of 13)

MODEL 35/36SERIES AIRCRAFT

51-00-01

Page 66 May 15/92

Learjet ~1 STRUCTURAL REPAIR MANUAL RESTRICTED AREAS

STRUCTURAL IDENTIFICATION

RESTRICTED AREAS DESCRIPTION

i.

A.

See

Figure

1 for restricted

area

locations.

XQX

NO STEP AREAS

NO PUSH AREAS

HONEYCOMB::::::::::z:::::;:;:´•na:;x;:;: (TYPICAL) Restricted Area

Repro

Figure

EFFECTIVITY:

MODEL

1

Diagram

(Sheet 1 of 2)

23/24/25/35/36SERIES AIRCRAFT

51-00-02

Pagel SRM~

May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Xi)X~

NO STEP AREAS NO PUSH AREAS

E~

HONEYCOMB

(TYPICAL) Repro

Restricted Area

Figure EFFECTIVITY: snM-4

Diagram

1 (Sheet 2 of 2)

MODEL28/29/31 SERIESAIRCRAFT

51-00-02

Page 2 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ACCESS DOORS AND PANELS

STRUCTURAL IDENTIFICATION

ACCESS DOORS AND PANELS DESCRIPTION

i.

A.

See

Figure

1 for

access

doors and

panels locations. 03

2

30

I

07 36

to

03

JO

"2f 318 II

CT)

9.

1.

FuelFiller

2.

FuelProbe

3.

TipTank Access Directisyn

5.

Equipment, Oxygen and Air Bottles Emergency Exit Window Fuselage FuelTank Probe WingTipFueland ElectricalConnections

7. 8.

o~

II

Vertical Stabilizer Attach Points and Controls

(LH Side Only)

4. 6.

11

FuxxValve

Electronic

10.

Nacelle Tailcone

11.

NacelleBottomSection

12.

Nacelle

13. 14.

NoseCap NacelleTop Section RudderHingeand RudderTabActuator

15.

StabilizerActuator

16.

TipTankFuelPump

(TYPICAL) Access Doors and Panels

Figure EFFECTIVITY:

MODEL23 SERIESAIRCRAFT

Fuselage, Empennage

Stabilizers

1 (Sheet 1 of 3)

51-00-03

rage SRM-4

1

Mav 15/92

Leariet STRUCTURAL REPAIR MANUAL

o

r3

o"O

D

o

Is

200

o

o

o

o

c>

o

o o

0

og

BE

o o

O

O

16

020 Z1

2\

29C1YV~19

27.

Rudder AttachPoints

27.

WingTankFuelPumps

18.

28.

19.

RudderHinge andBalanceWeights Wing Fuel Tank ~ypical Both Wings)

29.

ElevatorControls (LHSideOnly) Horizontal Stabilizer Attachment

20.

Aileron controls

30.

CabinDoor

21.

AileronActuatorand

31.

FuelVent Lines

22.

FuelVentLines

32.

FudShutoffValves

23.

WingFlapBellcrankand SpoilerActuator

33.

24.

Cablesand Pulleys Batteries, Electrical

34.

PulleysandFuelLines HydraulicLinesand WingFuelTanks

25.

frigeration and 26.

Fuel Lines and

Hinges

Components, Fuel Filters, Hydraulic Components

Sump

Re-

Drains

35. 36. 37.

FuelLinesand Drain Elevator Hinge Pitch Axis Servo Access

(Optional)

(TYPICAL)

14-109C

Access Doors and Panels

Figure

EFFECTIVITY:

MODEL 23 SERIES AIRCRAFT

Fuselage, Empennage

Stabilizers

1 (Sheet 2 of 3)

51-00-03

Page SRM´•I

2

May 15/92

Learjet STRUCTU RAL REPAIR MANUAL

r

1

1

1

1

r!2

4

r’

5

1

3

6

9

10

12

11

7

2

9

OI

i

It8

I

I

FLOORBC)ARDS AND INNER SKIN

O Q 1.

BrakeValveandRudder

2.

Control Cables, Controls Sector

3.

Pulleys

PedalLinkage Hydraulic Lines

(II)

and

7.

Hydraulic Lines -InnerSkin BrakeSystem ShuttleValves Control Cables, Pulleys and Roll Servo Parking Brake Control Valve

8.

Cabin Air Distribution Ducts

9.

Hydraulic Lines Control Cables, Pulleys and Aileron-Rudder Interconnect Hydraulic Lines, Emergency Air Lines and Refrigerant Line Control Cables, Pulleys and Anti-Collision Beacon Fuselage Fuel Cell

4. 5. 6.

10. 11.

12. 13.

Inner Skin

(VIEW LOOKING FORWARD) FRAME 24

(TYPICAL)

Access Doors and Panels

Figure

EFFECTIVITY: SRM~

MODEL 23 SERIES AIRCRAFT

1

Floorboards

Fuel Cell Panel

(Sheet 3 of 3)

51-00-03

Page3 May 15/92

Learjet ~Fi

STRUCTURAL REPAIR MANUAL d

os

s

0~

j~o

Uo$ 100

whs oo

st (Zo

~IJ

1.

FuelFiller

10.

RearNacelle

2.

FuelProbe

11.

LowerNacelle

3.

TipTank Access

12.

4.

Directisyn

FluxValve

5.

Electronic

Equipment, Oxygen

and Air Bottles, and

Windshield De-Ice Tank Exit Window

6.

Emergency

7. 8.

FuselageFuelTank Probe WingTipFueland ElectricalConnections

9.

Vertical Stabilizer Attach Points and Controls (LH Side

14.

NoseCap UpperNacelle RudderHingeand

15.

Stabi~izerActuatorLower

16.

TipTankFuel Pump

13.

Only)

Nacelle

RudderTab Actuator

Attach

17.

RudderAttach Points

18. 19.

RudderHingeand BalanceWeights Wing Fuel Tank (Typical Both Wings)

20.

Aileron controls

(TYPICAL)

Access Doors and Panels

Fuselage, Empennage

Figure 2 (Sheet

EFFECTIVITY: SRM~

MODEL 24/24A SERIES AIRCRAFT

1 of

Stabilizers

3)

51-00-03

Page4 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

E~B

o

o o Q

O

O o

,1

Q If

o

020

210 220

21

1157

29pYV_~29

21.

AileronActuatorand

32.

Fuel Shutoff Valves

22.

Fuel Vent Lines

33.

Fueland

23.

WingFlapBellcrankand SpoilerActuator Fuselage Fuel Tank Probe (Lower Fitting) Batteries, Electrical Components, Fuel Filters, Refrigeration and Hydraulic Components Fuel Lines and Sump Drains Wing Fuel Plumbing, Pumps and Hydraulic

34.

Hinges

35.

HydraulicLines ElevatorHinge Stabilizer ActuatorUpper

36.

Pitch Servo Cable Drum and

37.

WireBundleand Conduit

38.

Navl andNav2Antenna

39.

PitchServo

Lines

40.

Pitch Servo Cable Drum and

41.

RudderServo

29.

Elevator Controls (LH Side Only) Horizontal Stabilizer Attachment

42.

Fuel/Defuel Adapter

30.

CabinDoor

43.

Precheck Panel

31.

FuelVent Lines

24. 25. 26. 27. 28.

Single

Attach

Pulleys (RH Only)

Pulleys (Optional)

Single Point (RH Only) Point (RH Only)

(TWICAL)

Access Doors and Panels

Figure EFFECTIVITY: SRM-4

Fuselage, Empennage 2

Stabilizers

(Sheet 2 of 3)

MODEL 24/24ASERIES AIRCRAFT

51-00-03

Page 5 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

I

I

s

112,

7

9

a

ill

12

3

11

9

2

i

l1

0[ I

I

i

g

4

FLOORBOARDS AND INNER SKIN

D Aircraft 24-200 fhru 24-129

O O ’T.

Brake Valve and Rudder Pedal

2.

Control

3.

Controls Sector

4.

Cables, Pulleys

and

Linkage

Hydraulic

Lines

7.

Hydraulic Lines-InncrSkin Brake System Shuttle Valves Control Cables, Pulleys and Roll Servo Parking Brake Control Valve

8.

CabinAirDistribution Ducts-InnerSkin

9.

Hydraulic Lines

5.

6.

10. 11.

12. 13.

Control Cables, Pulleys and Aileron-Rudder Interconnect Hydraulic Lines, Emergency Air Lines and D Refrigerant Control Cables, Pulleys and Anti-Collision Beacon Fuselage Fuel Cell

Line

(VIEW LOOKING FORWARD) FRAME 24

(TYPICAL) Access Doors and Panels

Floorboards

Figure 2 (Sheet 3 EFFECTIVITY: SRM4

MODEL 24/24ASERIESA~RCRAFT

Fuel Cell Panel

of 3)

51-00-03

Page 6 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL 2/1 b X~\\ \I

9

!l

I

a

Onb, r1\15 34

~7 o

o

Ji50

1.

Fuel Filler-Standard

14.

2.

FuelProbe

15.

3.

TipTank Access Directisyn FluxValve Wing Tip Fuel and Electrical Connections Electronic Equipment, Oxygen and Air Bottles,

16.

4. 5.

6.

17.

Flap ActuatorAttachment Wing map Sector, Spoiler Actuator Fuel Vent Lines, Hydraulic Lines Rudder and Elevator Cable Turnbuckles and Fuel Drain Valve

and

18. 19.

Windshield De-Ice Tank

Hydraulic Lines Fuel Crossflow Shutoff Valve,

Hydraulic Lines,

Pneumatic Lines, Jet Pump, Fuel Check Valve, Wing Tank Drain Valve and os. Aircraft 24-190

11.

EmergencyExit Window FuselageFuelTank Probe Wing FuelTankCTypicalBoth Wings) AileronTrim Tab Actuator (LH Only) Aileron Controls, Autopilot Roll Follow-Up

12.

Fuel ProbeConnecto~

21.

FuelLines

13.

WingAccess

22.

Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables and Aileron Sector

7. 8. 9. 10.

and Subseauen_t. Defuel Valve 20.

Fuel

plumbing, Hydraulic Lines, Wing

Drain Valve and,

(LH

on

Tank

Aircraft 24-190 and Subse-

BL1-e~t/ Defuel Valve

Only)

(TWICAL)

Fuselage, Empennage Figure 3 (Sheet 1 of 4)

Access Doors and Panels

EFFECTn7JTY: SRM~

MODEL24B SERIESAIRCRAFT

Stabilizers

51-00-03

Page 7 May 15/92

Leariet STRUCTURAL REPAIR MANUAL

18

000500 C

II

ooo,"

15

000

Detail A

T5’3 29,27

29

A

23.

Fuel and

Hydraulic Lines,

15

Aileron Cable Turnbuck-

40. 41.

les and Fuel Shutoff Valve

Stabilizer Actuator Lower Attachment Stabilizer Actuator Upper Attachment and Eleva-

24.

Fuel

25.

Fuel DrainValve

42.

26.

FuselageFuelTankProbe (LowerFitting)

43.

27.

FuelVentLines, Elevatorand RudderCables

44.

Spring Upper Attachment HingeandBellcrank RudderHingeand Bellcrank Pitch Servo Cable Pulley (RH Side)

28.

PylonAccess

45.

ElevatorControlsand IdlerArm

29.

Batteries, Electrical Components, Fuel Filters, Re-

46.

RudderHingeand

47.

PitchServo

30.

48.

YawServoand

31.

frigeration and Hydraulic Components Horizontal StabilizerHinge Points Elevator Hinge

49.

32.

CabinDoor

Rudder Bellcrank, Yaw Servo Sector, Bottom Rudder Hinge Point, Servo Sector Cables and

33. 34.

NoseCap Air Intake Upper Nacelle

35.

Bottom Nacelle

36.

RearNacelle

37.

Structural

38.

PitchServoElectrical

39.

Structural

Pump and

tor Down

Fuel Drain Valve

Elevatorinboard

RudderTabActuator

Follow-Up

Rudder Cables

Inspection

Plug

50.

RudderControl Cables

51.

Elevator Sector, Push-Pull Tubes, Autopilot Pitch Follow-Up, Elevator and Rudder Control Cables

52.

Ram Air Fuel Vent Lines, Rudder and Elevator Cables

Inspection (TYPICAL)

Access Doors and Panels

Figure

EFFECTIVITY: SRM-4

MODEL 24B SERIES AIRCRAFT

Fuselage, Empennage

Stabilizers

3 (Sheet 2 of 4)

51MM3

Page 8 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL

I

II

T12

S

5

5

1

5

1

1

6

1

7

5

5

II

r’

10

1

I

11

ii

I

FLOORROARDS AND INNER SKIN

2.

Linkage Control Cables, Pulleys and Hydraulic Lines

3.

Elevatorand RudderSectors

1.

4.

(12)

Brake Valves and Rudder Pedal

O O

Hydraulic Lines, Distribution Ducts and Brake System Shuttle Only) Hydraulic Lines Control Cables, Pulleys, Roll Servo and Warm Air Ducting ParkingBrakeValvesand HydraulicLines Control Cables, Pneumatic Lines, Hydraulic Lines, Aileron-

Valves (RH Side 5. 6. 7. 8.

Rudder Interconnect and Air Distribution Duct 9. 10. 11. 12. 13.

CabinAirDistribution Ducts Control Cables, Pneumatic Lines, Hydraulic Lines and AntiCollision Beacon Pneumatic Lines, Hydraulic Lines and Air Distribution Duct

(VIEW LOOKING FORWARD~

FuselageFuel Cell FloatSwitchand FuselageVentLines

FRAME 24

IAirmaft 24-181 thrtr 24-209)

(TYPICAL) Access Doors and Panels moorboards Figure 3 (Sheet 3 of 4)

EFFECTIVITY: sRM-4

MODEL24B SERIESAIRCRAFT

Fuel Cell Panel

51MH)3

Page 9 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

;I-~---F1 1

1

2

5

5

1

1

5

5

10

6

3

1

7

5

L\2

5

FLOORBOARDS AND INNER SKIN

1.

Brake Valves and I~uddcr Podal

2.

Control Cables,

3.

Elevatorand RudderSectors

4. 5.

Hydraulic Lines, Distribution Valves (RH Side Only) Hydraulic Lines

6.

Control Cables,

7. 8.

Pulleys

and

o

Linkage

c~

Hydraulic Lines Ducts and Brake

System

O O

Shuttle

Pulleys, Roll Servo and Warm Air Ducting ParkingBrakeValvesand HydraulicLines Control Cables, Pneumatic Lines, Hydraulic Lines, AileronRudder Interconnect and Air Distribution Duct

9. 10.

CabinAirDistribution Ducts Control

Cables, Pneumatic Lines, Hydraulic Lines and Anti-

Collision Beacon 12.

Pneumatic Lines, Hydraulic Lines and Air Distribution Duct Fuselage Fuel Cell

13.

FloatSwitchand

11.

(VIEW LOOKING FORWARD) FRAME 24

FuselageVentLines

(A ircraft 24-210 ann Subseauent)

(TYPICAL) Access Doors and Panels

Floorboards

Figure 3 (Sheet 4 EFFECTIVITY: SRM-4

MODEL 24B SERIES AIRCRAFT

Fuel Cell Panel

of 4)

51M)-03

Page 10 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ~I

P

~h

i

2\

0

L111

II

,I

0

,o

It

4

1.

FuelFiller

15.

2.

FuelProbe

16.

WingFlapSector, SpoilerActuator FuelVentLines, HydraulicLines

3.

TipTank Access

17.

Rudder and Elevator Cable Tumbuckles and Fuel

18.

Hydraulic

19.

Fuel Crossflow Shutoff

4. 5. 6.

Drain Valve

muxValve

Directisyn WingTip Fuel and Electrical Connections Electronic Equipment, Oxygen and Air Bottles,

and

7.

Emergency Exit Window

8.

FuselageFuelTankProbe Wing Fuel Tank (Typical Both Wings)

10.

Aileron Trim Tab Actuator

20.

(LH Only), Aileron

Aileron Controls,

Autopilot

Roll

Fuel

Plumbing, Hydraulic Lines, Wing

Follow-Up

21.

FuelLines

22.

Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables and Aileron Sector

(LH 23.

Only)

Fuel and

Hydraulic Lines,

12.

Fuel Probe Connector

buckles, Wing

13.

WingAccess mapActuator

ShutoffValve

14.

Tank

Drain Valve and Defuel Valve

Hinge Bolt 11.

Valve, Hydraulic Lines,

Pneumatic Lines, Jet Pump, Fuel Check Valve, Wing Tank Drain Valve and Defuel Valve

Windshield De-Ice Tank

9.

Lines

Aileron Cable Turn-

Fuel Pressure Switch and Fuel

Attachment

(TYPICAL)

Access Doors and Panels

Figure EFFECTIVITY:

Fuselage, Empennage 4

(Sheet

MODEL 24D/E/FSERIES AIRCRAF~

1 of

Stabilizers

4)

51-00-03

Page sahc4

11

May 15/92

Learjet STRUCTURAL REPAIR MANUAL ss

000

0~----12

000,0-~ oOo

Detail A

14 ls Is

29

A

15

\28

44.

Hingeand Bellcrank RudderHinge andBalanceWeight PitchDCTorquerCable Pulley(RHSide)

Aircraft)

45.

ElevatorControlsandIdler

27.

Elevatorand RudderCables

46.

28.

PylonAccess

47.

29.

Batteries, Electrical Components, Fuel Filters, Refrigeration and Hydraulic Components

Hinge and Rudder Tab Actuator Pitch DC Torquer (RH Side,LH Side Optional) YawDCTorquer andFollow-Up Rudder Bellcrank, Yaw DC Torquer Sector, Bottom Rudder Hinge Point, DC Torquer Sector

Pump and

Fuel

25.

FuelDrainValve (24DIE~FAircraft)

26.

Fuel Tank Probe (Lower

Fuselage

42.

Fuel Drain Valve

24.

30.

HorizontalStabilizerHinge

31.

Elevator

32. 33.

CabinDoor NoseCap AirIntake

43.

Fitting)

(24I~F

48´• 49.

Points

ElevatorInboard

Arm

Rudder

Cables and Rudder Cables

Hinge 50.

RudderControlCables

51.

Elevator Sector, Push-PullTubes, Autopilot Pitch Follow-Up, Elevator and Rudder Control Cables

34.

Upper Nacelle

35.

Lower Nacelle

52.

Rudderand ElevatorCables

36.

RearNacelle

53.

Bleed Air Shutoff Valve

39.

Inspection DCTorquer Electrical Plug Structural Inspection

40.

StabilizerActuator Lower Attachment

41.

Stabilizer Actuator

37.

Structural

38.

Pitch

Down

Upper Attachment Spring Upper Attachment

~ypical

LH

RH),

Air-

craft 24-350 and Subseauent

HingeBolt

54.

Aileron

55.

Aileron Drive Clevis

Bolt, Aileron Hinge bolt

and Elevator

(TYPICAZ.) Access Doors and Panels

Figure EFFECTTVITY: SRM-4

Fuselage, Empennage 4

Stabilizers

(Sheet 2 of 4)

MODEL 24D/E/F SERIES AIRCRAFT

51-00-03

Page 12 MaY 15/92

Learjet STRUCTURAL REPAIR MANUAL

ii

2

s

I

s

3

lo

i

ii

s

2

FLOORBQARDS AND INNER SKIN

o

2.

Linkage Control Cables, Pulleys and Hydraulic Lines

3.

Elevatorand RudderSectors

4.

6.

Hydraulic Lines, Distribution Ducts and Brake System Shuttle Valves (RH Side Only) Hydraulic Lines Control Cables, Pulleys, Roll DC Torquer and Air Distribution

7.

ParkingBrakeValvesand HydraulicLines

8.

Control Cables, Pneumatic Lines, Rudder Interconnect

9.

Cabin Air Distribution Ducts

1.

5.

Brake Valves and Rudder Pedal

o

Duct

10.

Hydraulic

Control Cables, Pneumatic Lines,

Lines and Aileron-

Hydraulic

Lines and Anti-

Collision Beacon

Hydraulic Lines and Air Distribution Duct

II.

Pneumatic Lines,

12.

FuselageFuelCell (24DIFAircraft) Float Switch and Fuselage Vent Lines

13.

(VIEW LOOKING FORWARD) FRAME 24

~24D/F Aircraft)

with 2Clnch Door)

(Aircraft

(TYPICAL) Access Doors and Panels

Figure

EFFECTIVITY: SRM~

4

moorboards

Fuel Cell Panel

(Sheet 3 of 4)

MODEL 24D/E/FSERIES AIRCRAFT

51-00-03

Page 13 May 15/92

Learjet ~i STRUCTURAL REPAIR MANUAL s

i

t

112~5

5

1

10

1

5

5

2

1

11

(Aircraft 24-230 thru 241253)

I r

5

6

5

5

2

I

o

5

j

t

o

i

24-243 and Subseauent)

(VIEW LOOKING FORWARD) FRAME 24

(Airmaft 24-243 and Subseauent) FLOORBOARDS AND INNER SKIN

PedalLinkage

i.

BrakeValvesandRudder

2.

Control

3.

Elevatorand RudderSectors

4.

Hydraulic Lines, Distribution Ducts and Brake System Shuttle

Valves (RH Side

Cables, Pneumatic Lines, Hydraulic Lines

8.

Control

9.

and Aileron-Rudder Interconnect Cabin Air Distribution Ducts

Cables, Pulleys and Hydraulic Lines 10.

Control Cables, Pneumatic Lines,

Hydraulic

Lines

and Anti-Collision Beacon

Only) 11.

5.

Hydraulic Lines

6.

Control Cables, Pulleys, Roll DC Distribution Duct

7.

ParkingBrakeValvesand HydraulicLines

Torquer

Pneumatic

Lines, Hydraulic Lines and Air Distribu-

tion Duct

and Air 12.

FuselageFuelCell

13.

Float Switch and

Fuselage

Vent Lines (24D/F Air-

(Aircraft eauiaaed with 36-Xlzch Door) (TYPICAL) Access Doors and Panels

Figure EFFECTIVITY: SRM~

4

Floorboards

Fuel Cell Panel

(Sheet 4 of 4)

MODEL 24D/E/F SERIES AIRCRAFT

51-00-03

Page 14 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL 2

3

obo

5

0

0-9

3

21

0

8

Jl IZ

--5

D

43

16

11

10 11

;?6 o~-FCSt 37

000

52

33

34

53

39

35

55

51

i.

Fuel Filler-Standard

15.

2.

FuelProbe

16.

Flap ActuatorAttachment Wing map Sector, Spoiler Actuator

3.

TipTank Access Directisyn FluxValve FuelDumpValve

17.

FuelVent Lines

4.

5. 6. 7.

WingTipFueland ElectricalConnections Electronic Equipment, Air Bottle, Alcohol Tank and,

on

Aircrafe 25-003

25-024,

Anti-ice

Rudder and

19.

Sump Drain Valve HydraulicLines

20.

Fuel Crossflow Shutoff

11.

EmergencyExit Window Fuselage Fuel Tank Probe Wing Fuel Tank ~ypical Both Wings) AileronTrimTab Actuator (LHOnly)

12.

Aileron Controls and

8. 10.

Autopilot 13. 14.

Roll

on

Cable Turnbuckles and

Valve, Hydraulic Lines, Lines, Jet Pump, Fuel Check Valve and on.Aircraft 25-030 and 5ubseauent, Fuel Pneumatic

Oxygen

Bottle 9.

Elevator

18.

Drain Valve 21.

Fuel

Plumbing, Hydraulic

Lines and,

on

Aircraft

25-030 and Subseauent. Fuel Drain Valve 22.

Fuel Lines, Sump Drain, Elevator, Aileron and Rudder Cables and Aileron Sector

23.

FuelLines

Aircraft 25-025 and Subse-

Follow-Up (LH Only)

24.

FuelProbeConnector

Fuel and

Hydraulic Lines,

Aileron Cable Turn-

buckles and Fuel Shutoff Valve

WingAccess (TYPICAL)

Access Doors and Panels

Rgure EFFECTIVITY: SRM~

Fuselage, Empennage

Stabilizers

5 (Sheet 1 of 4)

MODEL 25/25ASERIES AIRCRAFT

51-00-03

Page 15 May 15/92

Leariet STRUCTURAL REPAIR NIANUAL I 25 22 19

---I

21

aoo

Detail A

0 0 0

/29,28

tol

A’ oo

ElectricalPlug

25.

Fuel

43,

PitchServo

26.

Fuel DrainValve

44.

Stabilizer ActuatorLower Attachment

27.

FuselageFuelTank Probe (LowerFitting)

45.

Stabilizer Actuator

28.

Fuel Vent Lines

29.

PylonAccess

30.

Batteries, Electrical Components, Fuel Filters, Re-

Pump and Fuel Drain Valve

48. 49.

ElevatorControlsand IdlerArm

50.

PitchServo

51.

52.

RudderHingeand RudderTabActuator PrimaryYawServoand Follow-Up

53.

Rudder Bellcrank,

46.

and

47.

Down

32.

frigeration Equipment, Hydraulic Components Secondary Yaw Servo Horizontal Stabilizer Hinge Points Elevator Hinge

33.

Cabin Door

34.

Fuel/Defuel Adapter (Single Point) RH Only

35.

Precheck Panel

36. 37.

NoseCap AirIntake Upper Nacelle

54.

RudderControl Cables

38.

Bottom Nacelle

55.

Elevator

39.

RearNacelle Oxygen Bottle ~Aircraft25-025 andSuhseauent)

56.

31.

40. 41.

Structural

42.

Structural

(Single Point)

RH

and Eleva-

Upper Attachment Spring Upper Attachment ElevatorInboard Hingeand Bellcrank RudderHingeand BalanceWeight Pitch Servo Cable Pulley (RH Side)

tor

Primary Yaw Servo Sector, Hinge Point, Servo Sector Cables, Rudder Cables and Secondary Follow-Up

Bottom Rudder

Only

Sector, Push-Pull Tubes, Autopilot Pitch

Follow-Up,

Elevator and Rudder Cables

Ram Air Fuel Vent Lines, Rudder and Elevator

Cables

Inspection Inspection (TYPICAL)

Access Doors and Panels

Figure

EFFECTIVITY: SRM~

Fuselage, Empennage

Stabilizers

5 (Sheet 2 of 4)

MODEL 25/25ASERIES AIRCRAFT

51-00-03

Page 16 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

to

1

T!Z

1

L

s

7

s

1

2

~1

L

6

i

3

1

10

ii

I

I

s

1

a

12

8

4

II

tt

11

10

10

FLOORBOARDS AND INNER SKIN

(1J) 2.

3.

Control Sector

4.

8.

Hydraulic Lines Brake System Shuttle Valves and Hydraulic L.incs Control Cables, Pulleys and Roll Servo ParkingBrakeValvesand HydraulicLines Control Cables, Pulleys and Aileron-Rudder Interconnect

9.

WireBundle Conduit

5.

6.

7.

10.

CabinAirDistribution Ducts

11.

Hydraulic Lines, Emergency Air Lines Control Cables, Pulleys and Anti-Collision Beacon Fuselage Fuel Cell

12.

13.

~Tj)

Brake Valves and Rudder Pedal

Linkage Control Cables, Pulleys and Hydraulic Lines

1.

00 (VIEW LOOKING FORWARD~ FRAME 25

(Aivcraft 25-00~fhru 25-039 and 25-041 thru 25-045)

(TYPICAL) Access Doors and Panels

Floorboards

Fr’gure 5 (Sheet 3 EFFECTIVITY:

MODEL 25/25ASERIES AIRCRAFT

Fuel Cell Panel

of 4)

51~X203

Page SRM-4

17

May 15/92

Learjet STRUCTURAL REPAIR MANUAL

9\\

3

II

I

I

2

5

3

lgl

7

s

L

B

4

1

6

2

LlZ-F

I

it

I

19

r~

Ill

9

(1

9

I

11

FLOORBOARDS AND INNER SKIN

O 2. 3.

Control Sector

4.

8.

Hydraulic Lines Brake System Shuttle Valves and Hydraulic Lines Control Cables, Pulleys and Roll Servo Parking Brake Valves and Hydraulic Lines Control Cables, Pulleys and Aileron-Rudder Interconnect

9.

CabinAirDistribution Ducts

5. 6. 7.

10. 11.

12.

(lr)

BrakeValvesand Rudder

PedalLinkage Control Cables, Pulleys and Hydraulic Lines

1.

Hydraulic Lines, Emergency Air Lines Control Cables, Pulleys and Anti-Collision FuselageFuel Cell

00

Deacon

(VIEW LOOKING FORWARD) FRAME 25

(Airmaft 25-040 and 25-046 and Subseauent)

(TYPICAL)

Access Doors and Panels Floorboards Figure 5 (Sheet 4 of 4)

EFFECTIVITY: SRM~

MODEL 25/25ASERIES AIRCRAFT

Fuel Cell Panel

51-00-03

Page 18 May 15/92

Learjet Lear]et

STRUCTURAL REPAIR MANUAL 13 11

14 I

ct

15 16

r

~---17

1

18

~15

11

Detail A

3

A O

~3

O

O

io 9

5

1.

Electronic

Air Bottle,

Equipment,

Oxygen

Bottle

12.

Rudder and Elevator Cable Turnbuckles and

Sump

Drain Valve

and Anti-Ice Tank

3.

(Optional) FuselageFuelTank Probe PylonAccess

4.

Fuel VentValves

5.

Batteries, Electrical Components, Fuel Filters, Re-

14.

Fuel Lines and

frigeration Equipment, Hydraulic Components and Secondary Yaw Servo Fuselage Fuel Tank Probe (Lower Fitting) Rudder Bellcrank, Primary Yaw Servo Sector, Rudder Bottom Hinge Point, Servo Sector C:ables, Rudder Cables and Secondary Yaw Follow-Up

15.

Fuel and

17.

Pump and Fuel Drain Valve Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables, and Aileron Sector

8.

Rudder Control Cables

18.

Fuel Drain Valves

9.

Elevator Sector, Push-Pull Tubes, Autopilot Pitch Follow-Up, Elevator and Rudder Control Cables

19.

2.

6. 7.

13.

Fuel Crossnow Shutoff Valve, Hydraulic Lines, PneuLines, Jet Pump, Fuel Check Valve and Fuel

matic

Drain Valve

10.

Rudderand ElevatorCables

11.

Hydraulic Lines

Wing

on

25 C/F Aircraft. Transfer Valve

Hydraulic Lines,

Aileron Cable Turnbuckles,

Fuel Pressure Switch and

on

25 B/D Aircraft.

Fuel Shutoff Valve 16.

Fuel

Fuel

Plumbing, Hydraulic Lines, Wing

Tank Drain

Valve and Defuel Valve

(TYPICAL)

Fuselage Figure 6 (Sheet 1 of 5)

Access Doors and Panels

EFFECTIVITY: SRM-4

MODEL

25B/C/D/FSERIES AIRCRAFT

Empennage

51-00-03

Page 19 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

000

O

~BB

60

,00

O O

80

0’"

5.

TipTankAttach Fittings Wing Tip Fuel Electrical Connections Wing FuelTank Fuel VentPlumbing AileronControlsand Follow-Ups

6.

Fuel ProbeConnector

7.

WingAccess map ActuatorAttachment FlapSectorand SpoilerActuator

1.

2. 3. 4.

8.

9.

10.

Fuel Vent Lines

11.

Main GearAftTrunnion Pin

12.

Sparlt7 Spar#5

13.

C11 413

I 12

oO

(TYPICAL) Access Doors and Panels

Wing Figure 6 (Sheet 2 of 5)

EFFECTIVITY: SRM~

MODEL 25B/C/D/FSERIES AIRCRAFT

51MM3

Page 20 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

a

D

’D 11

I

(Optional)

1.

Oxygen Cylinder

2.

Rudder Trim Tab Motor and Center

3. 4.

Access

Hinge RudderDalanceWeight Access PrimaryYawServoand CapstanAccess

Access

Ei.

ElevatorServo Access

6.

Vertical Stabilizer Rib

7.

Elevator Down

8.

Lower Horizontal Stabilizer Actuator Attach Point Access Upper Horizontal Stabilizer Actuator Attach Point Access

9.

Inspection Access Spring and Servo Cable Turnbuckle

17.

Upper Rudder Attach Point Access Leading Edge Hot Air Tube Access Horizontal Stabilizer Hinge Pin Access Pitch Capstan Pulley and Cable Access Pitch CapstanAccess Vertical Stabilizer Rib Inspection Access

18.

AccessCover

19.

Stinger Oxygen Regulator Access (Optional)

10. 11.

12.

13.

14.

15. 16.

20.

(TYPICAL)

MIA-1

EFFECIIVITY: sRM4

Access Doors and Panels Stabilizers Figure 6 (Sheet 3 of 5)

MODEL 25B/C/D/FSERIES AIRCRAFT

51MM3

Page 21 May 15/92

Learjet ~i STRUCTURAL REPAIR MANUAL

9

9\\9

o

I

u_!

5

2

3

2

1

s

r]

1

7

11

6

5

5

Il

10

10

11

3

9

9

FLOORBOARDS AND INNER SKIN

O

00

1.

BrakeValveand Rudder

2.

Control Cables,

3.

Controls Sector

4.

8.

HydraulicLinesand AirDucts Brake System Shuttle Valves and Hydraulic Lines Control Cables, Pulleys and Roll Servo ParkingBrakeValvesand Hydraulic Lines Control Cables, Pulleys and Aileron-Rudder Interconnect

9.

CabinAirDistribution Ducts

5. 6. 7.

10. 11. 12.

Pulleys

PedalLinkage Hydraulic Lines

and

(VIEW LOOKING FORWARD)

Emergency Air Lines Control Cables, Pulleys and Anti-Collision Beacon FuselageFuel Cell Hydraulic

n

Lines and

FRAME 25

(Aircvaff eauitttled with 24-~nch Door)

(TWICAL)

Access Doors and Panels

moorboards

Figure 6 (Sheet 4 EFFECTIVITY: SRM-4

MODEL 25B/C/D/FSERIES AIRCRAFT

Fuel Cell Panel

of 5)

51-00-03

Page 22 May 15/92

Learjet Leariet j

STRUCTURAL REPAIR MANUAL 9

9

0

1

1

2

4

4

2

1

4

6

3

i

7

5

5

4

4

11

11

10

10

0

9

9

(Aiwsft 25-061 thru 25-074)

o 11

2

5

5

00

6

33

o

11244 04

($Aircraft 25-105 and Subseauen))

(VIEW LOOKING FORWARD) FRAME 24

(Airmaft 25-075 and Subseauent) PLOORBOARDS AND INNER SKIN

BrakeValveandRudder

2.

Control Cables,

3.

ControlSector

4.

Hydraulic LinesandAirDucts Brake System Shuttle Valves and

5. 6. 7.

8.

PedalLinkage Pulleys and Hydraulic Lines

1.

Control Cables,

Pulleys

and Aileron-Rudder Inter-

connect

9. 10. 11.

Hydraulic Lines RollServo ControlCables,Pulleysand Parking Brake Valves and Hydraulic Lines

12.

CabinAirDistribution Ducts

HydraulicLinesand EmergencyAirLines Control Cables, Pulleys and Anti-Collision Beacon FuselageFuelCell

(Aiucraft eauirmed with 3ti-lnch Door)

(TYPICAL) Access Doors and Panels

Figure EFlFECTIVITY: SRM~

MODEL

Floorboards

Fuel Cell Panel

6 (Sheet 5 of 5)

25B/C/D/FSERIES AIRCRAFf

51-00-03

Page 23 May 15/92

Learjet STRUCTURAL REPAIR MANUAL 13 14

11

lu

15

/-3

16

12-´•--1

r

1

F--17 18

11---/

´•g~cL4

~Y

~---15

\CLg

A’

Detail A

/--20

2

0000 ro

18 9

5

i.

Electronic

Equipment,

Air

12.

Bottle, Oxygen Bottle

2.

(Optional) Fuselage FuelTank Probe

3.

PylonAccess

4.

Fuel VentValves

5.

Batteries, Electrical

Rudder and Elevator Cable Turnbuckles and

Sump

Drain Valve

and Anti-Ice Tank 13.

Fuel Crossflow Shutoff Valve, Hydraulic Lines, Pneumatic Lines, Jet Pump, Fuel Check Valve and Fuel

Drain Valve

Model 29 Aircraft, Transfer Valve

Components, frigeration Equipment, Hydraulic Components and Secondary Yaw Servo Fuselage Fuel Tank Probe (Lower Fitting) Rudder Bellcrank, Primary Yaw Servo Sector, Rudder Bottom Hinge Point, Servo Sector Cables, Rudder Cables and Secondary Yaw Follow-Up

14.

Fuel Lines and

15.

Fuel and

17.

Fuel Pump and Fuel Drain Valve Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables, and Aileron Sector

8.

Rudder Control Cables

18.

Fuel

9.

Elevator Sector, Push-Pull Tubes, Autopilot Pitch Follow-Up, Elevator and Rudder Control Cables

19.

Fuel

10.

Rudder and Elevator Cables

20.

11.

Hydraulic Lines

6. 7.

Fuel Filters, Re-

Wing

on

Hydraulic Lines, Aileron Cable TurnbucWes,

Fuel Pressure Switch and

on

Model 28 Aircraft.

Fuel Shutoff Valve 16.

Pump and Fuel Drain Valve Plumbing, Hydraulic Lines, Wing

Tank Drain

Valve and Defuel Valve

Fuselage FuclTankFiller

(TYPICAL) Access Doors and Panels

Fislre EFFECTIVITY: SRM~

7

MODEL28/29SERIES AIRCRAFT

Fuselage

Empennage

(Sheet 1 of 5)

51-00-03

Page 24 May 15/92

STRUCTURAL REPAIR MANUAL

O O O 1.

FluxValve Installation

2.

Electrical Connections

3.

Wing FuelTank Plumbing

4.

FuelVent

5.

AileronControlsand

6.

Fuel Probe Connector

7.

WingAccess

8.

map

9.

FlapSectorand SpoilerActuator

10.

Follow-Ups

ActuatorAttachment

\O

FuelVentLines

11.

Main Gear AftTrunnionPin

12.

Spar#7 SparfS

13.

1,

’Tn,

I\ \o\O

(TYPICAL) Access Doors and Panels

Figure 7 (Sheet 2 EFFECTIVITY: Sf~M-4

MODEL 28/29 SERIES AIRCRAFT

Wing

of 5)

51~X)a3

Page 25 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Vs 15)/ U3

O

to Il

1)

(3

BottleAccess

(Optional)

1.

Oxygen

2.

Rudder Trim Tab Motor and Center

3. 4.

Hinge Weight Access PrimaryYawServoand CapstanAccess

Access

Rudder Balance

5.

ElevatorServo Access

6.

Vertical Stabilizer Rib

7.

Elevator

8.

Lower Horizontal Stabilizer Actuator Attach Point Access

9.

Upper Horizontal Stabilizer Actuator Attach Point UpperRudder AttachPointAccess Leading Edge Hot Air Tube Access Horizontal Stabilizer Hinge Pin Access Pitch Capstan Pulley and Cable Access PitchCapstan Access Vertical Stabilizer Rib Inspection Access

10. II.

12.

13.

14.

15. 16. 17.

Inspection Access DownSpringand ServoCableTurnbuckle

18.

AcccssCover

19.

Stinger OxygcnRegulator Access(Optional)

20.

Access

(TYPICA~) Access Doors and Panels

Figure EFFECTIVITY: sRM-4

7

MODEL 28/29SERIESAIRCRAFT

Stabilizers

(Sheet 3 of 5)

51-00-03

Page 26 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

1

u_ 1

1

5

2

3

2

I.

S

Z

sn

9

lI

I

1

7

1

6

5

9

J

r

o

I

11

5

11

10

10

4

11

9

9

9

FLOORBQARDS AND INNER SKIN

O

BrakeValveandRudder Control Cables, ControlSedor

3. 4.

5. 6. 7.

8. 9.

00

PedalLinkage Pulleys and Hydraulic Lines

1.

2.

HydraulicLinesand AirDucts Brake System Shuttle Valve and Hydraulic Lines RollServo ControlCable,Pulleysand HydraulicLines ParkingBrakeValvesand Control Cables, Pulleys and Aileron-Rudder interconnect Cabin Air Distribution Ducts

10.

Hydraulic Lines, Emergency Air Lines

11.

Control Cables, Pulleys and Anti-Collision Beacon Fuselage Fuel Cell

12.

Q

(VIEW LOOKING FORWARD) FRAME 25

with 24-Inch Door)

(Aircraft

(TYPICAL) 531A-1

EFFECTIVITY: SRM-4

Access Doors and Panels Floorboards Figure 7 (Sheet 4 of 5)

MODEL 28/29SERIES AIRCRAFT

Fuel Cell Panel

51MN)3

Page 27 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

o

11

2

s

1

1

o

7 s

5

a

3

s 4

2

tt

tt

to

to

o

s

FLOORBOARDS AND INNER SKIN

O

1.

2.

Control Sector

4.

8.

HydraulicLinesand AirDucts Brake System Shuttle Valve and Hydraulic Lines Control Cable, Pulleys and Roll Servo Parking Brake Valves and Hydraulic Lines Control Cables, Pulleys and Aileron-Rudder Interconned

9.

CabinAirDistribution Ducts

5. 6.

7.

10.

Hydraulic Lines, Emergency Air Lines

11.

Control Cables, Pulleys and Anti-Collision Beacon FuselageFuel Cell

12.

00

BrakeValve andRudder PedalLinkage Control Cables, Pulleys and Hydraulic Lines

3.

n

(VIEW LOOKING FORWARD) FRAME 25

(Aircraft eauitmed with 36-Inch Doov)

(TYPICAL) Access Doors and Panels

moorboards

Figure 7 (Sheet 5 EFFECTIVITY: SRM-4

MODEL 28/29SERIES AIRCRAF~

Fuel Cell Panel

of 5)

51-00-03

Page 28 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

(r5

3~

j.

3

g

~8

~--10

~13

L 9--1

1

4

0-7

10

L8 11

7

12

00000

I

14

1. 2. 3. 4. 5.

Oxygen Bottle (Optional), Avionics and Radio Equipment, Air Bottle and Alcohol Anti-Ice Tank Fuselage FuelTank Probe Hydraulic Lines and Electric Scavenge Pumps Rudder and Elevator Cable Turnbuckles, Sump

Fuel Drain Valve

12.

Fuselage Fuel Tank Probe (Lower Fitting)

13.

FuelVent Lines

14.

Batteries, Electrical Components, Fuel Ellters, ReMg-

Equipment, Hydraulic Components, Engine Extinguishers and Throttle Cables

eration

Fuel Crossflow Shutoff

Rre

Fuel

6.

FuelPumpand

11.

Drain Valve and Throttle Cables

Valve, Hydraulic Lines, Pneumatic Lines, Jet Pump, Fuel Check Valve, and Fuel Drain Valve

15. 16.

Standby Pump Plumbing, Hydraulic Lines, Wing Tank Drain, Drain Valve, Standby Fuel Pump and De-

17.

fuel Valve

18.

Fuel LinesandTransferValve

8.

Fuel and

Hydraulic

Rudderand ElevatorCables Elevator Sector, Push-Pull Tubes, Elevator and Rudder Control Cables

Fuel

7.

FuelDrainValve

10.

RudderControl Cables

Lines and Aileron Turnbuck-

Primary Yaw Servo Sector, Bottom Hinge Point, Servo sector Cables and Rudder

Rudder Bellcrank, Rudder cables

les 9.

Fuel Lines, Fuel tank Drain Valve, Elevator, Aileron and Rudder Cables, aileron Sector and throttle Cables

(TYPICAL) 14-90(3-4

14-909-6

EFFECTMTY: SRM~

Access Doors and Panels

Fuselage Figure 8 (Sheet 1 of 5)

MODEL31 SERIESAIRCRAFT

Empennage

51-00-03

Page 29 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

2.

FluxValve Installation Electrical Connections

3.

Wing

Fuel Tank

4.

Fuel Vent

5.

AileronControlsand

6.

Fuel ProbeConnector

7.

WingAccess Flap ActuatorAttachment FlapSectorand SpoilerActuator

1.

8.

9.

1QI

Plumbing Follow-Ups

10.

FuelVent Lines

11.

Main Gear AftTrunnionPin

12.

Spar#7

’rM,

13

(TYPICAL) Access Doors and Panels Wing Figure 8 (Sheet 2 of 5)

EFFErrNITY: SRM-4

MODEL31 SERIESAIRCRAFT

51-00-03

Page 30 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

15)/ ~3

i3

O

10 I

1.

Oxygen BottleAccess (Optional)

2.

Rudder Trim Tab Motor and Center

3.

RudderBalanceWeight

Hinge

Access

Access Access

4.

Primary Yaw Servo and Capstan

5.

Elevator Servo Access

6.

Vertical StabilizerRib

7.

ElevatorDown

8.

Lower Horizontal Stabilizer Actuator Attach Point Access

9.

17.

Upper Horizontal Stabilizer Actuator Attach UpperRudder AttachPointAccess Leading Edge Hot Air Tube Access Horizontal Stabilizer Hinge Pin Access Pitch Capstan Pulley and Cable Access PitchCapstan Access Vertical Stabilizer Rib Inspection Access

18.

AccessCover

19.

Stinger Oxygen Regulator Access (Optional)

10. 11.

12.

13.

14. 15. 16.

20.

Inspection Access Springand ServoCableTurnbuckle Point Access

(TYPICAL) Access Doors and Panels

Figure 8 (Sheet 3

EFFECTIVITY: sRM-4

MODELS1 SERIESAIRCRAFT

Stabilizers of 5)

51-00-03

Page 31 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

9

9 4

--r---

1

255

3& 1

1

2

7

11

8 5

~12

4

I

5

10

4

0

9

9

FLOORBOARDS AND INNER SKIN

Q 1.

Brake Valve and Rudder Pedal

2.

Control

3.

Control Sector

4.

Aux

5.

Brake

Linkage

Cables, Pulleys and Hydraulic Lines and Rudder

00

Boost Force Sensors

6. 7. 8.

Defog Control Box, Hydraulic Lines and Air Ducts System Shuttle Valves and Hydraulic Lines Control Cables, Pulleys and Roll Servo (31-002 thru 32-034) ParkingBrakeValvesand HydraulicLines Control Cables and Pulleys

10.

CabinAirDistribution Ducts Aural Warning Conrol Unit,

11.

gency Air Lines Control Cables, Pulleys and Anti-Collision Beacon

12.

Squat

9.

Switch

Relay

Hydraulic

Lines and Emer-

Panel and Rudder Boost Control Box

(VIEW LOOKING FORWARD) FRAME 25

(31-002 thru 31-034) 13.

FuselageFuel

Q

Cell

(Aircraft eaui~aed with 24-Inch Door)

(TYPICAL) 5J1A-1

Access Doors and Panels

Figure EFFECTIVITY: sRM-4

MODEL31 SERIESAIRCRAFT

Floorboards

Fuel ~ell Panel

8 (Sheet 4 of 5)

51-00-03

Page 32 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

9

I

1

ta

5

2 O

2

1

5

7

4

1

12

11

6

3~

1

5

9

8 5

10

O

9

9

FLOORBOARDS AND INNER SKIN

O 1.

BrakeValveand

2.

Control

RudderPedalLinkage

Cables, Pulleys and Hydraulic Lines and Rudder

00

Boost Force Sensors 3.

ControlSector

4.

8.

Defog Control Box, Hydraulic Lines and Air Ducts System Shuttle Valves and Hydraulic Lines Control Cables, Pulleys and Roll Servo (32-002 tht7e 31-03~t) ParkingBrakeValvesand Hydraulic Lines ControlCables and Pulleys

9.

Cabin AirDistribution Ducts

5. 6.

7.

10.

Aux

Brake

Aural

Warning

Q

Conrol

Unit, Hydraulic Lines

and Emer-

gency Air Lines 11. 12.

Control

Squat

Cables, Pulleys and Anti-Collision Beacon

Switch

Relay

Panel and Rudder Boost Control Box

(VIEW LOOKING FORWARD) FRAME 25

(31-002 thru 31-034) 13.

FuselageFuel Cell

(Aircuaft eauil7tled with 36-Inch Door)

(TYPICAL) Access Doors and Panels

Figure

EFEECTIVITY: sRM-C

MODEL31 SERIESAIRCRAF~

Floorboards

Fuel Cell Panel

8 (Sheet 5 of 5)

51M)-03

Page 33 May 15/92

Leariet STRUCTURAL REPAIR MANUAL

3-~/r5

4

----1

3

r7

L-8 )-10 r13

r 9~1

’\L6

~1

~----14

L,7 ~R

1

~2

g

0000

14

1.

2.

3. 4.

5.

Equipment, Air Bottle, Oxygen (Optional) and Anti-Ice Tank FuselageFuelTank Probe Hydraulic Lines Electronic

Bottle

Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables, Aileron Sector, Throttle Cables,

9.

10.

equipped) Drag Chute Cable FuelPumpand FuelDrainValve

Rudder and Elevator Cable Turnbuckles, Sump DrainValve, Throttle Cables, and (if so equipped)

11.

FuelDrainValve

12.

Fuselage Fuel Tank Probe (Lower Fitting)

Drag Chute Cable

13.

FuelVent Lines

Fuel Crossflow Shutoff Valve, Hydraulic Lines, Pneumatic Lines, Jet Pump, Fuel Check Valve,

14.

Batteries, Electrical Components, Fuel Filters, Refrig-

and (if

7.

Fire

Plumbing, Hydraulic Lines, Wing Tank Drain, Drain Valve and Defuel Valve

15.

Cables

Model 36 Aircraft. Transfer

16.

Fuel

Fuel Lines and

on

Rudder and Elevator Cables Elevator Sector, Push-Pull Tubes, Elevator, and Rudder Control Cables

Valve 8.

Equipment, Hydraulic Components, Engine Extinguishers, Secondary Yaw Servo and Throttle

eration

and Fuel Drain Valve 6.

so

Fuel Pressure Switch, Fuel and Hydraulic Lines, Aileron Cable Turnbucklcs, and on Modl?l

Wing

17.

RudderControlCables

18.

Rudder Bellcrank, Primary Yaw Servo Sector, Bottom Rudder Hinge Point, Servo Sector Cables and Rudder

35 Aircraft. Fuel Transfer Valve

Cables

(Aircraft 35-002 thru 35-646. nnd 36-002 thru 36-058) (TYPICAL)

14-I09C

Access Doors and Panels

Fuselage

Figure 9 (Sheet

EFFECTnlTITY: SRM~

MODEL 35/36SERTES AIRCRAFT

Empennage

1 of 6)

51-00-03

Page 34 May 15/92

Learjet ~Learjet

STRUCTU RAL REPAIR MANUAL

3

--~/r5 r7

1

s-~

~-8

15~r16

~17

a-l~

9

15"-16

L17

3--~\L6 L7

1

~18

2

g

0000

14

Air Bottle,

1.

Electronic

2.

(Optional) and Anti-Ice Tank FuselageFuelTank Probe Hydraulic Lines

3. 4.

5.

Equipment,

Oxygen

nettle

9.

10.

7.

Fuel Lines, Fuel Tank Drain Valve, Elevator, Aileron and Rudder Cables, Aileron Sector, Throttle Cables, and (if so equipped) Drag Chute Cable FuelPumpandFuelDrain Valve

11.

Drag Chute Cable

13.

FuelDrainValve Fuselage Fuel Tank Probe (Lower FuelVent Lines

Fuel Crossflow Shutoff Valve, Hydraulic Lines, Pneumatic Lines, Jet Pump, Fuel Check Valve,

14.

Batteries, Electrical Components, Fuel Filters, Rcfrig-

12.

15.

Monel 36 Aircraft. Transfer

16.

on

Equipment, Hydraulic Components, Engine Extinguishers, Secondary Yaw Servo and Throttle

Cables

Plumbing, Hydraulic Lines, Wing Tank Drain, Drain Valve and Defuel Valve Fuel

Fuel Lines and

Fitting)

eration Fire

Rudderand ElevatorCables Elevator Sector, Push-Pull

Tubes, Elevator, and Rud-

der Control Cables

Valve 8.

17

Rudder and Elevator Cable Turnbuckles, Sump DrainValve, Throttle Cables, and (if so equipped)

and Fuel Drain Valve 6.

15-iL16

Fuel Pressure Switch, Fuel and Hydraulic Lines, Aileron Cable Turnbuckles, and on 1Monrl 35 Aircraft. Fuel Transfer Valve

Wing

17. 18.

RudderControl Cables

Primary Yaw Servo Sector, Bottom Hinge Point, Servo Sector Cables and Rudder

Rudder Bellcrank, Rudder Cables

(Aircraft 35-647 anbSubseauenf, nzzn 36-059 Rnn Subseauazt)

(TYPICAL) 14-109C-1

EFFECT~VITY:

Fuselage Figure 9 (Sheet 2 of 6)

Access Doors and Panels

MODEL 35/36SERIESAIRCRAFT

Empennage

51-00-03

Page 35 SRM-4

May 15/92

Learjet

STRUCTLIRAL REPAIR MANUAL

01 00 000

8 FORWARD

OBB

O 60

,~B

B B

80

5.

TipTankAttach Fittings Wing Tip Fuel Electrical Connections Wing FuelTank Fuel Vent Plumbing Aileron Controls and Follow-Ups

6.

Fuel Probe Connector

7.

WingAccess

1.

2. 3. 4.

:11

~w I

ActuatorAttachment

8.

Flap

9.

mapSectorand SpoilerActuator

10.

Fuel Vent Lines

11.

Main GearAftTrunnionPin

12.

Spar#7 Spar#5

13.

0’"

12

O

i

oO (TYPICAL)

Access Doors and Panels

Figure 9 (Sheet 3 EFFECT~VITY: SRM~

MODEL 35/36 SERIES AIRCRAFT

Wing

of 6)

51-00-03

Page 36 May 15/92

Learjet Learjet

STRUCTURAL REPAIR MANUAL

i4~ 15)/ U3

8

0, Il

1)\

~3

1.

13.

Hinge Access

Rudder Trim Tab Motor and Center

3. 4.

RudderBalanccWeight Access PrimaryYawScrvoand Capstan

5.

ElevatorServo Access

6.

Vertical Stabilizer Rib

7.

Elevator Down

8.

Lower Horizontal Stabilizer Actuator Attach Point Access

9.

17.

Upper Horizontal Stabilizer Actuator Attach Point Upper Rudder Attach Point Access Leading Edge Hot Air Tube Access Horizontal Stabilizer Hinge Pin Access Pitch Capstan Pulley and Cable Access PitchCapstan Access Vertical Stabilizer Rib Inspection Access

18.

AccessCover

19.

Stinger Oxygen Regulator

10. 11.

OxygenBottleAccess (Optional)

2.

12. 14. 15.

16.

20.

Access

Inspection Access Spring and Servo Cable Turnbuckle

Access

Access

(Optional)

(TYPICAL)

5-31A-1

Access Doors and Panels

Figure

EFFECTIVITY: sRM-4

Stabilizers

9 (Sheet 4 of 6)

MODEL 35/36SERIES AIRCRAFT

51M203

Page 37 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

9

9

04 1

2

5

345 1

1

7

4

15

12

13

14

11

6 5

2

5

5

10

04

9

9

FLOORBOARDS AND INNER SKIN

c;a, i.

2.

BrakeValveand Rudder PedalLinkage Control Cables, Pulleys and Hydraulic Lines

3.

Control Sector

4.

HydraulicLinesand

5.

8.

Hydraulic Lines Pulleys and Roll Servo ParkingBrakeValvesand HydraulicLines Control Cables, Pulleys and Aileron Rudder Interconnect

9.

CabinAirDistribution Ducts

6. 7.

Brake

System

Control Cables,

10.

HydraulicLinesand EmergencyAirLines

11.

Control Cables, Pulleys and Anti-Collision Beacon AuralWarningControl Unit MachTrim Computer Spoiler Computer Squat Switch Relay Panel FuselageFuel Cell

12. 13.

14. 15. 16.

00

AirDuds

Shuttle Valves and

(VIEW LOOKING FORWARD) FRAME 25

(Aircraft eauit~ed with 24-Inch Door)

(TYPICAL) Access Doors and Panels

Figure 9 (Sheet 5 EFFECTIVITY: SRM~

MODEL35/36SE~IES AIRCRAFT

Fuselage

of 6)

51~X)-03

Page 38 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

9 O

1

1

2

5

sp 1

1

9

4 7

5

a

15

12

13

14

11

8

5

5

2

4

rD

04 9

9

FLOORBOARDS AND INNER SKIN

1.

a

BrakeValveandRudderPedallinkagc Control Cables, ControlSedor

4.

8.

HydraulicLinesand AirDucts Brake System Shuttle Valves and Hydraulic Lines Control Cables, Pulleys and Roll Servo ParkingBrakeValvesand HydraulicLines Control Cables, Pulleys and Aileron Rudder interconnect

9.

Cabin AirDistribution Ducts

5. 6. 7.

10.

Hydraulic

11.

Control

12. 13. 14. 15.

16.

Pulleys

Lines and

and

Hydraulic Lines

2. 3.

00

EmergencyAir Lines

Cables, Pulleys and Anti-Collision Deacon

WarningControlUnit Computer Spoiler Computer Aural

MachTrim

Squat Switch Relay Panel FuselageFuel Cell

(VIEW LOOKING FORWARD) FRAME 25

(Aircraff eauiatled with 36-Inch Door) (TWICAL)

Fuselage Figure 9 (Sheet 6 of 6)

Access Doors and Panels

EFFECTNITY: SRM-4

MODEL 35/36SERIESAIRCRAFT

51-00-03

Page 39 May 15/92

Learjet STRUCTURAL REPAIR MANUAL INVESTIGATION AND AERODMAMJC SMOOTHNESS

1.

STRUCTURAL IDENTIFICATION

INVESTIGATION A.

to resist variable forces imposed upon it in operation. the The structure must distribute these forces to principal structural strength members of the wing and fuselage. When a member has been damaged, a complete and thorough inspection must be made. This inspection should include the damaged structural member and the adjacent or attaching

The

primary

structure of

an

aircraft is

designed

possible that the damaging force might have been transmitted over the surrounding structure, causing secondary damage ir~ areas other than the primary damage area. Should the secondary damage not be discovered, forces distributed through the structure during normal aircraft operations may cause this structure to fail. Careful investigation must be made of all structure across which the forces must travel, and parts must be checked for possible misalignmcnt. Additionally, the use of X-ray and Eddy current inspections will further support the search for secondary damage. (Refer to the appropriate Leajet Non-Destructive Inspection [NDI] Manual.) members. It is

2.

AIRFRAMEAND MATERIALS INSPECTION A.

AirframeInspection (1) Preliminary External Inspection A

great deal may be learned about the

condition of the internal structure of

an

aircraft

by

a care

wings, stabilizers, and fuselage. Some indications might be buckle patterns on surface skin of stabilizers and along the sides, top, and bottom of fuselage. Loose, tipped, or sheared fasteners, and joggles or bulges in the skin at structural joints or where ful examination of the skin

heavy fittings

are

on

the

thorough inspection of the underneath structure parts for tears, cracks, buckles, and misthese parts is reason for a close inspection of the stntc-

attached, indicate that

a

and other nonstructural

should be made.

Inspect fairings

alignment. Any tures they cover.

unusual appearance of

Check also the fit of doors, covers, panels, etc. Anything unusual about their fit or alignment may indicate a warped or sprung structure, and is cause for inspection of that structure. When

possible,

actuate control

surfaces, flaps, spoilers,

etc.

Observe these units

closely through-

They should operate freely and without binding or chafing. Check the units in closed positions for proper alignment with adjacent members.

out their travel.

the

zero or

(2) Detailed Visual Inspection

Carefully inspect

all

areas

adjacent

to the obvious

damage. Inspect forgings

and other machined

often be done

by observhaving the rivet at bolt or a or heads, edge of by slight space edges, by tipped ing paint for bolts examine from and bolts When two a surfaces. remove suspected fitting possible, faying evidence of shearing or bending. Check bolt holes for elongation. parts

for cracks and for evidence of their

the

been moved. This

can

around the

warpage and jogglcs. Check for sheared, loose, or members is also important. Using a straightedge, frame webs and bulkheads. Any deviation should be webs, spar

Inspect supporting structures for buckling tipped fasteners. Alignment with adjacent check known flat

areas

such

as

thoroughly investigated.

EFFECTIVITY: SRM-4

ALL

51-10-00

rage 1 May 15/92

Leariet STRUCTURAL REPAIR MANUAL damage is suspected, a close examination is justified for joined or where heavy weights are supported. The princimajor components their with of this areas nature, supporting structures, are as follows: pal (a) Wing-to-fuselage attachments

When all

03) (c) (d) (e) (f)

aircraft has been

an

areas

damaged,

where

or

are

Vertical stabilizer attachments Rudder

hinge Landing gear trunnions and actuator attach points Pylon and nacelle attachments Engine mounts

inspection throughout disassembly and repair of aircraft. During this time, indications unsuspected damage are often revealed. When new parts being installed do not fit properly, find out why. It may be because of damage that has been overlooked. Overpressurization or Hard Landing Inspections When an aircraft has been subjected to overloads from overpressurization or hard landing, a careful inspection of the structure should be made to determine whether damage was sustained. Inspection of the structure should be concentrated on finding fractures, or partial fractures (appearing as cracks), sheared or partially sheared fasteners, cracked or broken lugs (or other fittings), cracked or broken spars, longerons, etc. (1) Hard or Overweight Landings After every hard or overweight landing, inspect the following components and areas: (a) Wing lower skin in landing gear rib area for skin buckles, fastener failures, security of landing gear rib and trunnion fittings. (b) Wing-to-body fittings and supporting structure for security, fastener condition, and permaContinue of

B.

nent

deformation.

(c) Trailing

edge region

of

wing

for local deformation

affecting

normal usage of

flaps

and aile-

rons.

(d)

Tip tank-to-wing tener

attachment and

wing

extension attachment at WS 181 rib for

tion. It is not necessary to evident.

remove access

security,

fas-

failures and/or permanent deformastraps unless excessive fastener load or working is

condition, and evidence of excessive load such

as

(e) Keel beam and attachments for security, fastener condition, permanent deformation and (f)

torque of primary tension joint bolts. landing gear assemblies, and

Nose and main

damage

or

deformation. Actuator attach

nose

points

and

and main gear actuator assemblies for support structure for security, fastener

condition and permanent deformation.

(g) Engine mount castings, for permanent deformation or cracks and support structure, ing pylon beams and beam-to-fuselage fittings, for security and fastener condition.

includ-

(2) Severe Turbulence and/or Maneuvers After

and

flight involving

severe

turbulence and/or maneuvers,

inspect

the

following components

areas:

(a) Wing-to-body fittings and supporting

structure for

security,

fastener condition, and perma-

nent deformation.

Cb)

Trailing edge region

of

wing

for local deformations

affecting

normal usage of

flap

and aile-

ron.

EFFECTIVITY: SRM-4

ALL

51-10-00

Page 2 May 15/92

Learjet STRUCTU RAL REPAIR MANUAL (c) Tip tank-to-wing attachment for security, fastener condition and permanent deformation. (d) Keel beam and attachments for security, fastener condition permanent deformation, and

torque of primary

tension

joint bolts.

(e) Canted bulkheads and lower fin spar attachments in aft tailcone. Check for fastener security,

permanent deformation of bulkheads and spar assemblies. (f) Horizontal stabilizer hinge fittings, actuator and fittings, and stabilizer center section structure for security, permanent deformation, skin buckles, or other evidence of overload. stabilizer for permanent deformation, skin buckles, and security at primary attachVertical (g) ments. mount castings for permanent deformation or cracks and support structure, including pylon beams and beam-to-fuselage fittings, for security and fastener condition. OverheatInspections Three methods are used in checking airplane structures after overheating: visual inspection for buckles, canning, and primer discoloration; hardness testing of questionable parts with a portable or a stationary hardness tester; and tension-testing of specimens taken from areas of doubtful val-

(h) Engine

C.

ues.

(1) Buckles, Canning and Primer Discoloration Visual Inspection

inspection of an airplane, the search for buckles or canning is primarily conpossibly weakened condition of primary internal structures. This is especialwhen the overheating has been in the wing area. It is possible that an area unafimportant ly fected by the fire directly may have been bent enough to receive a permanent set. In the visual

cerned with the

Large (or thick)

aluminum parts, such

and extruded

Similar

as

forgings,

are

not as

quickly

affected

components. However, when heat has been great enough

thinner and smaller

parts, all heavy fittings

parts from unaffected

areas

in the

area

by

heat

to

injure

as are

sheet

should be removed and hardness-tested.

may be used for

a

comparison.

It is often necessary to remove sample disks from sheet-metal parts, except wing skins, in order to test them on a bench-type hardness tester. Disks for this purpose should be removed

with

a

one-inch hole

saw.

If the

parts are

to be retained in use, make

repairs as directed

in the

applicable chapter of this manual. Access hole

also

covers

in the overheated

area are

provide an easily replaceable part

samples testing.

excellent

for destructive

for hardness

sampling. They

When tension bars from sheet-metal parts are taken for laboratory testing, the blanks removed should measure 1 x 7 inches. However, pieces measuring 1 x 5 inches are acceptable.

They should be cut

with the

long edges in line

with the

grain whenever possible.

samples are sent to a laboratory for analysis, information as to the type and duration of the overheating should be included. Also, the part number, whether metal or alloy, grain direction, etc., should be included wherever determinable. When

EFFECTIVITY:

ALL

parts

or

51-10-00

rage 3 SRM-4

May 15/92

Learjet STRUCTURAL REPAIR MANUAL Determining the extent of overheat damage by primer comparison can be a good indication when used carefully. A clean sample of the primer known to be unaffected by heat is compared with primer in the heated area. The sample should be from the same general area of the structure in question. The suspected area must be free of dirt, oil, and smoke. exposed to about 3000F of heat for a few minutes, it darkens. Temperatures that discolprimers will change the physical properties of 2024-T4 and 7075-T6 alloys. The 7000 Series alloys that are already in the T6, or artificially aged, condition are softened and weakened. The 2024-T4 is artificially aged and hardened, until the temperature reaches 500"F; then, with

When or

increased heat, this metal also softens and weakens. When the temperature of 2024-T4 is raised to 3000F to 5000F for a short period under uncontrolled conditions, as is the case in an aircraft fire, the inherent corrosion-resisting properties are seriously affected. Both 2024-T4 and 7000 Series be

subjected

er

is evident.

to

more

alloys (T6 condition) that are of questionable value and should testing when the slightest discoloration of the prim-

accurate methods of

(2) Hardness-Testing and Tension-Testing Reliable limits of correlation between hardness tests and tensile tests have been established

alloys. Materials reading may be considered acceptable:

for the 7000 Series aluminum "B" scale

that meet the

following

minimum Rockwell

Rg 88 (min)

(a) 7075-T6

replaced, or specimens should be rereadings and sent to a laboratory for ten-

Material that falls below the minimum should be moved from the

areas

with the lowest Rockwell

sion tests.

readings are not accurate indications of heat damage on 2024-T4 because of quick heating to 3000F may not raise the hardness number above normal but will affect the corrosion resistance. Therefore, if primer discoloration indicates that heat has affected the material, the material should be replaced or a specimen tests. should be removed and sent to a laboratory for tension and corrosion-susceptibility Hardness test

the corrosion factor. A

undergone slight meoverheating, every effort should be made to protect the metal. Painted areas should be stripped, treated with phosphoric cleaner, chemical-film-treated, and repainted. Surfaces not normally painted should be treated with phosphoric cleaner. Structural Joint Wear Inspection Wear allowances and repair data for fittings, forgings, and structural joints are shown in 51-71-00. If

a

decision is made to retain in

chanical

D.

EFFECTNITY: sRM-a

ALL

change

use a

section of 2024-T4 that has

due to

51-10-00

Page 4 May 15/92

Leariet ~Learieti STRUCTURAL REPAIR MANUAL

LOADS

/--TRANSITION POINT LOAD PATTERNS HARD TWO-WHEEL

(MAINGEAR)LANDING Resultant Inertia Load-

ing

Distribution

Loads these the

are

the

loading local

(weight),

on

f

~21

-~Initial Loads

LOADS

Airframe.

of

product

intensities and

distributed

BUCKLES

mass

combined with the

Lbl4P

initial external loads.

O

BUCKLE PATTERNS

HARD TWO-WHEEL

(MAIN GEAR) LANDING NOTES: Buckle

patterns shown

in the dia-

grams indicate the directions of the buckles that would tend to form in the skin

as a

loads

in

wheel

imposed landing.

result of the

a

hard

two-

B~1

Location of transition of buckle di-

loading transition point may be in a difpoint. ferent location for each landing, depending on gross weight, CG location, sinking speed, angle rection matches

8

This

BUCKLES

from horizontal, etc.

Buckles shown

are

for

fuselage

only. (TYPICAL) Load and Buckle Patterns Figure 1 (Sheet 1 of 3)

EFFECTIVITY:

ALL

51-10-00

Page SRM~

5

May15/92

Learjet ~arjet

STRUCTURAL REPAIR MANUAL LOADS

BUCKLES

/zi~b

1

oooo~ll

i

HARD

10000

THREE-WHEEL LANDING

LOADS

BUCKLES

TRANSITION POINT

OD00

HARD NOSE WHEEL LANDING

I

---)Initial Loads ----tResultant Inertia Load-

ing

Distribution

Loads

are

loading

the

on

Airframe.

product of

these

intensities and the lo-

cal distributed

(weight),

mass

combined with the initial

ex-

LOADS

ternal loads.

TRANSITION POINT

NOTES:

Buckle patterns shown in the diagrams indicate the directions of the buckles that would tend to form in the skin

as a

result of the

imposed in the landing figuration shown. loads

con-

Location of transition of buckle direction matches

loading

transition

may be in a different location for each landing, depending on gross weight, CG

point.

This

point

location, sinking speed, from horizontal, etc. Buckles shown

are

for

angle

fuselage

SUDDEN STOP

only.

LEFT WHEEL

(RightWheelOpposite) (TYPICAL) Load and Buckle Patterns

Figure EFFECTIVITY: SRM4

ALL

i

(Sheet

2 of 3)

51-10-00

Page 6 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ~Initial Loads

~Resultant Inertia LoadDistribution

ing

Loads

are

loading

the

Airframe.

on

product of

these

intensities and the lo-

cal distributed

mass

(weight),

combined with the initial

ex-

ternal loads.

TRANSITION POINT

SUDDEN STOP

RIGHT WING

(Left Wing Opposite)

NOTES:

SIDE TOW TOWARD READER

Buckle

SIDE DRT~T TOWARD READER

patterns shown

in the dia-

grams indicate the directions of the buckles that would tend to

YAW (TAIL AWAY FROM READER)

form in the skin

loads tions

imposed given.

Buckles

shown,

may be of either type or a

combination of both.

Buckles shown

COMPRESSION BUCKLES- ONE

as a result of the under the condi-

are

for

fuselage

only.

SIDE ONLY SIDE TOW TOWARD READER YAW (TAIL AWAY EROM READER)

SIDE DRIFT LANDING AND SIDE TOW

DIAGONAL SMEAR BUCKLES ON BOTH SIDES BUT OFPOSITE IN DIRECTION

(TYPICAL)

Load and Buckle Patterns

Figure 1 (Sheet 3 EFFECTIVITY: SRM-b

ALL

of 3)

51-’10-00

Page 7 May 15/92

Learjet STRUCTURAL REPAIR MANUAL INVESTIGATION AND AERODYNAMIC SMOOTHNESS 1.

DAMAGE CLASSIFICATIONS

A.

damage is damage that can be permitted to be "as is", or may be corrected by a simple procedure, without restricting flight. In most cases, a corrective action must be taken to keep the damage from spreading. Frequent inspection of areas with allowable damage is necessary to ensure the damage does not spread. Limitations regarding the extent of allowable damage vary in different locations throughout the airplane. These limitations are shown on the illustrations of allowable damage for the Allowable

various B.

C. D.

2.

ALLOWABLE DAMAGE

components.

flight damage is damage that can be left "as is" or requires only minor repairs to allow the aircraft to be flown to a repair facility, Repairable damage is damage that may be repaired so as to make the strength of the repaired structure equal to, or greater than, that required to maintain the structural capability of the airplane. Damage requiring replacement of parts including any damaged component that must be replaced when the location or the extent of damage makes it impractical to repair. When a damaged component or part is replaced, care should be taken to avoid damage to adjacent or attaching structure. One-time

CAUSESANDTWES OFDAMAGE which may occur to an aircraft. However, for purposes of or impact, stress, fatigue, corrosion, erosion and overheat. description, some of the causes are minor damage, such as a small hole or dent, to extensive from varies A. Collision or impact damage

There

are

many

causes

and

degrees of damage collision

B.

C.

D.

damage, such as torn, crushed, or burned skin and structural members, and misalignment of the airplane. Damage such as this can occur at any point on the airplane. Stress damage generally consists of loosened, sheared, or popped fasteners, wrinkled skin or webs, and cracked or deformed structural members. Damage such as this is caused by abnormal stresses imposed upon the members. Fatigue damage generally consists of small cracks that are caused by vibration, "oil cans," and variable loads imposed on skin, fittings, and load-bearing members where fittings are attached. Damage of this type occurs more frequently as the operation time of the aircraft accumulates. Corrosion damage may be defined as the gradual chemical or electromcchanical attack on a metal by atmosphere, moisture and other agents. The types of corrosive attack most commonly encountered are ordinary corrosion, resulting in a uniform deterioration or pitting attack on the surface; intergranular corrosion, resulting in a grain boundary attack; and stress corrosion and galvanic corrosion, resulting in the deterioration of the more active of two dissimilar metals in contact. Corrosion products from the deterioration of the

instance, magnesium and

more

active metal will sometimes corrode the other dissimilar metal (for

and aluminum).

fire-extinguishing agents

Corrosion caused

by foreign

Monobromotrifl u orometha ne, which i s used i n the

NOTE:

materials such

as

battery

acid

may be encountered under certain conditions.

portable

an d

engin e

fire

ex

tinguishers,

is non-corrosive.

(1) Ordinary corrosion may be recognized by aluminum and

duIling or pitting of the surface, accompanied by by a reddish rust coating on steel. Corrosion cannot a

powdery deposits always be detected by a visual examination alone, where the paint falls off under pressure. white

EFFECTIVJTY: SRM-4

ALL

on

but may sometimes be discovered under

paint

51-10-00

Page 101 May 15/92

Learjet STRUCTURAL REPAIR MANUAL (2)

the grain boundaries of the material resulting potential between the grain boundary material (or center of the grains). This corrosion cannot be readily recognized during a sur-

Intergranular corrosion from

a

is corrosion

occurring along

difference in corrosion (or electrochemical)

and the matrix

face examination until actual failure of the material. This failure then shows up much

as a

crack

might appear. (3) Stress corrosion occurs

as a

result of the

susceptibility of materials

to

intergranular corrosion com-

bined with presence of internally or extcnlally applied stresses such as residual stresses developed from quenching, welding, severe forming, or externally applied severe stress. occurs in the presence of moisture when two different metals are in actual contact, an electric current flows from one metal to the other, resulting in corrosive attack on one of the materials. This is similar to the action that takes place within a common storage battery. In galvanic corrosion, the more active of the two dissimilar metals serves as the anode, the moisture

(4) Galvanic corrosion

becomes the

electrolyte,

and the less active metal acts

as

the cathode. The

more

active of the two

metals suffers the corrosive attack.

(5) Corrosive Effects of Dry Chemical Powder (Sodium Bicarbonate). Dry chemical powder is

a speWhen sodium bicarbonate is heated, it decomposes and releases carbon dioxide gas and water vapor. The decomposed product is sodium carbonate (soda ash). In the dry state, sodium bicarbonate is harmless and sodium carbonate is relatively

cially prepared grade of sodium bicarbonate.

so.

In the wet state tin solution with

craft metals, and sodium carbonate is als.

water), sodium bicarbonate is mildly corrosive

extremely

(6) Corrosive Effects of Mechanical Foam. harmless

vegetable compound.

The

The

only

caustic and will

rapidly attack

agent combined with

water to

to most air-

most aircraft met-

produce

foam is

corrosive action of this combination is that caused

a

by

the water used.

(CF? Br), and Carbon Dioxide. These fireextinguishing agents evaporate rapidly and are relativePy harmless. No cleanup is required following use of these agents. Erosion damage is usually encountered on reinforced glass-fabric component such as antennas, radomes and wing tips. While this material is resistant to rain, weather, and aging, it may be eroded by hail, sharp objects, flying stones, or sharp blows. Overheat damage is most likely to occur in the engine nacelle structure and skins. Overheat damage may be detected by skin and web buckles, canning and primer discoloration. (7) Corrosive E ffects of Monobromo trifluorometha ne

E.

F.

EFFECTIVITY: SRM4

ALL

51-10-00

Page 102 May 15/92

Learjet 11R´•rpl STRUCTURAL REPAIR MANUAL INVESTIGATION AND AERODYNAMIC SMOOTHNESS 1.

REPAIR

AERODYNAMIC SMOOTHNESS Modern aircraft

specifications require that the aircraft exterior surfaces be of extremely smooth construcdesign performance. The structural repair person must keep this in mind when making reor pairs changes. Figure 201 shows the areas that are most critical aerodynamically; however, smoothness of the entire aircraft surface area is a critical requirement from the performance standpoint. The seriousness of this condition is proportional to the airflow disturbance created. (Refer to 51-40-04 for classification of zone and fastener smoothness requirements.) tion to obtain

The

prime considerations of aerodynamic smoothness are.parasite drag (drag caused by skin friction and nonlifting surfaces of an aircraft) and the aerodynamic load distribution on the surface. Any repair or change that increases parasite drag will reduce the top speed of the aircraft. Also, range will be reduced, since more power, and thus more fuel, is required to maintain cruising speed.

Any change that disturbs the smooth flow of air over a critical surface will change the load face, as well as increase the drag.

Any change in the airflow around

on

that

sur-

the control surfaces is critical, since the control effectiveness may be af-

fected.

problem that may arise is buffeting. Buffeting can be caused by airflow separation around an abrupt change, such as a nonflush patch, in the mold line. Another

Temporary (Nonflush) repairs are permitted in some areas designated "critical". (See Figure 201.) porary repairs must be replaced by permanent repairs at the earliest possible time.

Tem-

Paste-type fillers, that cure to a hard-rubber-like consistency, are used to fill skin and door gaps, to blend overlapping surfaces, and in other similar conditions to achieve a satisfactory degree of aerodynamic smoothness. (Refer to 51-70-01.)

EFFECTIVITY:

SRM-4

ALL

51-10-00

Page 201 Jun1/95

Leariet Cearjei TEMPORARY REVISION NO. 51-1 MANUAL AFFECTED:

Leajet 20/30 Series Structural Repair Manual (SRM-4).

FILING INSTRUCTIONS:

Insert

adjacent

to

51-10-00, page 202, dated

May 15/92,

and retain until fur-

ther notice.

REASON:

To

INSTRUCTIONS:

clarify and Revise

define

Aerodynamically Critical Areas.

Figure 201, Sheets

TEMPORARY REVISION NO. 51-1

1

2,

as

shown

on

enclosed pages.

51-10-00

Page SRM-~

1 of 3

Aug 25/97

Learjet

STRUCTURAL REPAIR MANUAL CRITICAL AREAS

Horizontal Stabilizer Lower Surfaces)

Temporary (nonRush) repairs are not pennitted in these areas.

mmmnm

I

I

(Upper and

Flight characteristics could be affected by temporary (nonflush) repairs in these areas. If temporary repairs are made, a review by Leajet Customer Service Engineering is mandatory and a Right test maybe required.

Elevator

LeadingEdge

FonvardoiCutout

nidettinrepaiIsare nep these

areas.

Fuselage skin

Vertical Stabilizer areas

adjacent to pyion, pyIon,

and lower surfaces of a;ld inboard half of nacelle. upper

Engine Inlets

Rudder Leading Edge Skin and 6-Inches Forward of Cutout

Wing Surfaces, Ailerons and

Flap-Leading Edge Skin

n0 \´•I

Wing Leading Edge

Aileron Leading Edge and Upper Main Box Skins forward of AiTeron

Static Port

(If Installed)

Model 23/24/25/35/36 Series Aircraft

(TYPICAL) clloc-2

TEMPORARY REVISION NO. 51-1

SRM-I

Aerodynamically Critical Areas Figure 201 (Sheet 1 of 2) 51-10-00

Page 2 of 3 Aug 15/97

Learjet

STRUCTURAL REPAIR MANUAL CRITICAL AREAS

Temporary (nonflush) repairs permitted in these areas.

mmmmn

are not

Flight characteristics could be affected by temporary (nonnush) repairs in these areas. If temporary repairs are made, a review by Leajet Customer Service Engineering is mandatory and a flight test may be required. Temporary (nonflush) repairs are permitted in these

areas.

Elevator Leading Edge Skin and Forward of Cutout

Horizontal Stabilizer (Upper and Lower Surfaces

Vertical Stabilizer

Winnlet

(Bot~ Surfaces)

Fuselage skin

areas

adjacent

to

pylon,

surfaces of pylon, a~d inboard half of nacelle. upper and lower

Engine Inlets

Delta Fins

(BothSuriace5)

Rudder Leading Edge Skin and ~-lnches Forward of Cutout

Wing Surfaces, Ailerons and

Flap‘teading Edge Skin

r

o" O

O

Wing Leading Edge Aileron Leading Edge and Upper Main BoSi Skins Fonvaia of Aileron.

Static Port

(If Installed)

Model 28/29/31 Series Aircraft

(TYPICAL)

Aerodvnamically Critical Areas Figure 201 (Sheet 2 of 2) TEMPORARY REVISION NO. 51-1

51-10-00

Page 3 of 3 SRM´•~

Aug 15/97

Learjet

r

STRUCTURAL REPAIR MANUAL NOTE: Please CRITICAL AREAS

see

the

TEMPORARY REVISION revises this page.

Temporary (nonflush) repairs are not permitted in these areas. Elevators (Upper and Lowa SurfaQs)

Flight characteristics could be affected by temporary (nonflush) repairs in these areas. If temporary repairs are made, a review by Leaiet Field Service Engineering is required and a flight test must be performed.

I

I

Temporary (nonflush) repairs are permitted in these

areas.

Horizontal Stabilizer (Upper and Lower Surfaces) Vertical Stabilizer

adjacent to pyion, lower surfaces of pylon, and

Fuselage skin upper and

areas

inboard half of nacelle.

Rudder (Both Surfaces)

Ailerons (Upper and Lower Surfaces)

Flaps (Upper

and

O

Lower Surfaces)

O

Nacelle Inlet

OV~

Wing Leading Edge

SpoilcrP(UppcrSurfarr)

i

Static Port

(RH Side

Only) (TYPICAL)

6110GZ

EFEECT~IVITY: SRM-(

Wings (Upper

and

Lower Surfaces)

Aerodynamically Critical Areas Figure 201 (Sheet 1 of 2) MODEL 23/24/25/35/36 SERIES AIRCRAFT

Q 51-10-00

Page 202 May 15/92

Learjet STRUCTURAL REPAIR MANUAL CRITICAL AREAS

Temporary (nonflush) repairs are not permitted in these areas.

Flight characteristics could be affected by temporary (nonflush) repairs in these areas. If temporary repairs are made, a review by Learjet Field Service Engineering is required and a flight test must be performed.

I

I

Elevators

(Upper and

Lower Surfaces)

Temporary (nonflush) repairs are permitted in these

areas.

Fuselage skin areas adjacent to pylon, upper and lower surfaces of pylon, and

Horizontal Stabilizer

inboard half of nacelle.

(Upper and Lower Surfaces)

BiiQ-~ ii,

i:iii-ii:~

Vertical Stabilizer Biia~isiiiiisii_i,:

Rudder

I Ailerons

(Both Surfaces)

(Upper and

Delta Fins

Lower Surfaces)

(Both Surfaces)

Flaps (Upper and

Nacelle Inlet

Lower Surfaces)

Static Port

(RH Side

Only)

O

O

O

O

C)

~Spoilers (Upper Surface)

Wing Leading Edge

Wings (Upper and--’

Winglet

Lower Surfaces)

(Both Surfaces)

(TYPICAL)

Aerodynamically Critical Areas Figure 201 (Sheet 2 of 2) EFFECTIVITY: SRM-4

MODEL28/29/31 SERIESAIRCRAFT

hL

NOTE: Please

see

fhe

TEMPORARY REV/SION that revises this page.

51-10-00

Page 203 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL MATERIALS- STRUCTURAL IDENTIFICATION CONSTRUCTION MATERIALS

i.

A.

repair of this aircraft may be listed in the following alloys, steels, extrusions, and formed sections), transparent plastic, and

Most of the materials used in the construction and

categories:

metals (aluminum

fasteners. As a general-purpose material, 2024 aluminum alloy is used: where greater compressive strength is required, 2014-T6 aluminum alloy is used. 2014-T6 is used for die forgings. 6061 alloy is used in areas where welding is required. (2) Steel -The principal steel alloy used in this aircraft is 4130 low-alloy steel. (3) Plastic Transparent plastics used in this aircraft for cabin windows is MIL-P-25690 stretched acrylic. (4) Fasteners The majority of the structure of this aircraft is assembled with conventional fixed and removable fasteners, such as standard aluminum alloy and steel rivets (driven and blind), screws, bolts, nuts, and quick-attach fasteners. For additional information concerning fasteners, refer to

(1) Aluminum

51-40-00. B.

The

following

materials

to the referenced

ALL

were

used in the construction of the

Learjet. Repair

materials must conform

specifications, as applicable

51-30-00

Page SRM-4

1

May 15/92

Learjet:

STRUCTURAL REPAIR MANUAL SPECIFICATION

MATERIAL

REMARKS

I

ALUMINUM BARS AND SHAPES

or

2014-T6511

aluminum

alloy shape

2024-0

2024-T351

2014-0

or

aluminum

Fed.

Spec QQ-A-200/2

Fed.

Spec QQa-225/6

alloy. Use 2024-0 only forming is too severe for 2024-T351. Heat-treat all 2024-0 parts to 2024-T42 condition after forming. Rolled bar. General purpose if

alloy shape

Do not weld. 2024-0

or

aluminum

Fed.

2024-T3511

alloy bar

or

Spec QQ-A-200/3

shape

Use 2024-0

if

forming

Extruded bar

or

is too

for 2024-T3511. Heat-treat all 2024-0

severe

shape.

to 2024-T42 condition after

parts

only

forming. Do

not

weld. 6061-0

or

6061-T6

T6511 aluminum

Fed.

or

Spec QQ-A-225/3

alloy bar ALUMINUM CASTINGS

356-T6 aluminum sand

Fed.

alloy

Spec QQ-A601

High-strength

structural

casting alloy. Heat-

treatable and weldable.

casting

ALUMINUM FORGINGS 201 4-T6 and 7175-r/36

Fed.

Spec QQa-367

High-strength

heat-treated. Not weldable.

ALUMINUM SHEET AND PLATE 2024-0

or

Fed.

2024-T3

bare aluminum

alloy

Spec QQd-250/4

Gages

from 0.010 to 0.250. Use 2024-0 when part

cannot be made from 2024-T3. Heat-treat all

sheet

2024-0

parts

to 2024-T42 condition after

forming.

Not weldable. Fed.

2024-0, 2024-T351 bare aluminum

Spec QQ-A-250/4

Plate thicknesses from 0.250 to 3.000. Use 2024-0 when

alloy plate

parts

cannot be formed from 2024-T351.

Heat-treat all 2024-0 after Fed.

2024-0 and 2024-T3

clad aluminum

alloy sheet

I

Spec QQ-A-250/5

forming.

parts

to 2024-T42 condition

Not weldable.

0.010 to 0.250. Use 2024-0 only when part cannot be made from 2024-T3. Heat-treat all 2024-0 parts to 2024-T42 condition after forming. May be spot- or seam-welded but not fusion-

Gages from

welded.

Construction Metals Table 1 (Sheet 1 of 3)

EFFECTIVITY:

ALL

51-30-00

Page 2 SRM-4

Tun 1/95

STRUCTURAL REPAIR MANUAL REMARKS

SPECIFICATION

MATERIAL

ALUMINUM SHEET AND PLATE 6061-0, 6061-T4 and

Fed.

Spec OQ-A-250/11

6061-T6 aluminum alloy sheet

or

Sheet gages from 0.010 to 0.250. Plate thicknesses from 0.250 to 3.000. Not to be used where other

alloys

plate

are

suitable. Use 6061-0 only if part cannot

be made from 6061-T4. Use 6061-T4

only

if part

cannot be made from 6061-T6. Heat-treat 6061-0

and 6061-T4 to T6 condition when required. May be spot- or seam-welded in the treated condition, and fusion-welded if resultant annealed condition in area

of weld is

acceptable.

STEEL BARS 4130 condition D, condition F

Spec MIL-S-6758

4340 steel bar

Spec MIL-S-5000

condition D

Low-alloy steel. Condition D (normalized) may copper-brazed or fusion-wekled, but not spotor seam-welded. May be heat-treated.

be

Low-allow steel. May be fusion-wekfed, but not or seam-welded. May be heat treated.

spot-

STEEL SHEETS AND PLATES 301 CRES sheet and

Spec MIL-S-5059

Sheet gages from 0.012 to 0.250. Plate thicknesses from 0.250 to 2.000. Unstabilized. Maximum service temperature is 7000F. Annea)ed material is nonmagnetic. May be spot- or seam-welded but not brazed or fusion-welded.

Spec MIL-S-6721

Sheet gages from 0.012 to 0.250. Plate thicknesses from 0.150 to 1.000. Use Specification MIL-S-5059

plate, annealed and 1/2 hard

321 heat-resistant and

CRES sheet and

plate

if possible. Forms easily, annealed and non-magnetic. Not to be heat-treated. Can be spotor seam-welded, fusion-welded, or silver-brazed. 4130 steel sheet and

plate, condition

A

or

N

Spec MIL-S-18729

Sheet gages from 0.020 to 0.250. Plate thicknesses from 0.250 to 1.000 low-alloy steel. May be

copper-brazed seam-welded.

or

fusion-welded, but

May

not

spot-

or

be heat-treated.

Construction Metals Table 1 (Sheet 2 o~ 3)

EFFECTNITY:

ALL

1 51-30-00

Fage 3 SRM~

lun 1/95

~Leariefl STRUCTURAL REPAIR MANUAL MATERIAL

REMARKS

SPECIFICATION STEEL TUBING

Spec MIL-T-6736

4130 steel tube

BRONZE BAR AND CASTINGS Aluminum-bronze bar

Used in the manufacture of

AMS4640

bushings and bearings.

STEEL CASTINGS 17-4 PH and 15-5 PH

AMS5355 and AMSS357

Used in forward and aft

engine mounts, and in

spoiler actuator fittings.

Construction Metals Table I (Sheet 3 of 3)

EFFECTIVITY:

ALL

51-30-00

Page 4 SRM-4

Jun1/95

E~t STRUCTURAL REPAIR MANUAL 0312

0~030 01)60

0~062

O’k~L_r 1.000

R

0~062

--I’

Material:

High Tear Silicone Rubber Dow Coming Silastic 55U Silicone Rubber

Durometer:

Shore A 40 to 50

Tolerances:

1116

~0.015)

5/16 (f0.015)

(I~t0.030)

1.0

Grey

Color:

EXTRUDED SEAL S-306

(MOLDED)

5 Points Centered 0.030 high at 45" angle 0~275 R

1

0.125

t,0.OSO (f0.030) Constant

0.170 to 0170

0.125R

t

0.187 00628

(Typical)

0.750

1

0.120

0.030

Tear Silicons Rubber Dow

Material:

High

Durometer:

Installation:

Shore A 50 (~5) No. 21 Hole Recommended

Color:

Grey

1500 Between Pull Thru’s

Coming Silastic 55U Silicone Rubber

CABIN DOOR SEAL S-308

(MOLDED)

Extrusions and Formed Sections

Figure 1(Sheet 1) EFFECTIVITY:

ALL

51-30-00

Page 5 SRM-4

Jun 1/95

Learjet ~Learjet( STRUCTURAL REPAIR MANUAL 0.062

4

CTypical)

0.062R

0375

0.0’6

~-0.046 0.171

Extrusion Die No.:

Material:

High Tear Silicone Rubber Dow Coming Silastic Synthetic Rubber

Specification:

Mll-S-6855, Class

Durometer:

Shore A 60

Color:

White

55U Silicone Rubber

4

EXTRUDED RUBBER CHANNEL S-325

(MOLDED)

0500

Coming

Silastic 55U Silicone Rubber

Material:

Dow

Durometer:

Shore A 50

Dimensions:

(In Inches~ Tolerances 0.500 (M.030), 0.062 (M.015) Grey

Color:

(~t5)

EXTRUDED SEAL S-341

(MOLDED)

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 2)

51-30-00

Page6 sRM-a

Jun 1/95

Leariet

STRUCTURAL REPAIR MANUAL

0.190 (+o.olo/-o.ooo)

0.250 (+0.000/-0.010)

Extrusion Die No.:

N/A

Material:

Nylon

6/6 DuPont Zytel 42

Specification: Durometer: Color:

Translucent

EXTRUDED TUBE S-355

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 3)

51-30-00

Page 7 sRM-4

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL 0.016 -0.008

0.984

0.079

1‘

1

t 0.984

0.079

Extrusion Die No.:

Alcoa 152232

Material:

2024-T4

Specification:

QQ-A-267

or

0.008 -0.004

r 0.016 0.008

0.098R ~0.024

0.008-0.004I-t:

2024-T3511

QQ-A-200/3

or

ANGLE S-502

.059 +0.008

900fl"

-0.004

0.709

f´•´•36~J

0.079R f 0.016

t

0.551f0.012

0.059+0.008 -0.004

Extrusion Die No.:

Alcoa 151922

Material:

2024-T4

SpeclficaUon:

QQ-A-267

or

2024-T3511

or

QQ-A-200/3

ANGLE S-512

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1 (Sheet 4)

51-30-00

Page 8 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

870

0.079

0.787 +0.016

1I

+0.008-0.004

0´•098R f 0.024

-0.008

0.787 +0.016

I_

~i

Alcoa 152022 2024-T4 or 2024-T3511

Specification:

QQ-A-267

or

1).079 +0.008 -0.004

-0.008

Eltruslon Die No.: Material:

\I

QQ-A-200/3

ANGLE S-515

Extrusions and Formed Sections

Figure EFFECTNITY:

ALL

I

(Sheet 5)

51-30-00

Page 5! SRM-4

Jun 1/95

Learjet ~Learjetl STRUCTURAL REPAIR MANUAL 1.260

,-r

+0.016~ -0.008

f

0.157 +0.012 -0.008

j

1.260 +0.016 0.098R f 0.024

-0.008

85"10’"f10 0.157

+0.012,I -0.008

Extrusion Die No.: Material:

Alcoa 152072; Pimalco 11225 2024-T6 or 2024-T6511

Specification:

QQ-A-261

or

QQ-A-200/2

ANGLE 5-516

61860

0.157 +0.012

-0.008

t

f 10

0.098R f 0.024

1.260 +0.016

1.260

+0.016-0.008

0.157

Extrusion Die No.:

Alcoa 152082

Material:

2024-T4

Specification:

QQ-A-267

or

+0.012-0.008

2024-T3511

or

QQ-A-200/3

ANGLE S517

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1 (Sheet 6)

51-30-00

Page SRM-4

10

Jun 1/95

Leariet I

STRUCTURAL REPAIR MANUAL

85" 40’ f 1" 0.118 +0.008 -0.004

T 0.098R f 0.024

0.984 +0.016 -0.008

0.984 +0.01

:t---if0.118

-0.008

Extrusron Die No.: Material:

2024-T4

Specification:

QQ-A-267

+0.008

-0.004

Alcoa 152102 or

2024-T3511 or

QQ-A-200/3

ANGLE S-519

Extrusions and Formed Sections

Figure EFFECTTVITY:

ALL

1 (Sheet 7)

51-30-00

Page SRM-4

11

Jun1/95

Learjet

STRUCTURAL REPAIR MANUAL 0.098 +0.008 -0.004 1.575 +0.016

-0.008

-~I

0.098R f 0.024 1.575 +0.016 -0.008 90"f 1"

Extrusion Die No.:

Alcoa 152192

Material:

2024-T4

Specification:

QQ-A-267

or

2024-T351 1

or

QQ-A-200/3

ANGLE S520

-It-

0.050

0.050R

0.075R

0.563

0.075R

J 0.750

0.050

Extrusion Die No.:

AND 10135-0601

Material:

2024-T4

Specification:

QQ-A-267

or

2024-T3511

or

QQ-A-200/3

EXTRUDED ANGLE 5-522

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1 (Sheet 8)

51-30-00

Page SRM~

12

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL 0.118

+0.00S-0.004

1

850 Lt 10

1.574 +0.024

0.098R f 0.024

-0.012

0.787

0.118 +0.008 -0.004 -0.012

Alooa 152142; Pimalco 11230 or 2024-T3511

Extrusion Die No.: Material:

2024-T4

Specification:

QQ-A-267

or

QQ-A-200/3

TEE S-524

1.574 +0.024

(e

0.118 +0.008 -0.004

-0.012

0.787

0.098R f 0.024 1.574 +0.024

-0.012

880 30’ f 10

-1

-/lt Extrusion Die No.: Material:

Alcoa 152132

Specification:

QQ-A-261

2024-T6

or

0.118

+0.008-0.004

2024-T6511

or

QQ-A-200/2

TEE S525

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 9)

51-30-00

Page SRM-4

13

Jun 1/95

Learjet ~Learjet

STRUCTURAL REPAIR MAN1JAL

I0.118

+0.008 -0.004

870 30’ fl

1.574 +0.024

0.098R f 0.024

-0.012

ij/ f

0.118 +0.008 -0.004

0.787

-0.012

Extrusion Die No.:

Material:

Alcoa 152162; Pimalco 11229 2024-T4 or 2024-T3511

Specification:

QQ-A-267

or

QQ-A-200/3 TEE S-526

0.118 +0.008

-1.197 +0.024

-0.004

-0.012

-t 1.574 0.098R f:0.024

+0. 240.78 -0.012

860 10’ f 10

0.118

Material:

Alcoa 152152; Pimalco 10966 2014-T6 or 2014-T6511

Specification:

QQ-A-261

Extrusion Die No.:

or

+0.008-0.004

QQ-A-200/2

TEE 5527

Extrusions and Formed Sections

Figure 1(Sheet 10) EFFECTIVITY:

ALL

51-30-00

Page sRM-a

14

Tun 1/95

Learjet

STRUCTURAL REPAIR MANUAL 0.016 -0.012

2284 1.142~0.008 0.157 f 0.008

+0´•047

0.197R 1574

;I

0.118

0.008 -0.004

0.059f0.008

-0.000

+0.024 -0.012

900 40’ f 10

ExtNsion Die No.: Material:

Alcoa 152212

Specification:

QQ-A-261

2014-T6

or

,I

0.008 -0.004

0.118

11‘

2014-T6511

or

QQ-A-200/2

TEE S-534

91"f 1"

-0.004

n

t 1.574 +0.024

0.047

0.197;R

-0.000

lil

-0.012

0.059f0.00s

I

I

0.157 f 0.008 1.142 f 0.008

0.118 +0.008 -0.004

2.284 +0.016

-0.012

Extrusion Die No.:

Alcoa 152222

Material:

2014-T4

Specification:

QQ-A-267

or

2014-T3511 or

QQ-A-200/3

TEE S-535

Extrusions and Formed Sections

Figure 1(Sheet 11)

EFFECTIVITY:

ALL

51-30-00

Page SRM-4

15

Jun 1/95

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL 1.969

0.512

0.177 0.394

0.098

i 0.980

jl

t

0.098R

0.039R

T

0.063R

0.689

C0.079 Extrusion Die No.:

Alcoa 165812

Material:

2024-74

Specification:

QQ-A-267

or

2024-73511

or

QQ-A-200/3

SEAT RAIL S-537

0.625

L

0.093R

_yaoa~rrwi 1.000

Extrusion Die No.:

Pioneer Aluminum Co. PA5580

Material:

2024-74

Specification:

QQd-267

or

17

2024-73511

or

QQ-A-20013

EXTRUDED ANGLE S-545

Extrusions and Formed Sections

]l;igure 1(Sheet 12) EFFECTIVITY:

ALL

51-30-00

Page SRM-I

16

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

-II-

0.079

-r n 0.787

0.008-0.004

0.098B~0.024

0.016-0.008 IIJ

1~-----´•1 i

0.787

0.079

0.008 -0.004

0.0163-0.008

Extrusion Die No.: Material:

Alcoa 151982 2024-T4 or 2024-T3511

Specifrcation:

QQ-A-267

or

QQ-A-200/3

ANGLE S-548

Extrusions and Formed Sections

Figure 1(Sheet 13) EFFECTNITY:

SRM-4

ALL

51-30-00

Page 17 Jun1/95

Learjet ~Learjetl STRUCTURAL REPAIR MANUAL 0.062R

(Typical 2 Places)

r:

0.094

1.312 0.1259

I 0.875

Extrusion Die No.:

I-

.i

0.0169

(Typical 3 Places)

Pioneer Aluminum, Inc. PA4126 or 2024-T3511

Material:

2024-T4

Speclfrcation:

QQ-A-267

or

QQ-A-200/3

EXTRUDED ANGLE S-549

,lyo.oss

1970

01163R C~ypical)

7 0.690

-I I-~

Extrusion Die No.:

Pimalco 20168, Alcoa 265045, or Pioneer Aluminum, Inc. PA19680

Material:

2024-T4

SpecificaUon:

QQ-A-267

or

2024-T351

or

QQ-A-200/3

EXTRUDED TEE S-551

Extrusions and Formed Sections

Figure 1(Sheet 14)

EFFECTIVITY:

ALL

51-30-00

Page SRM-4

18

Tun 1/95

Learjet

STRUCTURAL REPAIR I\RANUAL Radii Not Noted

0.016

are

0.020R

0.050R

f~JO.:25

~t

fe

0.060 f 0.010 1.150

0.350 l.ooo-

1

-I

1 2.500

-1

TT_0.241(Check 0.040

3.000R

Dim)

0.012

-0.000

Extrusion Die No.:

Texas Aluminum Co. T-8319, Alcoa 68115, Pimalco 20169, PA31694

Alaterial:

2024-T4

Speoifioetion:

QQ-A-267

or

or

Pioneer Aluminum Inc.

2024-T3511

or

QQ-A-200/3

DOOR STRUCTURAL CARRY THRU

(MALE) EXTRUDED S-552

Extrusions and Formed Sections

Figure 1(Sheet 15) EFFECTIVITY:

ALL

51-30-00

Page sRM-a

19

Jun 1/95

~Learjetl STRUCTURAL REPAIR ~AANUAL 4L

1

I /r O.OM)R

0.130R

(TypicalBplaces)

0.075R

0.3130R

0.665

~Y_U/

-I~-

0.080

(-f 0.950

_j-0.060

0.350

L

0.200

1.000i

0. 050

1.570

Material:

Texas Aluminum Co. T-8320 Alcoa 68671, or Pioneer Aluminum Inc. PA31960 2024-T4 or 2024-T3511

Specification:

QQ-A-267

Extrusion Die No.:

or

0.016 -0.000

QQ-A-200/3

EXTRUDED DOOR STRUCTURAIL OARRTTHRU 5-553

CTypical)

01150

-~11

r _L 0.750

0.010R

CTypical 3 Places)

)1

0.075R 0.075R

I- -I-l 0.750

Extrusion Die No.:

Pioneer Aluminum, Inc. PA5324, Alcoa 33372 or 2024-T3511

Material:

2024-T4

Specification:

QQ-A-267

or

QQ-A-200/3

EXTRUDED BULB AN(;LE S-554

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 16)

51-30-00

Page 20 SRM-4

Jun 1/95

~i´•t

STRUCTURAL REPAIR MANUAL

r 0.120R

l.qW~-- 1.WOi

1.WO

0.850

(Typical)

i.

j-Extrusion Die No.:

0.080

(Typical)

0.050

(Typical)

3.000

Pimalco 11246, Texas Aluminum Co. T-8321 or 2024-T3511

Material:

2024-T4

Specification:

QQ-A-267

or

QQ-A-200/3

EXTENDED WEB CHANNEL S555

2.9501

i 0.080

II

II

U

0.120(Typical)

1.950

Extrusion Die No.:

Alcoa 315942

~Haterlal:

2024-0

Specification:

QQ-A-267

or

or

Pioneer Aluminum, Inc. PA20333

QQ-A-20013

EXTENDED WEB CHANNEL S-556

Extrusions and Formed Sections

Figure 1(Sheet 17) EFFECT~VITY:

ALL

51-30-001

Page 21 SRM-4

Jun

1

1/95(

Learjet

STRUCTURAL REPAIR EAANUAL

Sharp Edges_

0.125

Rounded U.olO- Inch

T I

0.875

0.125

~e Extrusion Die No.: Material:

AND 10133-0703

Specification:

QQ-A-267

2024-T4

or

0875

CTypical)

-~T

2024-T3511 or

QQ-A-200/3

EXTRUDED ANGLE S557

0.0478

0.750

111

LI0.094R

~0.125R

j

i

j

0.094

CTypical)

-t

1500

Extrusion Die No.: Material:

AND 10136-1402; Pimalco 10180 2024-T4 or 2024-T3511

Specification:

QQ-A-267

or

QQ-A-200/3

EXTRUDED TEE S-558

Extrusions and Formed Sections

E;igure 1(Sheet 18)

EFFECTIVITY:

ALL

51-30-00

Page 22 SRM-4

inn 1/95

Learjet Leariet i

STRUCTURAL REPAIR MANUAL

0.1Z0R 0.620 0.12R

I- 0.620Ij Tool No.:

Roll

Material:

0.032 2024-T4 Clad

Specification:

QQ-A-362

Tolerance 0.00

0.030

Inch)

Forming Corp. RFCd00-1

ROLLED J-SECTION S-559

(Typical All Comers) 920 8’

1 I

j1.250

~0.156R

i i

0.156(Typical)

1.500

Extrusion Die No.: Nlaterial:

2024-T4

Pioneer Aluminum Inc. PA 1373

Specification:

QQ-A-267

or

2024-T3511

or

QQ-A-200/3

EXTRUDED ANGLE S-565

Extrusions and Formed Sections

Figure 1(Sheet 19) EFFECTTVITY:

ALL

51-30-001

Page 23 SRM-´•1

1

Jun 1/95)

Learjet STRUCTURAL REPAIR MANUAL

0.118R

0.118

-((C

0.118

0.010 Inch Radius

on

all

Outside Comers

30.71R

Extrusion Die No.:

Pima\co 11227, Alcoa 153332

Texas Aluminum Co. 19471

Material:

2024-T4

Specification:

QQ-A-267

2024-T3511

or

or

QQ-A-200/3

EXTRUDED TEE S-566

0.094R

CTypical)

f

SharpEdRes

RoundedD.010

0.875

0.0948

LI

f0.094R (Typical) 0.875

Extrusion Die No.:

AND 10133-0702

Material:

2024-T4

Specification:

QQ-A-267

or

Inch

--1

2024-T3511

or

QQ-A-20013

EXTRUDED ANGLE S-568

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 20)

51-30-00

Page 24 SRM-I

Jun 1/95

Leariet

STRUCTURAL REPAIR MANUAL 2598

1

0.016 -0.008

0.138

f~

3 1.181

0.016 -0.008

0.098R f 0.024

900

-/C

10

0.980

0.010 On all outside

Extrusion Die No.: Material:

Specification:

corners

Alcoa 152202

2024-74 or 2024-73511 QQ-A-267 or QQ-A-200/3

EXTRUDED TEE S-569

0.063

C~ypical)

0.750

1

0.0949

IExtrusion Die No.:

AND10133-0601

Material:

2024-74

Specification:

QQ-A-267

or

0.750

f

0.063(7ypirJI)

II~f

2024-73511

or

QQ-A-20013

EXTRUDED TEE 5-571

Extrusions and Formed Sections

Figure 1 (Sheet 21) EFFECTIVITY:

ALL

51-30-001

Page 25 SRM-4

Jun 1/95(

Learjet STRUCTURAL REPAIR MANUAL 0.072

900 f 10

1.000

L

ya

I

1.080

Extrusion Die No.:

Pioneer Aluminum Inc. PA 1036

Material:

2024-T4

Specification:

QQ-A-267

or

i~ It

0.0308

0.125

2024-T3511

or

QQ-A-200/3

EXTRUDED ANGLE S575

0.125R

(Typical 2 Places)

r

Sharp Edges Rounded 0.031

1.250

0.1878

I

0.250

(Typical)

j Extrusion Die No.:

Pioneer Aluminum, Inc. PA4210, Pimalco 10967 or 2024-T3511

Material:

2024-T4

Specification:

QQ-A-267

or

QQ-A-200/3

EXTRUDED ANGLE S-578

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 22)

51-30-00

Page 26 SRM-4

Jun 1/95

~9 Learjet STRUCTURAL REPAIR MANUAL 0.0168 0.875

i

0.047R

f_

I Extrusion Die No.:

Pioneer Aluminum Co. PA5578

I~aterial:

2024-T4

Specification:

QQ-A-267

or

1.000

OS9ilCrypicnD

--I’

2024-T351 1

or

QQ-A-20013

EXTRUDED ANGLE S´•580

896f1O

t-

Break sharp at

comers

0.016R

1.200

0.1208

0.250

I

1.650

I

Extrusion Die No.:

Texas Aluminum Co. T-8557, Alcoa 345282, Pimalco 10967, or Pioneer Aluminum Inc. PA 31516

Material:

2014-T6

Specification:

QQ-A-261

or

2014-T651

or

QQ-A-200/2

EXTRUDED ANGLE S-588

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 23)

51-30-001

Page27 SRM-4

Jun

1/95(

Learjet STRUCTURAL REPAIR MANUAL Break

Sharp Comers

at 0.016R

860 30’ f 1"

jl

0.090

1.100

0.120R

1_ 0.170

1.600

Extrusion Die No.:

Texas Aluminum Co. T-8558, Pimalco 11206, Pioneer Aluminum Inc. PA19925

Material:

2014-T6

Specification:

QQ-A-261

or

or

2014-T6511

or

QQ-A-200/2

EXTRUDED ANGLE S589

Ic

84" 45’ f10

t 1.070

I

0.120R

i

I

1.600

Extrusion Die No.:

Texas Aluminum Co. T-8559, Alcoa 223495, Pimalco 20196, or Pioneer Aluminum Inc. PA19926

Material:

2014-T6

SpecTfication:

QQ-A-261

or

~I

0.140

2014-T651 1

or

QQ-A-200/3

EXTRUDED ANGLE S-590

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 24)

51-30-00

Page 28 SRM-I

Jun 1/95

Learjet I

STRUCTURAL REPAIR MANUAL 0.125

CIj´•pical) BI~eak sharp 0.010R

corners

at

1.000

0.156R

i

0.125R

_E

I 2000

Extrusion Die No.: Material:

AND10134-2001 2014-T6 or 2014-T6511

Specification:

QQ-A-261

or

QQ-A-200/2

EXTRUDED ANGLE S591

II"’"

i

TI

0.120R

1.700

I

at

-I i-

Comers

0.156

Extrusion Die No.:

Pioneer Aluminum Inc. PA11250

Meterlal:

2024-T4

Specification:

QQ-A-267

or

0.030RBreak Sharp

2024-T3511

or

QQ-A-200/3

EXTRUDED TEE S-592

Extrusions and Formed Sections

Figure

EFFECTIVITY:

SRM-4

ALL

1

(Sheet 25)

51-30-00) Page 29 Jun 1/951

Learjet STRUCTURAL REPAIR MANUAL

I

1.600

-I

r

.060R

0.060

(Typical)

1.150 Break

j

at

-II-

sharp corners

O.030R

0.102

Aluminum, inc. PA~544

Extrusion Die No.:

Pioneer

Material:

2024-T3511

Alternate Material 2014-T6511

Specification:

QQ-A-267

Alternate Material

Spec. QQ-A-261

EXTRUDED TEE S596

zooo

I‘

0.094

T 0.0949

CTypical)

1.000 94’ 20’

Break sharp 0.0169

corners

at

-I lcOD94

Material:

Pioneer Aluminum, Inc. PA10728 7075-T651

Specification:

QQ-A-277

Extrusion Die No.:

EXTRUDED TEE S-597

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 26)

51-30-00

Page 30 SRM-I

Tun 1/95

Learjet I

STRUCTURAL REPAIR MANUAL 1.7so

0.090

u

f

-f 0.125R

CTypical)

1.000

9306

0.045R

0.090--(IZ Extrusion Die No.:

Pioneer Aluminum, Inc. PA10642

Material:

7075-T651

Specification:

QQ-A-277

or

or

CTypical 2 Places)

7075-T6511

QQ-A-200/11

EXTRUDED TEE S-598

10 30’ fl"

2.600

0.010R

t

0.;98_L

1.340

Break

Sharp Corners

at 0.016R

I

i

0.100

Extrusion Die No.:

Martin Marietta 50810, Pimalco 20202, or Pioneer Aluminum Inc. PA20088

Material:

2024-T3511

Specification:

QQ-A-267

or

Harvey Aluminum

50810

QQ-A-200/3 EXTRUDED TEE S´•599

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 27)

51-30-001

Page 31 SRM-4

1

Jun 1/95(

Learjet

STRUCTURAL REPAIR MANUAL 0.350 30 fl"

2600

i

0.010R

7 1.390

Break

Sharp Corners

at 0.016R

--IC~.loo Extrusion Die No.:

Martin Marietta 50812, Harvey Aluminum 50812 Pimalco 20203, Pioneer Aluminum Inc. PA19837

or

Material:

2024-T3511

Specification:

.QQ-A-267

or

QQ-A-200/3

EXTRUDED ANGLE S-600

Break

Sharp Corners

at 0.016R

jl

83" 30’

0.940

0.080R

C 0.940(Typical) Extrusion Die No.:

Pioneer Aluminum, Inc. PA 1523 or 7075-T6511

Material:

7075-T651

Specification:

QQ-A-277

or

QQ-A-200/11

EXTRUDED ANGLE S603

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 28)

51-30-00

Page 32 SRM-I

Jun 1/95

Learjet I LearJet

STRUCTURAL REPAIR MANUAL 3.130

------I

0~250

0.1876

Brea~ sharp corners at0.031R

4.130

IC Extrusion Die No.: Material:

Specification:

0´•lm

Pioneer Aluminum, Inc. PA6745; Pimalco 10836 or 2024-T3511 QQ-A-267 or QQ-A-200/3 2024-T4

EXTRUDED TEE S-604

Sharp edRes roun;ded D.OIOR 0.0636

1.000 0.1256 0.063

(Typical)

I---Extrusion Die No.:

AND10134-1204

Material:

2024-T4

Specification:

QQ-A-267

or

1´•´•´•

-----I

2024-T3511

EXTRUDED ANGLE S-606

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 29)

n-~o-oo

I

Page33 SRM´•4

Jun 1/95 1

Learjet ~LearjetJ

STRUCTURAL RE´•PAIR MANUAL

r 1.000 0.156R

BIO~LIC.mBJ

I

~_

Extrusion Die No.:

AND10134-1403

Material:

2024-74

Specification:

QQ-A-267

or

17

2024-73511

EXTRUDED ANGLE S-607

I.oOo

I I

0.’56R

0.125

(Typical)

t-Extrusion Die No.:

AND10134-1601

Material:

2024-74

Specification:

QQ-A-267

or

2024-T3511

EXTRUDED ANGLE S608

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 30)

51-30-00

Page 34 SRM-4

lun 1/95

Learjet I

STRUCTURAL REPAIR ~ANUAL 0.090R

0.125Ji

Extrusion Die No.:

0.600

i

Pioneer Aluminum, Inc. PA 17956 or 2024-T351 1

Material:

2024-T4

Specification:

QQ-A-267

EXTRUDED BAR 5610

f

00946

1.250

0.188R

L

0.125

-f(Typical) 2500

Extrusion Die No.:

Pioneer Aluminum, Inc. PA 4430

Material:

2024-T3511

Specification:

QQ-A-267

EXTRUDED ANGLE S-612

Extrusions and Formed Sections

Figure 1 (Sheet 31)

EFFECTIVITY:

ALL

51-30-00

Page 35 sRM-4

Jun 1/95

Leariet

STRUCTURAL REPAIR MANUAL

0.160

f jL 1.576

1

1.200 f 0.010

1.200 f 0.010

0.120R

r.

0.600R 0.125R

0.500 +0.010 J

L

0´•500

0.009

-0.030

~c- 1.500

IC----- 2.oso---~l Extrusion Die No.:

Alcoa 182732

Material:

2014-T60r-T6511

Specification:

QQ-A-261

EXTRUDED S-613

M0D1FIED OHANNEL

-1,1.

o~w,

I

0.188R

Tli,I I

II~-

oaso~z

I

2750

Extrusion Die No.:

Pioneer Aluminum Inc. PA 1310

Material:

2024-T3511

Specification:

QQ-A-267

fl"’" I

EXTRUDED ANGLE S-614

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 32)

51-30-00

Page 36 SRM-4

Jun 1/95

~Learjet STRUCTURAL REPAIR MANUAL 0.020R

0.043

1.000

0.040

0.580 0.062R

"12~1

_I 0.016R

Extrusion Die No.:

Martin Marietta 51199, Inc. PA20085

Material:

6061-T6

Specification:

QQ-A-270

or

Han/ey Aluminum 51188, Pimalco 20213,

or

Pioneer Aluminum

6061-T6511 or

QQ-A-200/8

EXTRUDED TEE S-621

Extrusions and Formed Sections

Figure EFFECTTVITY:

ALL

1

(Sheet 33)

51-30-00

Page 37 SRM-4

~un 2/95

Learjet STRUCTURAL REPAIR MANUAL Sharp Corners

i

0.118

Rounded 0.016

rn i)

1.181

~0.190R

Extrusion Die No.:

Pimalco 10970, Alcoa 303322,

Material:

2024-T3511

Specification:

QQ-A-267

or

or

Pioneer Aluminum Inc. PA19343

QQ-A-200/3

EXTRUDED ANGLE S622

Sharp Comers Rounded 0.016

1.20 0.190Rti~0.150

r/1~7 1.181

1~

~U

~n lann

950 45’ f 10

0.118

Extrusion Die No.:

Pimalco 10969

Material:

2014-T6511

Specification:

QQ-A-261

EXTRUDED ANGLE S623

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 34)

51-30-00

Page 38 SRM-I

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

ir 0.060R 0.500

_ Extrusion Die No.:

AND101350401

Material:

2024-T3511

Specification:

QQ-A-267

EXTRUDED BULB ANGLE S626

QS401C~k

0.OSO

TB R II

3MxI

II

liUli,

0.125R

(Typical)

I-

I

Extrusion Die No.:

Pioneer Aluminum, Inc. PA 11808

Material:

2024-73511

Specification:

QQ-A-267

0,120

t

EXTENDED WEB CHANNEL S627

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 35)

51-30-001

Page 39 SRM-4

Jun 1/95(

~Learjetl STRUCTURAL REPAIR MANUAL

~i=ri0.1M)

Break sharp

comers

at 0.016R

1.500

0.050

0.060R

(Typical 3 Places)

I-----lsso Extrusion Die No.:

Reynolds

Material:

2014-T6511

Specification:

QQ-A-261

-’t

0.050

Metal Co. 02946, Pimalco 20217, or

or

Alcoa 157005

QQ-A-200/2

EXTRUDED FLANGED TEE 5-630

Sharp edRes rouniied‘CJ.010R

~--o-I (Typical 2 Places)

0.063

0.875

-cl 1(

0.063 0.125R

j

(Typical 2 Places) 0.063 C~ypical)

I- -I 0.750

Extrusion Die No.:

AND10138-0704; Pimalco 50169

Material:

2024-T3511

Specification:

QQ-A-267

EXTRUDED ZEE S633

Extrusions and Formed Sections

Figure 1 (Sheet 36)

EFFECTIVITY:

ALL

51-30-00

Page 40 SRM-4

Tun 1/95

Leariet ~Learjetl

STRUCTURAL REPAIR MANUAL Isoo

i

Sharp comers

roun~ded 0.016R

O~OR

0.094R 1.400

j -)IExtrusion Die No.:

Pioneer Aluminum Inc. PA 6910

Material:

7075T6511

Specificatior:

QQ-A-277

0225

EXTRUDED TEE S-634

0.031R

r_

r,.,,

~040

17

n

Extrusion Die No.:

Pioneer Aluminum, Inc. PA 2822

Material:

2024-T3511

Specification:

QQ-A-267

or

QQ-A-200/3

EXTRUDED BAR S-636

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 37)

51-30-00( Page 41

SRM-4

i

Jun 1/951

STRUCTURAL REPAIR MANUAL

Tn 0.750

II

I_0.125R 1.500

Material:

Pioneer Aluminum, inc. PA5595 2024-T3511

Specification:

QQ-A-267

Extrusion Die No.:

I

0.062

---I7-

EXTRUDED ANGLE S-637

0375

5" 30’

(ReD 0.062R

so 30’ (Ren

(mM)

t’-

i

0.032R

0.010R

-----t0.136

(Maximum)

Extrusion Die No.:

Material:

AZ61 F-F

Specification:

QQ-M-31

EXTRUDED BAR S-639

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 38)

51-30-00

Page 42 SRM-I

Tun 1/95

Leariet

STRUCTURAL REPAIR MANUAL 0.460 0.140 0.020

0.042

CTypical)

CTypical)

f 0.080

0.680 0~034

CTypical)

Full R

18.006 0.040

4.750

Extrusion Die No.:

Alcoa 263215, Pimalco 20223,

Material:

2024-T3511 QQ-A-267 or QQ-A-20013

Specification:

or

Pioneer Aluminum Inc. PA20602

EXTRUDED BAR S-841

8

0.120

’i 0.080

1.970

0.090R

(Typical)

i

0.120

(Typical)

Extrusion Die No.: Material:

Alcoa 181235, Pimalco 20224,

Specification:

QQ-A-261

or

Pioneer Aluminum Inc. PA20959

2014-T6511 or

QQ-A-20012

EXTRUDED I-BEAM S-642

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 39)

51-30-001

Page43 SRM-4

Jun

I

1/95(

~LBarjetJ STRUCTURAL REPAIR MANUAL

T

0.031R

0.625

I

0.062R

t

I

Extrusion Die No.:

Pioneer Aluminum, Inc. PA 4030

Material:

2024-T3511

Specification:

QQ-A-267

0.062

EXTRUDED ANGLE S-644

0.062R

f

0.062

(Typical)

0.750

0.125R

(Typical 2

Places)

0.812

Extrusion Die No.:

Pioneer Aluminum Inc. PA 7539

Material:

2024-T4

Specification:

QQ-A-267

or

2024-T3511

EXTRUDED CHANNEL S-646

Extrusions and Formed Sections

Figure 1 (Sheet 40)

EFFECTIVITY:

ALL

51-30-00

Page 44 SRM-4

lun 1/95

E~ Learjet STRUCTURAL REPAIR MANUAL 0~500

~I

0.130R

f

(ReD

E

I

(SUM) 0~280

1 0.010R

(Maximum)

CTypical) Extrusion Die No.: Material:

AZG1A-F

Specification:

QQ-M61 EXTRUDED BAR S-649

T

0.063R

0.500 0.063R

CExtrusion Die No.:

0.750

Material:

AND10134-0601 2024-T4 or 2024-T3511

Specification:

QQ-A-267

or

L

0.063

QQ-A-200/3

EXTRUDED ANGLE S854

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 41)

51-30-001

Page 45 SRM-4

Jun

1/95(

Learjet STRUCTURAL REPAIR MANUAL OJ00

I

5

0.105R

60 (ReD

-T0310

7

_I

0.145R

O.O1OR(Ma~imum)

CTypicai) Extrusion Die No.:

Material:

AZG1A-F

Specification:

QQ-M-31

EXTRUDED BAR S-657

0.031R

on

All Outside Comers

2.600

I

0.025 f 0.005

~L

0.100R

(Typical)

30.008

Extrusion Die No.:

0.800

-c( C1- 0.100

Material:

Alcoa 217342-A, Pimalco 20235, 2024-T4 or 2024-T3511

Specification:

QQ-A-267

or

0´•100

or

Pioneer Aluminum Inc. PA24766

QQ-A-200/3

EXTRUDED TEE S-681

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 42)

51-30-00

Page 46 SRM-4

Jun 1/95

Learpt I~il STRUCTURAL REPAIR MANUAL Sharp ednes

rrr\r-

rouniied b.OlOR

oSwl I

L Ilc~ei0.063R0.063R

(Typical)

f 0~500

Extrusion Die No.: Material:

AND10133-0401

Specification:

QQ-A-267

2024-74

or

2024-T3511

or

QQ-A-200/3

EXTRUDED ANGLE S-699

t

.m~

0.750

L

I:

0.062R

CTypical)

I

Extrusion Die No.: Material:

2024-T3511

Pioneer Aluminum Inc. PA5540

Specification:

QQ-A-267

or

QQ-A-200/3

EXTRUDED ANGLE S-705

Extrusions and Formed Sections

Fi~ure EFFECT~VITY:

ALL

1

(Sheet 43)

51-30-001

Page47 SRM-4

Jun 1/95

I

Learjet STRUCTURAL REPAIR MANUAL

0.750R

0.15~3

Ef Co-´•o-IT

Extrusion Die No.: Material:

2024-T4

Pimalco 20240

Specification:

QQ-A-267

or

or

Pioneer Aluminum Inc. PA31794

2024-73511

or

QQ-A-200/3 EXTRUDED BAR S-706

Extrusions and Formed Sections

Figure

EFFECTNITY:

ALL

1

(Sheet 44)

51-30-00

Page 48 SRM-4

Jun 1/95

Learjet i STRUCTURAL REPAIR MANUAL 0.025R

0.050

1.500 0.060R

(Typical 2 Places) 0.050R

1_

(Typical 2 Places)

tC--Extrusion Die No.:

---tl

I´•ooo

Material:

Pimalco 20241, Alcoa 236012 2014-76511

Specltication:

QQ-A-200/2

or

0.050

Pioneer Aluminum Inc. PA29028

EXTRUDED TEE S-707 1.073

0.512

0.098R

0.177

I 0.394

0.098ypical) 0.063R~

I

~--0.063R

_r

0.098

7 0.689

Extrusion Die No.: Material:

2024-73511

Speciilcation:

QQ-A-200/3

Reynolds

54260

~JC0.079

EXTRUDED SEAT RAIL S-713

Extrusions and Formed Sections

Figure 1(Sheel 45) EFFECTNITY:

ALL

51-30-00

Page 49 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MAMUAL

z.wo

0.185

U

1

1~ Extrusion Die No.: Material:

Alcoa 250372 6061-0

Specification:

QQ-A-20018

0.093

EXTRUDED BAR S-715

Extrusions and Formed Sections

Figure 1 (Sheet 46) EFFECTIVITY:

ALL

51-30-00

Page 50 SRM-I

Jun 1/95

Learjet Learjet

STRUCTURAL REPAIR MANUAL 60(ReD

i,0.6450.500

1

60(Ref)1 _

0.310

0.470 0.200

0.490

96" (Ref)

---;--$-fi

0.010R (Max)

(Typical)

90"(Ren

i-

0.125

Extrusion Die No.:

Standard

Material:

AZG1A-F

Specification:

QQ-M-31

Magnesium

288

EXTRUDED BAR S-717

t

Sharpedges~

I

mun;ded 0.010R

-~1 I r-

1.000

0.094

0.125R 0.09411

(Typical)

1-

2000T,0.094

1.000

Extrusion Die No.: Material:

AND10136-2002

Specification:

QQ-A-200/3

(Typical)

2024-T3511

EXTRUDED TEE S-727

Extrusions and Formed Sections

Figure

EFFECTIVITY:

sRM-4

ALL

1

(Sheei 47)

51-30-00

1

Page 51 1 Jun 1/95)

Learjet

STRUCTURAL REPAIR MANUAL -I~- CTypical)

0.082 f 0.004

0.016R

on

all

outsidecomers

f 1~320 ~0.012

CTypical) 0.120R

(Typical)

I

I------ -´•~´•1´•1-----( Extrusion Die Na.:

Material:

Pioneer Aluminum PA 27155 2014-76511

Specification:

QQ-A-200/2

EXTRUDED CHANNEL S-728

Break

sharp comers 0.016R

100 f 0.010

0.080

0.030R

CTypical) 0.030R

CTypical 2 Places)

0375

CTypical)

1.188 f 0.010

0.188R

(Typical

(Typicai 2 Places)

1.135

1.135

0.125R

CTypical 4 Places)

3 Places)

1,90" (Typical)

0.080

0’010 -0.005 C

f 0.010 r--- 3.766 (At base only)

Extrusion Die No.:

Pimalco 11245, Texas Aluminum

Material:

2024-73511

Specification:

QQ-A-200/3

Company

T-17884

EXTRUDED CHANNEL S-729

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 48)

51-30-00

Page 52 SRM-4

Jun 1/95

Leariet ~Learjet

STRUCTURAL REPAIR MANUAL

1.6u,

Bruak

0.010

LI

-(MD5

I

sharp comers 0.016R

rOMO

900 0.800

0.010 -0.005

1.060 f 0.010

~le

0~070

Extrusion Die No.:

Alcoa 276155, Pimalco 20259, Texas Aluminum Co. T-17885, or Pioneer Aluminum Inc. PA29135

Material:

2024-73511

Specification:

QeA-200/3

EXTRUDED TEE S-731

r

1.500

0.010 -0.005

90"

II

Illr0.060 71

~0.120R

0.940 f 0.010

0.720

i_l

0.010-0.005

I_

Extrusion Die No.:

Texas Aluminum Co. T-17886

Material:

2024-73511

Specification:

QQ-A-200/3

or

Pimalco 11406

EXTRUDED TEE S732

Extrusions and Formed Sections

Figure

EFFECTNITY:

SRM-4

ALL

1

(Sheet 49)

51-30-00( Page 53 Jun 1/951

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL Odl~R

(Typical

2

Places)

0.031R(Typical

4

Places)

1.000

11

0.094R

t

(Typical 2 Places)

-~1 ~e 0.062

Extrusion Die No.:

PA 6104 Pioneer Aluminum, Inc.

Material:

2024-73511

Specification:

QQ-A-200/3

EXTRUDED TEE S-733

0.016R on all outside corners

I‘

1

Fa080

´•in ’t 0.156R

I I

1.000

U

1

I~alu

Extrusion Die No.:

Pimalco 11228

Material:

2014-T6511

Specification:

QQ-A-200/2

or

Texas Aluminum Co. T-18430

EXTRUDED TEE S-734

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 50)

51-30-00

Page SRM-4

54

Jun 1/95

Learjet I

STRUCTURAL REPAIR MANUAL

-rl ~-0a94cT,icas

0.094R

t

~I

(TYPical)

1.000

0.125R

CT

1.

2.000

Extrusion Die No.:

AND10137-2004

Material:

2024-T3511

Specification:

QQ-A-200/3

tl‘:

0.010R

(Typical)

EXTRUDED CHANNEL S1735

0.225R

(Typical)

1~

0.125R 1.000

(Typical)

0.010R

(Typical) -I

Extrusion Die No.:

AND10137-1113

Meteriei:

2024-73511

Specitrcation:

QQ-A-200/3

EXTRUDED CHANNEL S-736

Extrusions and Formed Sections

Figure 1 (Sheet 51) EFFECTIVITY:

ALL

51-30-001

Page 55 SRM-4

Jun

1/951

Learjet

STRUCTURAL REPAIR MANUAL

i" Y 1.493

ri

0.125R

C

0.130

0.0318 (5 Places)

j 79"

(Typical) Extrusion Die No.:

Aicoa 71223

Material:

2024-T351 1

Specification:

QQ-A-200/3

EXTRUDED ANGLE S-738

r1.200

Break sharp comers at 0.016R

´•I´• 0.3a3

0.740

J

0.023 (Ref)

I-

0.1208

CTypical)

0.180

86" 30’ fl

Extrusion Die No.: Material:

Aicoa 349252, Pimaloo 20265, 2024-T4 or 2024-T3511

Specification:

QQ-A-200/3

or

Pioneer Aluminum Inc. PA31720

EXTRUDED TEE S-739

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 52)

51-30-00

Page 56 SRM-4

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL

r cj~ 27oo1.050

0.740

j-

Break s~arp

corners

at OD16R

~1

0.1U0R

(Typical)

0.280

940+1

Extrusion Die No.: Material:

Alcoa 349242, Pimalco 20266, 2024-74 or 2024-73511

Speoitioation:

QQ-A-200/3

or

Pioneer Aluminum Inc. PA31721

EXTRUDED TEE S-740

830

0.750

0.125R

t

t 0.062 CTypical) Extrusion Die No.:

Pioneer

Material:

2024-73511

Specifioatron:

QQ-A-200/3

Aluminum, Inc. PA1509

EXTRUDED ANGLE S-744

Extrusions and Formed Sections

Figure 1 (Sheet 53) EFFECTIVITY:

ALL

51-30-001

Page 57 SRM-4

Jun

1

1/95(

Learjet ~arjet

STRUCTURAL REPAIR MANUAL 0.016R On

lametxElA

Corners 83"

r 0.620

0.090R

1

I

0.062

ic~-Extrusion Die No.:

Alcoa 377162

Material:

2024-T3511

Specification:

QQ-A-200/3

or

0.6U)

(Typical)

0.062 X 450 Chamfer

Pioneer Aluminum Inc. PA31251

EXTRUDED ANGLE S745 0~016R

on

all oubide comers

0.025450 0.0908

r

0.090R

0.625

1

I

’0.0168

0.070

0.025R

0.0908’

Extrusion Die No.:

C~---- 0.700

---I

0.063

Alcoa 353302

Material:

2024-T3511

Specification:

QeA-200/3

EXTRUDED STRINGER SPLICE S-748

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1

(Sheet 54)

51-30-00

Page 58 SRM-4

Tun 1/95

Learjet

STRUCTURAL REPAIR MANUAL 2aoa

:I

j

0.350

I

840 50’ f 10

Extrusion Die No.:

Pioneer Aluminum Inc. PA32173

Material:

2024-T3511

Specitlcation:

QQ-A-200/3

0.125R

(Typical) 1.700

0.188~1

EXTRUDED TEE S-759 0.016R On All Outside Corners

0.188

r

890 25’ f 10

1.900 0.125R

(Typical)

0.200

1476~1 Extrusion Die No.:

Pioneer Aluminum Inc. PA32176

Material:

7075-73511

Specification:

QQ-A-200/11

Z.98

.I

EXTRUDED TEE S762

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 55)

51-30-00

Page 59 SRM-4

Jun 1/95

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL 4.500 3.000

---cl

1

r

0.310f 0.012

--L~I ´•t´•

0.125R

1.550

(Typical)

_L 0.188

850 45’ f 10

´•-cl

Extrusion Die No.:

Pioneer Aluminum Inc. PA32177

Material:

7075-T3511

Specification:

QQ-A-200/11

EXTRUDED TEE 5765

jt

2.360

0.340

0.190R

(Typical)

i2.0 0

93" 30’

1"

-tl

Extrusion Die No.:

Pioneer Aluminum Inc. PA32180

Material:

7075-T3511

Specification:

QQ-A-200111

EXTRUDED TEE ST15

Extrusions and Formed Sections

Figure

EFFECTNITY:

ALL

1

(Sheet 56)

51-30-00

Page 60 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

0.190R

(Typical);r 2.200

I

940 15’ f 10

~e Extrusion Die No.:

Pioneer Aluminum Inc. PA32181

Material:

7075-T3511

Specification:

QQ-A-200/11

0.080

EXTRUDED TEE S-n6

T

0.190R(Typical)

1 I

1.600

900 40’ f 1"

o.loo

Extrusion Die No.:

Alcoa 32182

Material:

7075-T3511

Specification:

QQ-A-200/11

EXTRUDED TEE S-777

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1 (Sheet 57)

51-30-00

Page 61 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL o.oso

1 1.600

_I

JahORiiypii~U

00~

2.700

Extrusion Die No.:

Pioneer Aluminum Inc. PA32183

Material:

7075-T3511

Specification:

QQ-A-200/11

EXTRUDED TEE s-ns

i-´•--I

f 0.900

(Typical)

0.120R

0.170

1’

(Typical)

0.180(Typical)

tl

I

Extrusion Die No.:

N/A

Material:

7075-T3511

Specification:

QQ-A-200/11 EXTRUDED HAT SECTION S-783

Extrusions and Formed Sections

Figure

EFFECTIVITY:

ALL

1 (Sheet 58)

51-30-00

Page 62 SRM-4

Tun 1/95

Learjet

STRUCTURAL REPAIR MANUAL 0.031R

C

SYM

r 0.750

0.125R

900f 10

I:0.062

0.062R

J 1.500

Extrusion Die No.: Material:

AND10136-1401

Specification:

QQ-A-267

Sharp Comer

2024-T3511

EXTRUDED TEE S-787

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 59)

51-30-00

Page 63 sRM-a

Jun 1/95

STRUCTURAL REPAIR MANUAL

r 0.750

I 1~0.75o--tl Extrusion Die No.:

Pioneer Aluminum Inc. PA4026

Material:

2024-T3511

Specification:

QQ-A-200/3

or

Pimalco 50087

or

Tiernay 60-3754

EXTRUDED ANGLE S-5001

rn II 0.125R

1- 1.450-I Extrusion Die No.:

Martin Marietta 69359

Material:

2024-’13511

Specification:

QQ-A-267

or

0.157

(Typical)

QQ-A-200/3

EXTRUDED ANGLE S-5017

Extrusions and Formed Sections

Figure 1 (Sheet 60)

EFFECTIVITY:

ALL

51-30-00

Page SRM-4

64

Jun 3/95

Learjet

STRUCTURAL REPAIR MANUAL 0.340

2.360

0.190R

(Typical)

2.000

L

920 30’ It 30’

0.125-~ Extrusion Die No.:

N/A

Material:

7075T73511

Specification:

QQ-A-200111

EXTRUDED TEE S-5022

0.030R

t

Breaksharpedp" (Typical)

0.112

i

\i

I- -´•0.1660332 Extrusion Die No.:

Pioneer Aluminum Inc. PA33576

Material:

6061-T6511

Specitication:

QQ-A-200/8 (for 6061)

or

I

6063-T6 or

QQ-A-200/9 (for 6063)

EXTRUDED SHAPE S-5075

Extrusions and Formed Sections

Figure EFFECTIVITY:

ALL

1

(Sheet 61)

51-30-00

Page 65 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

0.160 3.160

I

Full R

0.190R

i

(Typical)

L

1500

Extrusion Die No.:

Pioneer Aluminum Inc. PA33573, Alcoa 373892

Material:

6061-T6511

Specification:

QQ-A-200/8

0.100

EXTRUDED TEE S5078

1 2.000

0.125R 0.125R

ii t,,,.125

Extrusion Die No.:

AND10136-2407

Material:

2024-T3511

Specification:

QQ-A-200/3

EXTRUDED TEE 8-5088

Extrusions and Formed Sections

Figure 1 (Sheet 62)

EFFECTNITY:

ALL

51-30-00

Page 66 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

1 I-0.238

Break all

ednes

sharp

comers

Om6R

r‘1.190

0.098R

0318

85" 20’

Extrusion Die No.:

Alcoa 389282

Material:

7050-T3511

Specification:

AMS 4341

1.120

t

-I

EXTRUDED ANGLE S-5091

0.004

Break all sharp edges 0.031R maximum

0.005 -0~000 1300

1.000

0.500

t -71+ 0.028_

0.017

+0.008 0.000

0.1000.012 0.000

0.100R

0.800f0.007

30.000R(ReO

~11-o.1mtaM6 SYM Extrusion Die No.: Material:

Alcoa 390672

Specification:

QQ-A-267

2024-T3511 or

QQ-A-200/3

EXTRUDED TEE S-5093

Extrusions and Formed Sections

Figure 1 (Sheet 63)

EFFECTIVITY:

ALL

51-30-00

Page 67 SRM-4

Jun 1/95

Leariet Learjet

STRUCTURAL REPAIR MANUAL METAL PARTS

i.

REPAIR AND PROTECTION

HEATTREATMENT OFALUMINUMALLOY A.

is required for the fabrication of some aluminum parts used on the Leajet. These prorequired to give the parts the physical characteristics they need for the situations to which they are applied. These characteristics include, but are not limited to, strength and malleability. Heat treating processes include annealing, solution heat treating, and aging. Aluminum alloy parts shall be heat treated per AMS2770. Heat

treating

cesses are

B.

C. 2.

HEATTREATMENTOF STEELALLOYS A.

Steel

alloys shall be heat treated per MIL-H-6875.

EFFECTIVITY: srzM-4

ALL

51-30-01

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL SEALING METAL 1.

STRUCTURAL REPAIR

DESCRIPTION A.

Sealing

of the aircraft is

required

to eliminate

leakage

of air pressure,

liquids, dust,

and heat

through

the airframe structure. B.

This section on

2.

and the

provides sealing procedures

equipment

necessary for

performing

maintenance

the aircraft.

TOOLSAND

EQUIPMENT

following materials have been found interchanged.

A.

The

B.

Sealant

to be the most efficient in their

PART NUMBER

NAME

applications and must not be

MANUFACTURER

USE

SEALANTS Class A

Sealant

Products Research Chemical

Corp.

Pay and hole sealing

5430 San Fernando Rd P.O. Box 1800

Glendale, CA 91209 Sealant

Sealant

Pro-Seal 890

Products Research

(MIL-S-8802) Class B-1/2

Chemical

Corp.

Fillet, injection, fay, and hole sealing within

Class B-2

1/2-, 2-,

Class B-4

hour work life

or

4-

Pro-Seal 890

Products Research

Pay sealing

(MIL-S8802)

Chemical

Class C-24

within 24-, 48-, or 80-hour

Class C-48

squeeze-out life

Corp.

Class C-80

Sealant

Pro-Seal 890

Products Research

(MIL-S8802)

Chemical

Corp.

Sealing in wet fuel areas only

SOLVENTS

Methyl Ethyl Ketone (MEK)

1T-M-261

Commercially available

Toluene, Type Ii

TT-N-95

Commercially available

Aliphatic Naptha, Type II

TT-N-95

Commercially available

EFFECTIVITY:

ALL

51-30-02

Page SRM-4

1

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL NAME

PART NUMBER

MANUFACTURER

USE

TOOLS

Sealant Removal and

(See Figure 1.)

Fabricated

locally

(See Figure 1.)

Fabricated

locally

Stiff Bristle Brushes

(Not nylon)

Commercially available

Solvent

(Polyethylene squirt bottle)

Commercially available

Cutting Tools Sealant

Fairing Tools

Dispensers

Sealant Gun

Semco No. 250

Polyethylene Nozzles

(For Sealant Gun)

Polyethylene Cartridges

(For Sealant Gun) MATERIALS

Lint-Free Clean

White Cotton Cloth

Vinyl Plastic Tape

CT-93 (0.010"

x

1")

:Borden Chemical

Company

Lint-Free White

Cotton Gloves

Commercially available

Masking Tape

Commercially available Rezolin 8300

Parting Agent

or

832A

Rezolin, Hexcel

Clean Gauze

Division of

Corp.

Commercially available

Lubricant

Shell L-73101 Mobil

3.

a

or

Commerically available

Jet 35

PREPARATION OF FAYING SURFACES PRIOR TO SEALING A.

Cleaning (1) Clean existing aluminum alloy parts and repair parts in accordance with 51-30-04. (2) Immediately prior to applying sealant clean metal surfaces with 1,1,1, trichloroethane (MIL-T81533) or methyl ethyl ketone (MEK). Apply solvent with a damp cloth and wipe dry with a lintfree, clean, white, cotton cloth.

EFFECTIVITY: SRM-4

ALL

51-30-02

Page 2 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

glnches

Approx.

(LARGESEALANT

BeveledSharp

CUTI1NG TOOLS)

Edge bInches

Approx.

Surface

t

1_\

6-Indhes

Sharp Edge (SEALANT FAIRING TOOL)

Approx.

6-Inches Beveled

(LARGE SEALANT CUTIING TOOLS)

Approx.

Surface

(SMALL SEALANT

Sharp Edge

FAIRING TOOL WITH SPOON TYPE HEAD) O.O´•lO-Inch

Approx.

6-Inches

Approx.

bInches

Approx. 0.050-Inch

Approx. (LARGE SEALANT

IZ

(SEALANT REMOVAL TOOL)

FAIRING TOOLS)

eInches

Approx. NOTE:

Beveled Surface

(SMALL SEALANT CUT~ING TOOL)

NOTE:

These tools may be made of l/~-lnch diameter bronze or s~teel welding rod and mav be plated to improve smoothness.

Sharpe Edge

These tools should be made of hardwood to reduce the possibilih´• of shuctural damage.

Repro

EFFECTIVITY:

Sealant

ALL

Cutting and Fairing Tools Figure 1 51-30-02

Page 3 sRM-a

Jun 1/95

STRUCTURAL REPAIR MANUAL WARNING:

SPECIAL PRECAUTIONS SHOULD BE OBSERVED DURING CLEANING. SOLVENTS ARE TOXIC AND FLAMMABLE. FRESH AIR MASKS AND/OR ADEQUATE VENTILATION SHOULD BE AVAILABLE IN ALL CLOSED AREAS. CLEANING

NOTE:

Never pour

or spray cleaning solvent on aircraft structure. If this is done, the solmay run back between structure layers, then after cleaning is completed, solvent may creep back out and contaminate previously cleaned surface.

vent

Use

lint-free, clean, white,

cotton cloth to

ensure

that

no

dye residue is left on treat-

ed surfaces.

(3) Thoroughly scrub the

area

to be sealed. Extreme care shall be exercised to clean inaccessible

cor-

ners, gaps, etc. A small

paint brush or pipe cleaners may be used for these areas. Always clean an area larger than that required for the sealant. (4) Before solvent has evaporated, wipe area dry with a lint-free, clean, white, cotton cloth. (5) Repeat steps (3) and (4) until no discoloration is evident on the drying cloth. If

NOTE:

primer is removed during cleaning, the exposed metal surface need not be furprovided the cleaning is accomplished per steps (3), (4), and (5). However, if primer is completely removed, reprime surface after completion of all sealing. some

ther treated

(6) After surfaces

gloves 4.

The

(1) (2) (3) (4)

6.

are

thoroughly cleaned, personnel should wear lint-free, clean, white, applying sealant.

cotton

prevent surface contamination while

TYPES AND CLASSES USED FOR SEALING A.

5.

to

following is a list of metal bonding uses, and required Fay seal with Class A, Class 8, or Class C sealant.

sealants.

Fillet seal with Class B sealant.

Injection seal

with Class B sealant.

Hole fill with Class A

SEALING

or

machine-mixed Class B sealant.

REQUIREMENTS

A.

Metals finished with epoxy tion.

B.

C.

Fay sealed joints must be closed and securely fastened before work life expiration. Threaded fasteners which have been shank or underhead sealed shall not be retorqued tion of application time.

D.

~oints shall

primers

shall have

aged

a

minimum of 48 hours

prior

to sealant

applica-

after

expira-

not be flexed until sealant is tack-free.

SEALING APPLICATIONFOR STRUCTURALREPAIRS A.

Mix sealant in accordance with the manufacturer’s instructions, or refer to Learjet Maintenance Manual for mixing, handling, and application.

Chapter 20

in the

applica-

ble

I

B.

Apply sealant to cleanedareas.

C.

Install all fasteners within work life of the sealant.

D.

Allow sealant to

E.

cure. Cure times may be accelerated by heat application. Fillet seals may be applied to all edges of repaired and original parts. Fair-in sealant with tool so a continuous smooth fillet is formed.

EFFECTIVITY:

ALL

a

fairing

51-30-02

Page 4 SRM4

Jun1/95

Learjet

STRUCTURAL REPAIR MANUAL 7.

METHOD OFAPPLICATION A.

Sealant material may be applied with a brush, an extrusion gun, or a spatula. Each method works best in a particular situation. The following paragraphs describe these methods and the situations in which

(1)

they are used.

A stiff-bristled brush (not

nylon)

is used to

apply

the precoat of Class A sealant. Sealant shall be

onto the surface and into the joint which is to be sealed.

brushed

thoroughly faying surface, and pre-pack seals may be applied with an extrusion gun. Injection seals must be applied with an extrusion gun. The extrusion gun uses air pressure to force the sealant material through a nozzle onto the surface or into the cavity to be sealed. Nozzles are available in different sized beads of extruded sealant. The nozzle tips may be shaped locally to produce a bead of sealant with the shape and dimensions to fit a specific job. Pre-pack seals are used to fill voids in structure which cannot be reached by the injection method. These voids are packed with sealant before they are closed by the assembly of the structure. (3) A spatula is used to spread sealant material for faying surface and pre-pack seals. Small repair fiE let seals may be applied with a spatula if an extrusion gun is not available.

(2) Fillet,

8.

FILLET SEALING A.

Repair Fillet Seal (See Figure 2.) (1) Use sealant cutting tools similar to those shown in Figure 1. (2) Cut faulty section from fillet. Slope cuts at ends of section so new sealant tions of old fillet in these areas. Avoid abrupt changes in cross section. NOTE:

Remove

rial is

enough sealant on both sides

of defective

area

to be

will

sure

lap remaining

that

por-

remaining mate-

satisfactory.

cut surfaces. Remove loose cuts or flaps. Make sure that no faulty sealant remains. If fillet adhesion is good, it is not necessary to cut sealant down to bare metal. (4) Refinish damaged surface if necessary. (5) Clean surface to be sealed.

(3) Examine all

NOTE:

If epoxy finish is removed in the fuel area during cleaning operation, it is permissible directly over the bare metal. Touch up exposed areas after the sealant has been

to seal

applied. (6) B.

Apply new fillet seal.

Repairing FilletSealed Fasteners (1) Leaking fastener fillet seals are repaired by replacing the faulty sealant. Proceed as follows: (a) Using a sealant cutting tool; cut around seal at base of fastener to separate sealant from structure.

(b) Grasp seal with pliers, and pull up and away from fastener end. Most of seal should be

by this process. (c) Cut away remaining sealant with cutting tool. Small ly to fastener need not be removed.

re-

moved

NOTE:

quantities

of sealant which adhere firm-

Tightening fasteners during or after sealing destroys sealant effectiveness.

(d) Clean fastener and surrounding area with cleaning solvent. (e) Using an extrusion gun or spatula, apply a coat of Class B sealant around and over fastener. (f) Work sealant with fairing tool until fillet seal dimensions given in Figure 2 are obtained.

(g) EFFECTIVITY:

Use extreme

ALL

care

to eliminate any visible voids

or

bubble

areas

around the fastener base.

51-30-02

Page 5 sRM-a

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL Force Sealant ahead of gun

Q

Cut

Away

Fillet Bead

~s C

C O C

Outlirr

C´•´•´• i~

(FILLET SEAL REMOVAL)

(APPLICATION OF FIRST FILLET)

Remove trapped air from faired’fillet

Cut nozzle material to fit size of fillet

6

by brushing. Press fillet into seam

o \t, a

9

firmly

d

u

C

6

G

d

a

FairingTool -~C7

3

u

(APPLICATION OF FINAL SEALANT)

(PRESSINC FIRST FILLET INTO SEAM)

Repro

EFFECTIVITY:

Fillet

Sealing Figure 2 (Sheet 1 of 2) ALL

51-30-02

Page 6 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

Fillet Reentrant

R~entrant

Edge

Edge

Fillet

(RE-ENTRANT FILLET)

b r 0.125Inch Maximum

b

0.126 to 0.349-Inch

1

b

0.350" Minimun

1

w

rl

\-r

-II

[L~lil

w

0.150-Inch ~d Minimun

d 0.150-Inch Minimun

d 0.150-Inch Minimun

(VIEW A)

(VIEW C)

(VIEW B)

(FILLET DIMENSIONS)

For View A 0.250" to 0.500" w

For View B and C 0.350" to 0.500"

w

a

b

b

0.150-inch minimum, 0 when b and c 0.350" or more.

except a

i

b

w,

0.35

except a

0 when

or more

-I~ t

b

d

~t

t Gap must be filled, not bridged

-L1C 14-

(BUTT JOINT FILLER DIMENSIONS)

Sealing Figure 2 (Sheet 2 of 2) Fillet

Repro

EFFECTIVITY:

ALL

51-30-02

Page 7 sRM-a

Jun 1/95

Learjet I

STRUCTURAL REPAIR MANUAL C.

ApplyNewFilletSeal (SeeFigure2.) (1) Prior to fillet sealing, all fasteners in the area to be sealed must be installed. All bolts must be torqued to their respective values as retorquing is not permitted after sealing. The proper nozzle for the sealing gun must also be used. If a small fillet is to be applied, use a small nozzle; a large fillet requires a large nozzle. (2) With extrusion gun, apply a small fillet of Class B sealant as shown in Figure 2. (3) When a nozzle tip is used, point it into the seam and maintain nearly perpendicular to the line of travel. SEALANT MUST BE APPLIED CAREFULLY TO AVOID TRAPPING AIR IN

CAUTION:

FILLET. OPERATE GUN SO THAT A BEAD OF SEALANT IS CONTINUALLY

FORCED AHEAD OF NOZZLE TIP, IN THE DIRECTION OF NOZZLE TRAVEL.

(4) Using

a

fillet

fairing tool,

press the first fillet

firmly into position as

shown. Work the entire bead-

ed section. CAUTION:

CHECK THAT THE FAIRING TOOL IS ABSOLUTELY CLEAN. DO NOT USE SOLUTION OR LUBRICANT TO MAKE TOOL SLIDE SMOOTHLY OVER THE SEALANT. WIPE THE TOOL WITH CLEAN GAUZE

FREQUENTLY TO

AID IN THE FAIRING OPERATION.

(5) If the first fillet has cured but is

not

clean, then it

must be cleaned before the

application

of the

shown. A

larger

second fillet.

(6) Apply the second application of Class

B sealant to

produce

a

full-bodied fillet

as

extruded nozzle head is used, make cuts in nozzle to fit fillet and make it conform to the dimensions given in Figure 2. If extruded nozzle will be

required

than

head nozzle is not used, fillet dimensions.

I

was

use a

used for the first fillet. If

fairing

tool

as

required

an

to make sealant conform to the full-bodied

Keep the sealing gun nozzle in direct contact with the work to prevent inclusion of air bubbles between fillets. Do not hurry. Good sealant application requires patience as

NOTE:

as proper technique. If a fillet extrusion firmly against the part in such a position that be directly over the edge.

well

head is used, the head shall be pressed the maximum thickness of the fillet will

(7) Work out any evident air bubbles. (8) Fillet re-entrant edges are not acceptable. (9) A typical finished fillet seal with dimensions is shown in Figure 2. 9.

INJECTION A.

SEALING

Repair Injection Seal (1) Remove sealant from short injection channels with

a

hooked wire and small

require disassembly of structure. injection (2) Clean injection channel all the way through, since trapped

cutting tools. Longer

channels

air will

prevent complete filling

of the

channel with sealant.

(3) Exercise care so that structure is not damaged during the removal process. (4) Clean channel with cleaning solvent and pipe cleaners.

EFFECTIVITY:

ALL

51-30-02

Page8 SRM-C

Jun 1/95

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL (5) Apply solvent with saturated pipe cleaner until

drying

at least

(6) Clean channel

brush.

Wipe

surface

dry

with

pipe

cleaner.

Repeat

once more

after visible evidence of

impurities

has been removed and the

to be clean.

thought injection seal. Apply New Injection Seal (See Figure 3.) (1) To apply a new injection seal; a fairing tool, pipe cleaners, and an extrusion gun with an injection nozzle attachedare required. (2) Ensure that channel is thoroughly cleaned. (3) Inject channel full, from one end only, with Class B sealant until sealant emerges from all other openings. Completely fill joggles and channels that require continuity of seal, or block off seal. surfaces

(7) Apply

B.

or

cleaner remains clean.

are

new

ENSURE GUN HAS ENOUGH SEALANT TO MAKE COMPLETE SEAL AT STOPPING AND STARTING ONE INJECTION WITHOUT ANY BREAK.

CAUTION:

WILL CAUSE AIR BUBBLES IN SEAL AND IS CAUSE FOR

REJECTION

OF

JOB. (4) Remove excess sealant with fairing tool and smooth out ends of seal. (5) Inspect finished job, checking for poor adhesion and air bubbles. Any air bubble is

jecting

a

seal. Rework

(6) Check that the

area

only

area

cause

for

re-

that has bubbles.

protrudes, into the fillet seal area, has no abrupt changes in gradually into the area that is to be fillet sealed.

where the sealant

section. Sealant must be faired out 10. FAYING SURFACE SEALING

A.

Repair Faying Surface Seal (See Figure 4.) (1) Disassemble structure surrounding seal. (2) Remove all sealant from faying surfaces with sealant cutting tools and suitable plastic scrapers. (3) Refinish damaged surface. (4) Clean faying surfaces with cleaning solvent. (5) Apply a coat of Class B sealant to one faying surface with a roller, an extrusion gun, or a spatula. Spread the sealant over the entire surface to obtain a uniform coating. (6) Removable seals shall be applied with the use of a parting agent. The parting agent shall be applied to one surface. Paint shall be omitted from this surface. When the parting agent is dry to the touch, the parts may be assembled with a faying surface seal. If the part is removed, the sealant shall be removed, new parting agent applied, and resealed. NOTE:

LigMning Strike and Leak Preventive Seal Application wing fuel access covers, refer to Chapter 57.

For to

on

removable seals

applied

(7) Assemble parts within sealant work life. (8) Fair out extruded sealant to leave a smooth fillet along joint. NOTE:

joint

EFFECTIVITY:

SRM-4

ALL

applied to ensure a continuous assembly of the faying surfaces.

Sufficient sealant must be

after

extrusion

on

both sides of the

51-30-02

Page 9 Jun1/95

Learjet I

STRUCTURAL REPAIR MANUAL

Injection Sealing Figure 3

Page

10

Jun 1/95

Learjet Leariet

STRUCTURAL REPAIR MANUAL

Sealant Sealant

(ASSEMBLED)

(BEFORE ASSEMBLY) (PERMANENT SEAL)

Sealant

Thin coat oi

parting agent

(A SSEMBLED)

(BEFORE ASSEMBLY) (REMOVAL SEAL)

Faying Surface Sealing Figure 4

Repro

EFFECTIVITY:

ALL

51-30-02

Page SRM-4

11

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL 11. PRE-PACK SEALING

A.

Failed

pre-pack

and

faying

surface seals

normally repaired by raising the seal plane to isolate the option, surrounding the faulty seal can be disassembled, a new seal applied, and the structure reassembled. To replace a failed pre-pack seal, proceed as follows: (1) Disassemble structure surrounding seal. (2) Remove all sealant from pre-packed cavity with sealant cutting tools and suitable plastic scrapfailed seal from fuel. As

are

the structure

an

ers.

I

(3) Complete all preassembly operations such as hole drilling and deburring. Use Shell L-73101 or Mobil Jet 35, or equivalent lubricants for preassembly drilling or deburring operations. (4) Clean parts with cleaning solvent. (5) Apply a coat of Type B sealant to one of the parts. Shape sealant with a fairing tool to the general contours of the

cavity.

Sufficient sealant must be

NOTE:

applied

to

ensure

complete filling of the cavity.

(6) Assemble parts within sealant work life. 12. HOLE SEALING

A.

SealToolingand CoordinationHoles (1) Plug tool and coordination holes with soft rivets. (2) Clean area to be sealed. (3) Apply Type A sealant over rivet and/or head. Sealant may also be applied

brushing

in two directions until

a

coating

to structure.

Apply by

of 0.005- to O.Oli-inch thickness is obtained.

13. FASTENER SEALING

A.

Seal

Nutplates, Nuts, Bolts, and Rivets as follows: (See Figure 5.) (1) Clean fastener and area around fastener. (2) Using an extrusion gun or spatula, apply Type B sealant around fastener. When sealing

plates,

ensure

that

attaching

rivets

are

nut-

sealed.

(3) Work sealant with a fairing tool to obtain fillet seal dimensions shown. (4) Use extreme care to eliminate any visible voids or bubble areas around base of fastener.

EFFECTIVITY:

ALL

51-30-02

Page 12 SRM-4

Tun1/95

Learjet I

STRUCTURAL REPAIR MANUAL

0.005 to 0.015-Inch

0.060-inch 0.060-Inch

Rivet

(DOME TYPE NUTPLATE)

(RIVET)

0.060-Inch

_L I~i

\T 0.060-Inch

0.060-Inch

(NUT GND THREAD)

Repro

EFFECTNITY:

SRM-4

(BOLT HEAD)

Sealing Figure 5

Fastener

ALL

51-30-02

Page 13 Tun1/95

Learjet Ledliet STRUCTURAL REPAIR MANUAL STRUCTURAL IDENTIFICATION

CKARTS AND TABLES i.

CHARTSAND TABLES A.

Chartsand Tables Charts and tables that

parts are presented (1) (2) (3) (4) (5) (6) B.

as

provide

the necessary data to

Minimum Bend Radii Chart

Figure Figure 2

Bend Allowance Chart Setback Chart

accomplish

the

layout

and fabrication of

repair

follows:

Figure

1

3

Equivalents Figure 4 Circumference Table Figure 5 Shop Mathematics Figure 6 Special Tools Locally manufactured special tools, and/or methods and procedures, are shown in Figures 7 through 10. The special tools/procedures provide methods of reducing the head size of flush rivets, picking and using drilled up the location of blind or hidden fastener holes, locating hidden skin trim lines, countersunk holes. in for fillers out heads of flush fasteners dimpled or Drill Sizes and Decimal

EFFECTIVITY:

ALL

51-30-03

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ALUMINUM THICKNESS

20240

0.016

1/32

0.020

1/32

0.025

1116

2024-74

5052-0

5052-Hs4

60614

8061-74

6061-76

70750

7075-T6

1116

1/8 118

1/32

1116

1116

118

1/16 1/32

1/16

1/32

1116

1/32

71780

7178-76

1116

1/8

1H6

1/8

1/16

1/8

111

SHEET

0.040

1/16

3/32

1116

1/18

6

3/32

3/16

3/32

7/32

0.051

1116

1/8

1116

3/32

1/16

1/16

3/32

3/32

114

1/8

9/32

0.~4

3/32

5/32

1116

3/32

1118

3/32

1/8

3/32

5/16

1/8

11/32

0.091

1/8

9/32

13/32

3/16

6

112 1

0.188

11/32

0.250

2T1

1/4

5/32

7/32

9/32

3/4

15/32

17/32 13/16

1-1/8

19/32

1-3116

6T*

3-1/2T*

6-1/2T*

PLATE 5T*

1-1/2Tt

2T1

2-1/2TI

3T*

STEEL CARBON STEEL

4137. 4340 AND 8630

THICKNESS 0.012

1/32

1118

0.016

1/32

1116

1116

3/32

1/32

1/16

1132

1116

1132

1116

0.035

1/16

1/8

0.036

1/16

1/8

0.018

0.020

0.024 0.025 0.030

1116

3/32

1H6

3/32

1/8

3/16

0.032 1/16

118

0.040 1 0.045 0.048

1/16

118 3/32

0.049

1/8 3/16

0.060

SHEET

1116

118

0.063 0.065

0.072 0.075

3/32

3/32

1/8

1/8

3/16

1/8

3/16

3/16

1/4

31t6

114

1/8

3/16

5/32

114

Y16

3/8

3/32

7132

7116

118

1/4

1/2

1/8

5/8

5/32

1/4

3/8

3/4

3/16

9/32

1-1/2T*

2T’

Y16

0.078

0.080 0.083 0.093 0.095 0.

1/8

1/4

1/8

114

Y32

0.112

0.119 0.120

3/16

0.125 0.134

3/16

114

318

0~56

1/4

3/8

0.188

5/16

3/8

0.250

PLATE

3/8

1

Y16

3/8

OVER 0.250

YT

3/8

1-1/2T"

material thickness (round off bend radius

to next

2T*

I-lnT*

5T*

largest 1/32.)

Minimum Bend Radii Chart

Figure EFFFCTIVITY:

ALL

1 (Sheet 1 of 2)

51-30-03

Page 202 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL CRES, INCONEL,

AND TITANIUM PURE

ALLOY

AISI-302 AIS1321 AiS1347

AIS1302

350

INCONEL

IksDL

IgDL

AMS0901

AM54908

17=7PH

INCONEL X

19-9DX

I9-9DX

NAS7123

NAS7125

1RHARD

THICKNESS

9~

90"

0.010

1/32

1118

0.012

1132

1/32

1/32

1/16

0.016

1/32

1/32

1M2

1/18

0.020

1132

1116

1/16

3/32

1116

1/32

1118

1/16

1118

0.025

1/32

1118

1/16

3/32

1/16

1132

1116

1HB

Y32

118

Y32

5/32

1/16

0.018

1/16

0.028 0.030

1132

1116

1118

3/32

1/16

1/32

1/16

3/32

1/8

5/32

0.036

1118

1/8

1/8

3/16

3/32

1116

3/32

3/32

1/8

5/32

0.040

1/16

1/8

1/8

3/16

3/32

1116

3/32

1/8

1/8

3/16

1118

1/6

5/32

3/16

1118

1/8

5/32

7/32

Y16

1/4

Y16

9/32

1/4

3/8

0.032 0.035

0.042 0.045

3/18

0.048 0.049 0.050

1/8

3/16

1/8

1116

1/8

1/8

0.056 0.060 0.063

1/16

1/8

1/8

3/18

1/8

1116

118

5/32

0.065 0.071

SHEET

0.072 0.075

0.078 0.080

3/32

3/18

3/16

5/16

3/16

3/32

1/4

9/32

9r32

13/32

3/32

3/16

3/16

5/16

3/16

3/32

9/32

5/16

Y16

15/32

3/8

1/2

0083

0.090 0.093 0.095 0.100 0.104 0.109

0.112

1/8

1/4

114

3/8

1/4

1/8

318

13/32

13/32

9/16

1/8

1114

1/4

3/8

1/4

118

318

7/16

7/16

5/8

1/2

23/32

0.119 0.120 0.125

0.140

0.156 0.180 0.180 0.188

3/16

3/8

3/8

3/16

9/16

11/16

13/32

3/18

5/8

11/16

1/2

1/2

1/4

3/4

7/8

2T’

2r

lr

0.190

PLATE

0.250

1/4

2r

9/16

13/16

21132

29/32

OVER 0.250

T

material thickness (round off bend radius to next

largest 1/32.)

Minimum Bend Radii Chart

Figure EFEECTIVITY:

ALL

f

(Sheet 2 of 2)

51-30-03

Page 203 SRM~

May 15/92

Learjet STRU~TURAL REPAIR MANUAL empirical formula for finding the allowance

The

for

material

required

(0.0078

thickness).

This

x

a

bend

radius)

of

i.

Multiply the numbers in the

table

by the degrees

of bend to determine the amount of material

x

required for the bend. Example:

the material

equals

(0.01743

x

required

for

one

degree

of

95

deg bend, 1/8

0.00249

bend. 2. Mold Lines

Degree

x

For bends

calculated

as

which is taken

Bend Lines

Example: 90 deg bend, (R)

the

are

one

required of

1 in.

of the material.

radius, 0.064 in. material.

Radius to center of material

x

1

Rx

Circumference of are

BEND ALLOWANCE COEFFICIENTS FOR ALUMINUM

bend radius ~1 in.) 0.032

1.032 in.

degreeof bend

360 (total

(T)

inch radius, the for the bend is

circle, the radius of

a

to the center

1/2 material thickness

Thicltness

O.aQO in, material

radius,

than

larger

amount of material

of Bend

Radius

in,

0.2365 in.

95

degrees in circle)

ALLOYS, BASED ON ONE-DEGREE ANGLE

METAL THICKNESS RADII

0.018

0.020

0.022

0.025

0.092

0.040

0.0~0

0.063

0.080

OAgO

0.125

0.180

1132

0.00067

9.90976

O.MX)72

0.00074

O.MX)79

0.00086

0.00094

0.00104

0.00117

0.00125

O.M)154

0.00200

1H6

0.00121

0.00125

0.001 26

9.99129

0.00135

0.00140

0.00149

0.00159

0.00171

O.M)180

0.00209

0.00255

3/32

0.00176

0.00179

0.00180

0.00183

9.90188

0.00195

0.00203

0.00213

0.00226

0.00234

0.00263

0.00309

1/8

0.00230

0.96234

0.00235

0.99238

0.90243

0.00249

0.00258

0.99268

0.00281

9.96289

0.00317

0.00364

5/32

0.00285

0.99288

0.00290

0.00292

0.96297

0.00304

0.00312

0.00322

0.99335

0.90343

9.99372

O.M)418

3/16

0.00339

0.00342

0.00344

0.a0347

0.00352

0.M)358

0.00387

0.00377

0.00390

0.00398

0.00426

0.00473

7/32

0.00394

0.00397

0.00398

0.00401

0.004108

O.W412

0.00421

0.00431

0.00444

0.00452

9.99481

0.00527

1/4

0.00448

0.0045~

0.00454

0.00458

a.00461

0.00467

0.00476

9.99486

0.00499

0.00507

0.00535

0.00582

9/32

0.00503

9.96506

0.00507

0.00510

0.00515

0.00521

0.00530

0.00540

0.96553

0.00561

0.00580

0.00636

5/16

0.00557

0.00560

0.99562

0.00564

9.99579

0.00578

0.00584

0.00595

0.00608

OX~0816

0.M)644

0.00691

11132

0.00612

0.00615

9.80616

0.00619

0.00624

0.00630

9.96639

0.00649

0.00662

0.00670

0.00699

0.00745

3/8

0.00666

0.00869

0.00671

0.00673

0.00679

0.00685

0.00693

O.M)7W

O.W717

0.00725

0.00753

0.00800

13/32

0.00721

0.00724

0.00725

0.M)728

0.00733

0.00739

0.00748

0.00758

0.00771

0.96779

8.90898

0.00854

7/16

0.00775

o.oons

9.90783

o.oo7eg

0.00787

0.00794

0.00802

0.00812

0.00826

0.99834

0.00862

0.00908

15/32

6.99829

0.00833

0.00834

0.00837

6.80842

0.00848

0.00857

0.00867

0.00880

0.00888

0.00917

0.00963

112

0.00884

0.00887

0.00889

0.69891

0.M)896

0.00903

0.00911

0.00921

0.00935

0.00943

0.00971

0.01017

17/32

0.00938

0.M)942

0.00443

9.86016

0.00951

0.00957

0.00966

0.00976

0.00989

O.M)997

0.01925

0.01072

9/16

0.00993

0.00996

0.00998

0.01000

0.01095

0.01012

0.01020

0.01030

0.01043

0.0~051

0.0108D

0.01126

19/32

0.01047

0.01051

0.01052

0.01055

0.010M)

0.01065

0.01073

0.01083

0.01098

0.01105

0.01133

0.01179

518

0.0\\02

0.01~05

0.0~\07

0.01\09

0.01~14

0.01121

0.01129

O.Dt139

0.01152

0.01160

9.91189

0.01235

21132

0.01158

0.01160

0.01161

0.01164

0.01170

0.01175

0.01183

0.01193

0.01207

0.a1214

0.01245

0.01289

11116

0.01211

0.01214

0.01216

0.01218

0.01223

0.01230

0.01238

0.01248

0.01261

0.01269

0.01298

0.01344

23/31

0.01265

0.01268

0.01269

0.01273

0.01276

0.01283

0.01291

0.01301

0.01316

0.01322

0.01351

0.01397

3/4

0.01320

0.01323

0.01324

0.01327

0.01332

0.01338

0.01347

0.01357

0.01370

0.01378

0.01407

0.01453

25/32

0.01374

0.01378

0.01379

0.01381

0.01386

0.01392

0.01401

0.01411

0.01425

0.01432

0.01461

0.01507

13/16

0.01429

0.01432

0.01433

0.01436

0.01441

0.01447

0.01456

0.01466

0.01479

0.01487

0.01516

0.01562

27/32

0.01483

0.01488

0.01487

OA1490

0.01494

0.01501

0.01509

0.01519

0.01534

0.01 510

0.01569

0.01615

7/8

0.01538

0.015H

0.01542

0.01545

0.01 550

0.01556

0.01565

0.01575

0.01588

0.01 596

0.01625

0.01671

29/32

0.01592

0.01595

0.01596

0.0159g

0.01804

0.01610

0.01619

0.01629

0.01643

0.01650

0.01679

0.01 727

15H6

0.01848

0.01850

0.01651

0.01654

0.01859

0.01885

0.01674

0.01684

0.01697

0.01705

0.01734

0.01780

31/32

0.01701

0.01704

0.01705

0.01708

0.01712

0.01718

0.01727

0.01737

0.01752

0.01758

0.01787

0.01833

1

0.01755

0.01759

0.01760

0.01763

0.01768

0.01774

0.01783

0.01793

0.01806

0.01814

0.01843

0.01888

Bend Allowance Chart

Figure 2 EFFECTIVITY:

ALL

51-30-03

Page 204

May15/92

Learjet STRUCTURAL REPAIR MANUAL Example:

Angle of bend ~A)

r

deg

Radius (R)= 0.125 in. K from table 2.7475 SETBACK

a’

_t L,-

1-

140

Material thickness (T)= 0.064 in.

K

2.7475

x

(0.064

2.7475

x

0.189

SETBACK

(T

x

R)=

0.125)= 0.509

0.509 in.

r

SETIICK

ANGLE

ANGLE

ANGLE

ANGLE

ANGLE

ANGLE

DEGREE

K

DEGREE

K

DEGREE

K.

DEGREE

K

DEGREE

K

DEGREE

1

0.00873

31

0.27732

61

0.58905

91

1.0176

121

1.7675

151

3.8667

K

2

0.01745

32

0.28874

82

0.60086

92

1.0355

122

1.8040

152

4.0108

3

0.02618

33

0.29621

83

0.61208

93

1.0538

123

1.8418

153

4.1653

4

0.03493

31

0.30573

64

0.62487

94

1.0724

124

1.8807

154

4.3315

5

0.04368

35

0.31530

65

0.63707

95

1.0913

125

1.9210

155

4.5107

6

0.05241

36

0.’32492

86

0.&1941

96

1.1106

126

1.9626

156

4.7046

7

0.06116

37

0.33459

67

0.66188

97

1.1303

127

2.0057

157

4.9151

B

0.06993

38

0.34433

68

0.87451

08

1.1504

128

2.0503

158

5.1455

9

0.07870

39

0.35412

89

0.88728

99

1.1708

129

2.0965

159

5.3995

10

0.08749

40

0.36397

70

0.70021

100

1.1917

130

2.1445

160

5.6713

11

0.09629

41

0.37388

71

0.71329

101

1.2131

131

2.1943

161

5.9758

12

0.10510

42

0.38386

72

0.72654

102

1.2349

132

2.2460

162

6.3137

13

0.11393

43

0.39391

73

0.73996

103

1.2572

133

2.2998

163

6.6911

14

0.12278

44

0.40403

74

0.75355

104

1.2799

134

2.3558

164

7.1154

15

0.13165

45

0.41481

75

0.76733

105

1.3032

135

2.4142

165

7.5957

16

0.14051

46

0.42447

76

0.78128

106

1.3270

136

2.4751

166

8.1443

17

0.14945

47

0.43481

77

0.79543

107

1.3514

137

2.5386

167

8.7769

18

0.15838

48

0.44523

78

0.80978

108

1.3764

138

2.8051

168

19

0.16731

49

0.45573

79

0.82434

109

1.4019

139

2.6746

169

10.385

20

0.17633

50

0.46631

80

0.83910

110

1.4281

140

2.7475

170

11.430

21

0.18534

51

0.47697

81

0.85408

111

1.4550

141

2.8239

171

12.706

22

0.19438

52

0.48773

82

0.86929

112

1.4826

142

2.9042

172

14.301

23

0.20345

53

0.49858

83

0.88472

113

1.5108

143

2.9887

173

16.350

24

0.21256

54

0.50952

84

0.90040

114

1.5399

144

3.0777

174

19.081

25

0.22169

55

0.52057

85

0.91633

115

1.5897

145

3.1718

175

22.904

26

0.23087

56

0.53171

86

0.93251

116

1.6003

148

3.2708

176

26.636

27

0.24008

57

0.54295

87

0.94896

117

1.6318

147

3.3759

177

38.188

28

0.24933

59

0.55431

88

0.96569

118

1.6643

148

3.4874

178

57.290

29

0.25862

59

0.56577

89

0.98270

119

1.8977

149

3.6059

179

114.590

30

0.28795

80

0.57735

90

1.00000

120

1.7320

150

3.7320

180

INFINITE

9.5144

Setback Chart

FigureJ EFFECTIVITY: swc4

ALL

51-30-03

Page 205 May 15/92

Learjet E~ Learjet]

STRUCTURAL REPAIR MANUAL DECIMAL EaU\VALENTS

TAP DRILLSIZES I

NC

I

SCREW

I

TAP

SCREW

1

u

7/16-14

TAP

NUMBER, LETTER, AND FRACTIONAL SIZE DRILLS

I

I

I

1

1

SIZE DRILL

I

SIZE

I

DECIMAL

I

DRILL

I

I

I

SIZE DRILL

I DECIMAL

I

DECIMAL

DRILL

7/16-20

25/64

1/2-20

29/64

27/64

1/2-13

I

SIZE

DRILL

SIZE

I

NF

9/16-12

31/64

9/16-18

33/64

5/8-11

17/32

5/8-18

37/64

11/16-11

19/32

1

5/8

11/16-11

1

79

0.0145

1

30

0.1285

1

Q

1/M

0.0156

1

29

0.1360

1

R

0.3390

78

0.0160

1

28

0.1405

1

11/32

0.3437

n

omeo

1

9164

S

0.3480

76

O.OMO

1

27

0.1440

1

T

0.3580

75

O.M10

1

26

0.1470

1

23/64

0.3580

1

0.\406

0.3320

3/4-10

21/32

1

3/4-16

11/16

1

1

74

o.om

1

25

0.1495

1

U

13/16-10

23/32

1

7/8-14

13/16

1

1

73

0.0240

1

24

0.15X)

1

318

7/8- 9

49/64

1

1-14

15/16

1

1

72

0.0250

1

23

0.1540

1

V

0.3770

15/16- 9

53/64

1-1/8-12

1-3/64

71

0.0260

1

632

0.1562

1

W

0.3860

7/8

1-14/-12

1-11/64

1-112-12

1-27/64

1- 8

1

1-1/8- 7

1

63/64

1-1/4- 7

1-7/64

1-1/2- 6

1-11/32

MACHINE SCREW SCREW

DRILLS FOR

I

SIZE

0.3680

1

9.8759

70

0.0280

f

22

0.1570

1

25154

0.3906

89

0.029~

1

21

0.1590

f

X

0.3970

88

0.0310

20

0.16~0

1/32

0.0313

19

0.1660

1

1

Y

0.4040

13/32

9.4989

67

0.0320

1

18

0.1695

1

Z

0.4130

68

0.0330

1

11/64

0.1719

1

27/64

0.4219

65

0.0350

1

17

0.1730

1

7/16

0.4375

64

0.0360

1

16

0.1770

1

89/54

0.4531

M

0.0370

1

15

0.1800

1

15/32

0.4687

82

0.0380

1

14

9.1889

1

31/64

61

0.0390

1

13

0.1850

1

112

1

1

0.4843

1

9.5009

No.50

No. 43

1

No. 47

No. 40

1

se

0.0410

1

12

o.lseo

1

17/32

1

No.43

No. 32

1

I

58

9.9499

I

11

0.1910

1

35/64

6-32

1

No.36

No. 28

1

1

57

0.0430

1

10

0.1935

1

9116

8-32

1

No.ZS

No. 19

1

1

56

0´•0465

1

9

0.1960

1

37/64

0.5781

10-24

1

No. 25

No. 10

3/64

0.0489

1

8

0.1990

1

19/92

0.5937

1

No.21

No. 10

55

0.0520

1

0.2010

1

39/64

0.6094

10-32

54

0.0550

1

0.203~

1

518

0.8259

7/32

0.6406

2-56

1

3-48 4-40

12-24

1

No.16

1/4-20

1

No.

7

1/4

1/4-28

1

No.

3

114

5/16-18

1

F

5/16-24

1

I

3/8-16

1

5/16

3/8-24

DIAMETER

1

1

PIPE I

7 1Y64

I

0.5469

1

0.5625

53

0.0595

1

6

0.2040

1

41~4

1/18

0.0625

1

5

9.9955

1

21/32

9.8589

1

52

0.0635

1

4

0.2090

1

43/64

0.6719

5/16

51

9.9879

1

3

0.2130

1

11/16

0.8875

5/16

50

0.0799

1

1/32

0.2187

1

45/&1

0.7031

49

0.0730

1

2

0.2210

1

23612

0.7187

48

0.0760

1

1

0.2280

1

47/64

9.7314

5/64

0.0781

1

A

0.2340

1

3/4

0.7500

47

0.0785

1

15/64

0.2344

1

49164

0.7656

46

0.OB10

I

B

O.nBO

1

25/32

0.7812

1

3/8

1

I

1

45

0.0820

1

C

0.2429

1

51164

0.7969

I

1

44

0.0860

1

D

0.2480

1

13/16

0.8125

CLEARANCE I

1

43

9.9890

1

114

9.2599

1

5384

0.8281

1

1

42

0.0815

1

F

0.2570

1

27/32

0.8437

3/32

0.0837

1

G

0.2610

1

55/64

0.8594

41

0.0960

1

17/64

0.2656

1

7/8

0.8750

40

0.0980

I

H

39

0.0995

1

I

DRILLS FOR

OF TAP

I

TAp

1/8-27

1

11/32

7/16

I

1

0.5312

I

318

Q

I

1/4-18

1

7/16

7/16

3/8-18

1

37/64

314

1/2-14

1

23/32

7/8

1

1

1

57164

1

57/64

0.8906

0.2720

1

29/32

0.9062

3/4-14

1

59/64

1-3/16

1

1

38

0.1015

f

J

0.2770

1

59/64

0.9219

1-11-1/2

1

1-5/32

1-7/16

1

1

37

0.0140

1

K

0.2811

1

15118

0.9375

1-1/4-11-1/2

1

1-1/2

1-3/4

1

1

38

0.0165

1

9132

0.2812

1

8~164

0.9531

1-1/2-11-1/2

1

1-47/64

2

I

7/54

0.1093

1

L

9.2999

1

31/32

0.9687

1

2-7/32

2-112

35

0.1100

1

M

0.2950

1

89/84

0.9844

34

0.1110

1

19/84

0.2968

1

1

1.M)O

33

0.1130

1

N

0.3020

32

0.1160

1

615

9.3125

31

0.1200

1

O

0.3160

I

p

0.3230

2-112-8

1

2-5/8

3

3-8

1

3-114

3-3/4

3-1/2-8

1

3-314

4-1/4

1

1

4-8

1

4-1/4

4-3/4

1

I

Drill Sizes and Decimal

I

1

Equivalents

Figure 4 EFFECTNITY: sI~M-a

ALL

51-30-03

Page 206 May 15/92

Learjet STRUCTURAL REPAIR MANUAL INCHESORFEET

OFONEINCH DIAMETER FRACTION

I

DECIYAL

1/64

0.015625

AREA

I

0.04909

0.00019

1

1

3.1416

0.7854

64

1

201.06

3216.99

CIRCUM.

1

I

DIA.

I

CIACUIM.

I

AREA

I

CIRCUM.

DIA.

I

AREA

1/32

0.03125

0.09818

0.00077

1

2

6.2832

3.1416

65

1

204.20

3318.31

3/64

0.046876

0.14726

0.00173

1

3

9.4248

7.0686

68

1

207.35

3421.19

1116

0.0625

0.19635

O.M)306

1

4

12.5864

12.5664

67

1

210.49

3525.85

5/64

0.078125

0.24545

0.00479

1

5

15.7080

19.635

68

1

213.63

3631.88

3/32

0.09375

0.99452

0.00690

1

8

18.850

28.274

69

1

218.77

3739.28

7/64

0.109375

0.34383

0.00939

1

7

21.991

1

38.485

70

1

219.91

3848.45

50.266

71

1

63.617

72

1

0.125

0.38270

0.01227

1

8

25.133

9/64

0.140625

944161

0.01553

1

9

28.274

5/32

1/8

1

223.05

3958.19

228.19

4071.50

229.34

4185.39

232.48

4300.84

0.15625

0.49087

0.01917

1

10

31.418

78.540

73

11~64

0.171875

0.53999

0.02320

1

11

34.558

95.033

74

3/18

0.1875

0.58905

0.02761

1

12

37.699

113.1

75

235.62

4417.88

13/84

0.203125

0.63817

0.03241

1

13

40.&11

132.73

78

238.78

4538.48

7/32

0.21875

0.68722

0.03758

1

14

43.982

153.64

77

241.90

4656.63

15/64

0.234375

0.73635

O.M314

1

15

47.124

176.71

78

245.04

4778.36

0.25

0.78540

0.04909

1

18

50.265

201.08

79

248.19

4901 .67

17/64

0.265625

0.83453

0.05542

1

17

53.407

226.98

80

251.33

5026.55

9/32

0.28125

0.88357

0.06213

1

18

56.549

254.47

B1

254.47

5153.

19/64

0.296875

0.93271

0.06822

1

19

59.690

283.53

82

257.81

5281.02

0.3125

O.gS175

0.07670

1

20

62.832

314.18

83

260.75

5410.81

0.328125

1.0309

0.08456

1

21

85.873

348.38

84

283.89

5541.77

11/32

0.34375

1.0789

0.09281

1

n

ss.l 15

380.13

85

267.04

5674.50

23/64

0.359375

1.1291

0.10144

f

23

72.287

415.48

86

270.18

5808.80

0.375

1.1781

0.11045

f

24

75.398

452.39

87

273.32

5944.68

25/84

0.390825

1.2273

0.11984

1

25

78.540

490.87

B8

276.46

8082.12

13/32

0.40625

1.2763

0.12962

1

26

81.681

530.93

89

279.60

8221.14

27/64

0.421875

1.3254

0.1397g

1

27

84.823

572.58

80

282.74

6361.73

0.4375

1.3744

0.15033

1

28

87.985

815.75

1

91

285.88

65W.8B

0.453125

1.4236

0.16126

1

29

91.106

660.52

1

82

289.03

6647.81

15/32

0.46875

1.4728

0.17257

1

30

94.248

706.88

1

93

292.17

6792.91

31/64

0.4&1375

1.5219

0.18427

1

31

97.389

754.77

94

295.31

6939.78

0.5

1.5708

0.19635

1

32

100.53

8W.25

95

298.45

7088.22

33/64

0.515625

~.6199

0.20880

1

33

108.67

855.30

86

301.59

7288.29

17/32

0.53125

1.8890

0.22166

1

34

106.81

907.92

97

304.73

7389.81

35/64

0.546875

1.7181

0.23489

1

35

109.96

98

307.88

7542.96

0.5825

1.7871

0.24850

1

36

113.10

1017.88

99

311.02

7897.69

0.678125

1.8163

0.28248

1

37

118.24

1075.95

1M)

314.16

7853.98

1134.11

101

317.30

8011.85

1184.59

102

320.44

8171.28

103

323.58

8332.29

1/4

5/16

3/8

7/16

29/64

In

9/16 37/84 19/32

1

1

0.27688

1.8653

0.59375

1

38

1

1

1

0.30680

i 1

40

2.0127

0.32232

1

41

128.81

1320.25

104

326.73

8491.87

0.65625

2.0617

0.33824

1

42

131.95

13B5.M

105

329.87

8659.01

43/64

0.671875

21108

0.35453

1

43

135.09

1452.20

108

1

333.01

8824.73

11/18

0.6875

2.1598

0.37122

1

44

138.23

1520.53

107

1

338.15

8992.02

45/&0

0.703125

2.2090

0.38828

1

45

141.37

1590.43

108

339.29

9160.88

23/32

0.71875

2.2580

0.40574

1

48

144.51

1661.90

109

342.43

47/64

0.734375

2.3072

0.42356

1

47

147.65

1734.94

110

345.58

0.75

2.3562

0.44179

1

48

150.80

1809.56

111

348.72

49/64

0.765625

24054

0.46038

1

49

153.94

1885.74

112

351.88

9852.03

25/32

0.78125

24561

0.47937

1

50

157.08

1963.M)

113

355.00

10028.75

51/64

0.796875

2.5036

0.49872

1

51

180.22

2042.82

114

358.14

10207.03

13/16

0.8125

25525

0.51848

1

52

163.36

2123.72

115

381.28

10386.89

53/64

0.828125

2.6017

0.53862

1

53

166.50

2208.18

116

364.42

10568.32

27/32

0.84375

2.6507

0.55914

1

54

169.65

2290.22

117

367.57

10751.32

55/64

0.859375

2.6999

0.58003

1

55

172.79

2375.83

llS

3M.71

10935.88

0.875

2.7489

0.60132

1

175.93

2463.01

119

373.85

1112.02

57164

0.880625

27981

0.62298

1

57

179.07

2551.76

120

376.99

11309.73

29132

0.90625

28471

0.64504

1

58

182.21

2642.08

121

380.13

11499.01

59/64

0.921875

2.8959

0.66748

1

59

185.35

2733.97

122

383.27

11689.87

15/16

0.9375

2.9452

0.69029

1

60

188.60

2827.43

123

386.42

11882.29

61164

0.953125

29945

0.71349

1

61

191.64

2922.07

124

389.58

3102

0.06875

3.0434

0.73708

1

62

194.78

3019.07

125

392.70

63/&1

0.984375

3.0928

0.76097

1

63

197.92

3117.25

126

395.84

0.609375

1.8145

0.29164

0.625

1.9635

41/84

0.640625

21/32

39/64 5/8

3/4

7/8

1

1

Diameter

multiplied by

39

1 1

119.38

1

1

1P.52 125.68

1

1258.64

equals circumference. Circumference multiplred by Square of the diameter multiplied by 0.7854 equals area.

3.1416

1

0.3183

1

9331.32

1

9503.32 9878.89

12076.28 1

12271.85

12468.98

equals diameter.

Circumference Table

Figures EFFECTIVITY:

ALL

51-30-03

Page 207 SRM´•L

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL SPHERE 4

r

4 Tr

VOLUME

Ir

3

AREA

CONE

d3

nr3

VOLUME

AREA OF

SURFACE

1

r2 :Xd2

AREA

I

L

nr2L

~r2h

3

CYLINDER

VOLUME

(OF EITHER)

6

O.7854D2L

d

(OF

n DL

~ZTrs

a3

DIAGONAL

CYLINDRZCAL

CONE)

CUBE VOL UME

I

RIGHT

d

E

a

J-;-

6a2

TOTAL AREA

a

RECTANGULAR PRISM CYLINDER VOLUME AREA OF

SURFACE

(area base)

I

h

h:

CYLINDRICAL

(perimeter base)

f´•--j-i-

h

VOLUME

I I

(area of end)

DIAGONAL

d

TOTAL AREA

CONVERSION OF DECIMAL FRACTION TO

C

abe

2(ab

ca)

be

CONVERSION OF FRACTION TO DECIMAL

COMMON FRACTION To convert fraction to decimal To convert decimal to

common

fraction

Divide numerator

(top) by denominator (bottom)

Multiply the denomminator (bottom) of fraction desired

Bxamp~:

0.678 (decimal fraction)

5/8

8~2:

5/8

0.625

48

64 (denominator desired)

20

2712

16

4068

40

43.392

Result: 43

40

64

0

Shop Mathematics Figure 6 (Sheet 1 of 2) EFFECTTVITY: SRM~I

ALL

51-30-03

Page 208 May 15/92

Learjet STRUCTURAL REPAIR MANUAL 8

TRAPEZOID

(a parallel

b)

to

I

AREA

bh

Ih h

AREA

\lbZ+

A

2 is

RECTANGLE

/1

a+b

h

C

a

perpendicular

to

a

b

h2

b

D

and b

RIGHT

TRIANGLE

8

ba AREA

CIRCLE nd

CIRCUMFERENCE

a

AREA=~Tr

2n

circumference

(n=

HYPOTENUSE:

A

1F

qd2

b/

C

b

A.*B.+C’.1BOdegrees

I/\B d

=0.7854d2

diameter

n=

ANY TRIANGLE

3.1416

bh ELLIPSE AREA:

AREA=

C

~(DA)x(OC) n (AB) x (CD)

2

I_C-’l_~

B

is

AO

perpendicular BO

C"

180

~o

h;

b)

A

C

b

degrees

I PARALLELOGRAN

SECTOR

AREA

l(h

r(arcAB)

(opposite

1

2 IT~

r2(angleA08)

360

degrees

B

parallel)

C

AREA= bh

(h

0

sides

AO

is

perpendicular BO

FUNCTIONS OF ANGLES

CO

360

SINE

to

b)

A

b

D

degrees

Side

Opposite

Hypotenuse TANGENT

SIDE

HYPOTENUSE

SECANT

SideOpposite Side Adjacent =Hypotenuse

OPPOS I IE

COSINE

iSIDE

ANGLE

Side

Adjacent

Side

Adjacent

Hypotenuse COTANGENT

Side

ADJACENT

COSECANT

ediStncajAOpposite

Hypotenuse Side

Opposite

Shop Mathematics Figure 6 (Sheet 2 of 2) EFFECTIVITY: SRM4

ALL

51-30-03

Page 209 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Dimple

or

countersunk

Dimple

to

filled

be

install

filler,

flush

heat-treated

Select

drill

Drill

through

same

diameter

rivet. as

rivet.

Typical application

head.

Filling Dimpled

ad Countersunk Holes

Couotersink to match

existing fastener. Steel

block ill

where a dimpled or countersunk hole has become enlarged, and it is not

In

case

possible next

to

size

countersink for the

redimple larger fastener, or

the

size

Aedrill size

larger

fastener.

fastener before

Drill size

2.

a

as

hole in the

a

steel block the

Fastener

existing

so

size fastener head is flush

Redrill hole to next size

larger fastener

trimming.

after

that

with the surface of the steel block. 3.

trimming.

same

existing fastener.

CounteISillk the drilled hole the

existing

Q

Q

method may be used to trim the next size larger fastener head to match the existing

1.

match

fastener.

match next

to

following

dimples or countersinks.

to

of

Note This method to be used the next

larger

only

for

fastener.

diameter. 4.

Place the fastener to be used in the countersunk hole in the steel block, and file or grind off head flush with

5.

the surface of the block. Install the fastener to be used in redrilled holes. ~ter installation, coat

o

head of fastener with epoxy primer, and paint to match surrounding area. ~C

Tr’

ring

j

Fastener Heals

Trimming Fastener Heads and Filling Countersunk Holes Figure 7 EFFECTIVITY: SRM-4

ALL

51-30-03

Page 210 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL NOTES:

fastening operations on covers and doors, secure part firmly in place before trimming. Use radius gage or disk to duplicate radius. Radius

First

Perform all

of

Edge

~ICCLCOCC

Opening

Tape (Ref)

Second

and

(Refer

Note)

to

i

(Ref)

OO

Y

CDL16U

t

Tape (Ref)

Oversize Filler

gC,

c

I

oi:

Edge

of Cutout

I

I,

o

c

E

CCi

e

cc

c

go

II

o

i~

c c

cc

c

Repair or

Doubler

Door Frame

c~

c~

Place second

tape

cover,

over

matching

it

accurately

with

outer

edges of

first

tape.

Oversize

filler

Trace trim line

material

placed

inside outer

over

taped

cutout.

(second) tape.

WITH MASKING TAPE

NOTES: Trim out

area.

Cut filler

over-

cutout, and insert skin scribe. Hold filler firmly in place,

j

------~f

r-

damaged

size. Place filler

over

and slide scribe around cutout. o

This trim

marking method is not recomfitting covers and doors.

mended for

1/2 Skin Scribe

ribe Line

T

Oversize Filler

Spacer

Any Alloy Steel

(Approx. or

0.040

in.)

Scribe

(Ref)

Hacksaw Blade

I WITH SKIN 9CRIBE

Locating Skin Trim Lines Figure 8

EFFECTIVITY: SRM-4

ALL

51-30-03

Page 211 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL 5/8 (Approx.) 30

No.

Peen Probe Stem

0.050

Material Steel

40 Drill

No.

Spacer -0.050 (or as required)

(Approx.)

Heat-Treated

or

Bu:7

Probe SCREW LOCATOR This variation of

Aluminum Alloy

Either be

member

may

formed to clear

obstructions

~1

the

sizes,

such

J(;-;---==jSweat or

as

\LAS required mid-panel

or

far

holes

screw

doors

of

holes in

and

covers.

50

No.

Solder

Stake

finder may be

hole

locating larger

undrilled structural

as

HOLES

various

Peen

necessary.

LOCAIIH; BLIH)

for

used

or

1

40

or

Bushing

3j8

o

Sweat Solder

Flush--\

Drill

Drill Bushing

1/8 Rivet

1/$

i-

edge

holes

I/iii

WITH HME

Probe

CAHLOC STUD LOCATOR NOTE:

shapes of

The

hole

the

only examples.

Other

finders

shown

configurations

are

This variation of the hole

will

required for accomplishing many jobs. The main points to keep in mind when

be

making

hole

a

drill be To

finder

snugly

fit

must

in

the

probe

and

:2)

transfer

bushing accurately

or

accomplish

the

should be

(1)

hole,

are

the

centered

punch

over

latter,

the

the

series) When

the

and

hole must

probe.

in undrilled

is

shown

in

assembly

a

center

of

rivet.

selected distance

on

line

1

With

from

to

figure

of blank a

set

the Camloc 10

is

covers

of stud

locating locator

recommended.

repair sheet in place, align

scale

along

line;

then

of rivet. e

sheet. tance.

To locate center, insert AD rivet

uncovered

project

portion of

line

onto

repair

Carefully mark chosen disCenter-punch and drill hole.

in hole.

g~

~ETHOO Draw two

MTHOD

lines

intersecting center

expected,

(4002

and doors.

covers

frequent fitting doors

finder may be

studs

line-drilled.

through

centerline

2

Camloc

)ETHOD

Draw line Mark

locating

tools similar

METHOD

1

for

used

2

at

of rivet,

Install

repair

scale

sheet.

Accurately

portion along project lines onto repair sheet. Center-punch at drill pilot hole. and intersection, align

uncovered

of lines and LOCATING BLIND HOLES IILTH A SCALE

TW0 MTHODS

Locating Blind Holes Figure 9

EFFECTIVITY: SRM-4

ALL

51-30-03

Page 212 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

NOTE: This

type and

doors tool

Camloc

of

when

recommended

covers

receptacle

under

1-1/4

the door

Camloc

each

in

cover

or

T

A locator

expected.

is

installed

be

can

is

locator

stud

regular replacement of

8

being

11 1/4

I

__i__\

fitted. r~-lc.nol

LDrill 1/2-CSK

Fabricate all parts from 0.050-inch

1

2024-74

7075-16 clad material.

or

5/32

2

Cut

3

Joggle loner (collar-retaining) strip. Align and clamp strips and 0.050-inch spacer in drill vise, and insert a

4

sheet-metal

strips

and spacers.

Rig

140

Rivet

/\--cxiii

(Typ)

5

6

all

rivet

hole,

and

No.

a

Remove

Rig-Pin

end.

30

upper

Pin

Rig parts, drill a

No.

21

transfer-punch strip

21

No.

a

Rivet

rig-pin hole,

and

x

Hole

No.

(Typ)

Transfer-Punch Hole

(loosely

From

Reclamp lower strip; drill and countersink 1/2-inch Camloc collar vise.

0.050 Spacer Camloc Grommet

hole. 7

Install Camloc collar.

8

Assemble ensure

in

parts,

and

rivet

alignment, rig pin

them.

Camloc

Rig

Pin in

with

Place~

Tape

door

securely :P:

(Typ)

inplsce.

(Typ’

Q´•

Untrimmed Door amloc Grommet

loc

and Stud

1/8 in.

transfer punch.

Camloc Stud Locator Ali

Camloc Stud Locator

Ring

Mark hole center

should be

Receptacle (Typ

and

CA~LOC STUD LOCATOR

To

place during riveting operation.

(Typ)

Receptacle (Typ)

Door Frame

LOCATI~ CAIUOC STUDS 1

Install Camloc stud locator in eaCh

receptacle 2

3

around

opening.

Align mtrimmed door and securely tape it

Skin

opening, place.

in

each

Door Frame (Ref

and

Align locator, install rig pin, on

(Ref

over

mark center of stud location.

procedure opening.

Repeat

locator around

Locating Access Door Fastener Locations Figure 10

EFFECTTVITY: SRM-4

ALL

30

(5/32 Rivet)

hole.

spacers

5/8

Pin Hole

Drill No. 21

0.100-inch spacer between strips at

joggled Through

Deg.

2

Drill No.

51-30-03

Fage 213 May 15/92

Leariet

STRUCTURAL REPAIR PIIANUAL PROTECTIVE TREATMENT OF STRUCTURAL MATERIALS i.

GENERAL A.

B.

2.

Any repair process which breaks the surface of the original structure requires a protective treatment. The treatment acts as a paint base and corrosion protection when applied prior to the installation of repair parts. Structural components whose surfaces have not been damaged beyond the limits of allowable dam age or whose surfaces have been damaged by corrosion must be protective treated. Final aircraft exterior finish is described in the appropriate Leajet Maintenance Manual.

FINISH SPECIFICATIONS AND CODE NUMBER (See Figure 1.) A. The finish specifications are listed in tabular form using code numbers that or

three dash numbers

as

are

composed of one, two,

required to finish a part.

(1) The order of the dash numbers specifies the sequence of application. (2) Finish code numbers also are listed in each table. Finish

B.

Specifications

NON-

ALUMINUM

Wings

CORROSIONRESISTANT STEEL

FIBERGLASS

Tip Tanks

Exterior of skins as

CORROSIONRESISTANT STEEL

except

F4

(1)

noted

Interior of skins except as noted

F4-4

Exterior surface of upper and lower skin between

F4-6

(6)

fuselage fairings Exterior surface of lower skin under

F4-6

leading edge

fairing between

spats No. 1

and No. 2 Exterior surface of doublers Interior surface of between

dry bay extension and tip tank

Tip tank casting

LE~ -1135

EFFECTIVITY:

F4-6 F4-6

F4-4

Specifications Table Figure 1(Sheet 1)

Finish

ALL

51-30-04

Page 1 SRM-4

Jun 1/95

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL R.

FinishSpecifications (cont.)

NON-

CORROSION-

CORROSION-

RESISTANT

RESISTANT

STEEL

STEEL

ALUMINUM Area between spars 7 and 8

F4-6

Wing Spar No.

F4-4

8

FIBERGLASS

Parts In fuel

Attach

F4-4

area

In non-fuel

F8-4

F4-6

area

fittings

F4-6

Plumbing (3) In fuel

F4-4 Ext

area

F4 Int. In non-fuel

Throughout

F4-6

area

Aircraft

I

I

I

F17, F17-6, orF20

Main Gear Wheel Well

F4-4

Battery Area

F4-4

F8-4

Structure Not Visible

F4-6

F8-6

Horizontal Stabilizer

F4-6

Tubing in Structure Open

(2)

(2)

F4-6 Int.

F1-2 Int. 8

(4)

8 Ext. Closed

i

F8-6 Ext.

Fl Int. 8 F4-6 Ext.

Fuselage

Fuel Cell

Engine Nacelle

(8)

F15 Int. 8 F8-6 Ext.

F4-6 F4-6 Int.

F8-6 Int.

Finish

Specifications Table Figure 1 (Sheet 2)

EFFECTIVITY:

ALL

51-30-04

Page2 SRM-4

Jun 1/95

Learjet STRUCTLIRAL REPAIR WIANUAL FinishSpecifications (cont.)

B.

NONCORROSIONALUMINUM

RESISTANT STEEL

F1 Ext. 8

FO-0-7

CORROSIONRESISTANT STEEL

FIBERGLASS

Landing Gear Doors Skin

F14-6 Int. F8-6

F4-6 Ext.

Pan

8 Int. Inside

Assembly

F8-6

FO-0-7

Tailcone Access Door Skin

F4 Ext. 8

Pan

F4-6

Inside Assembly

FO-0-7

F4-6 Int.

Other

Hinged

Access

F4-6

F0-0-7

Doors

F4-6 Int. 8

Exterior Skins

F4 Ext. Covered

fairings,

by attach angles

F4-1

(5)

F4a

(7)

etc.

Fuselage Area Over wing, under floors,

F8-6

(9)

between frames 15 and 22

I

Specifications Table Figure 1 (Sheet 3)

Finish

EFFECTIVITY:

ALL

51-30-04

Page sRM-4

3

Jun 1/95

STRUCTURAL REPAIR MANUAL NOTES:

(1) Add aircraft exterior finish per the appropriate Learjet Maintenance Manual. (2) No interior finish is required on tubing closed by welding (3) Except on plumbing lines that are beaded on the end, omit primer from exterior surfaces of plumbing lines for

(a) (b) (C) (d)

a

distance of 1 inch from end. Prime beaded lines end to end.

primer from connecting surfaces of welded bosses. Where possible, protect to avoid removing anodized finish of fittings. Omit primer from interior surfaces of oxygen lines and fire extinguisher lines. Omit primer from plumbing lines less than 6 inches in length, unless they ate exposed ceive a top coat. Omit

(e) Omit primer from exterior surfaces of 1100-0 and 3003-0 aluminum

and

t´•e-

tubing. Chemically clean in-

terior and exterior.

(4) Finish major structural parts

to F4-4.

Brackets, plumbing, and other easily replaced parts may be fin-

ished to F4-6.

(5) Mask off, clean, and prime surface removable

1

fairings

that

are

not

fay

areas

of skin that

sealed in

are

to be covered

by

removable attach

angles or

place.

(6) Finish areas for lightning strike protection to Fl. (7) As an option, apply Pro-Seal 890 (MIL-S8802) to fasteners that may

not need to be corrosion

proted-

by only using epoxy primer. (8) Major structural parts installed in the battery area shall be finished to F8-4. After installation, all rivet heads and any damaged areas shall be touched up with epoxy primer. (9) After installation, all bolt heads and nuts and any damaged areas shall be touched up with epoxy primer. ed

EFFECTNITY:

ALL

51-30-04

Page 4 SRM~

Jun 1/95

Learj~t ~Learptl STRUCTURAL REPAIR MANUAL C.

FinishCode Number

DASH NUMBERS Ist

I 2nd

I 3rd

I

DESCRIPTION this part of finish given before (Assemblies).

Fo

No finish required (Detail Parts)

F1

Chemically

F2

(a)F1,

(b)Gritblast

F3

(a) F1,

(b) Anodize (Chromic Acid)

F4

(a) F1,

(b) Chemical Film

Colored Chemical Film

F5

(a) Fl,

(b) Chemical Film

Clear Chemical Film

F6

Apply Sanding

F7

(a) Fi,

(b) DichromateTreatment

F8

(a) F1,

(b) Cadmium Plate 0.0003

F9

(a) F1,

(b) Cadmium Plate

F10

(a) F1,

(b) Hard Chromium Plate

F11

(a) F1,

(b)

F12

(a) F1,

(b) Apply Manganese Phosphate Coating

F13

(a) Fl,

(b) Apply Zinc Phosphate Coating

F14

(a) Solvent Clean,

F15

(a) F1,

F16

Apply Hard Anodize

F17

(a) Fl,

F18

Natural Satin Finish (Stainless Steel)

F19

Natural Satin Finish

F20

I

I

I

or

clean.

Surfacer

to 0.0005

0.0002 to 0.0003

Decorative Chromium Plate per QQ-C320 Class

1.Type

1

(b) Apply Pretreatment Primer

(b) Apply corrosion preventive to interior surface per Mll-A-8625,

Type

of closed end steel assemblies.

111

(b) Pickle and Passivate (300 Series Stainless Steels.)

(Aluminum Alloys)

(a) F1, Passivate Only

F21

Non-Directional Satin Finish

(Stainless Steel)

F22

Non-Directional Satin Finish

(Aluminum Alloys)

S100AR

(Low Electrical Resistance)

Finish Code Numbers

Figure 2 (Sheet 1) EFFECTIVITY:

ALL

51-30-04

Page sRM-4

5

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL C.

FinishCodeNumber (cont.)

DASH NUMBERS Ist

2nd

3rd

DESCRIPTION

F23

Chemical Treatment of Lead

F24

Chemical

F25

(a) Fl,

(b)

F26

(a) Fl,

(b) Zinc Plate

F27

Pickle

only. (300 Series Stainless)

F28

Pickle

only. (Low Alloy Steel)

F29

(a) F1,

(b) Electropolish (Corrosion Resistant Steels)

F30

(a) Fl,

(B) Zinc-Nickel

F31

(a) Fl,

(B) Zinc-Nickel Plate

F32

(a) F1,

(B) Applly Non-Chromic Acid Anodize Per MIL-A-8625, Type IC

-O

This

Cleaning

and

Etching

of Aluminum Parts for

Bonding

Zinc Plate 0.0003 to 0.0005 0.0002 to 0.0003

Plate 0.0003 to 0.0005 0.0002 to 0.0004

part of finish previously indicated.

1

(Not Used)

-2

(Not Used)

3

(Not Used)

-4

Epoxy

-5

Apply

-6

Epoxy

-7

Corrosion

-8

Epoxy Primer (Light Green)

-10

No additional finish

Fuel Resistant and Corrosion Protection Finish Solid Film Lubricant Primer

Inhibiting

Metal Bond Primer

1

Flat Black

Topcoat (Urethane)

(Color

-2

Flat White

Topcoat (Urethane)

(Color No. 37875)

-3

Flat Red

Topcoat (Urethane)

(Color

No.

No.

37038)

31136)

Finish Code Numbers

Figure 2 (Sheet 2) EFFECTIVITY:

ALL

51-30-04

Page 6 SRM-4

Tun1/95

STRUCTURAL REPAIR MANUAL C.

FinishCodeNumber (cont.)

DASH NUMBERS 2nd

Ist

DESCRIPTION

3rd

-4

1

GlossBlack

-5

1

FlatBlack

-6

1

GlossGreen

(Color No. 17038)

Topcoat(Urethane)

Topcoat(Urethane) of

(Identifioation

No.

37038)

(Color No.

141 1 0)

(Color

Epoxy EnamelTopcoat

Prototype Parts)

-7

1

GlossAluminum Topcoat (Urethane)

(Color

No.

17178)

-8

1

FlatGrey Epoxy EnamelTopcoat

(Color

No.

36118)

-9

1

Gloss Omaha

Orange Topcoat (Urethane) (Color Parts)

No.

12473)

(Identification

of Slave

-10

No additional finish

-11

Gross White

-12

Gloss Red Topcoat (Urethane)

-13

Gloss Yellow

-14

Gloss Blue

(Color No. 17875)

Topcoat (Urethane)

(Color No. 11136) (Color

Topcoat (Urethane)

No.

13655)

(Color No. 15180)

Topcoat (Urethane)

Finish Code Numbers

Figure 2 (Sheet 3) 3.

VAPOR DEGREASING A.

Materials:

(1) 1,1,1 B.

Degreaser

trichloroethane

(methyl chloroform) inhibited, vapor degreasing (MIL-T-81533).

Procedure

(1) Rack parts so condensed solvent can drain freely from surfaces. NOTE:

Parts shall be

(2) Parts shall

dry when introduced into degreaser to

not be introduced into

degreaser

Parts shall be left in vapors until clean

or

avoid water contamination.

unless the vapor level is up to the condensing coils. no longer any condensation on the surfac-

until there is

es.

(3) Parts may be subjected

ing heavy

(4) Parts which the

are

scrubbing

not clean shall be

action

or

sprayed

with cold solvent to aid in

dislodg-

recycled. Cooling

the

parts prior

to the second

cycle

increases

cleaning efficiency.

(5) Parts which require

EFFECTIVITY:

to some

films.

ALL

no

further

cleaning prior to painting shall not be handled with bare hands.

51-30-04

Page 7 SRM-4

Jun 1/95

Learjet ~Leariet

STRUCTURAL REPAIR MAMUAL 4.

SOLVENT CLEANING A.

Use this

procedure to

clean the

(1) Parts covered with (2) Parts (3) Prior (4) Prior B.

following: significant quantities of oil or grease.

to receive brush chemical film treatment.

application of top coat or touch-up, primed parts which have been sanded. to application of wash primer, aluminum honeycomb parts, spot welded assemblies, anodized parts, and predominantly aluminum assemblies which include one or more steel parts. Cleaning Procedure (1) Wipe off excess oil and grease. (2) Apply methyl ethyl ketone (MEK) (TT-M-261) from safety cans with clean, oil-free, absorbent to

cloths.

(3) Scrub surface with a clean cloth, if necessary, to loosen the soil. (4) Repeat applications of clean solvent as necessary to remove all soil. (5) Wipe off solvent with clean, absorbent cloths. Do not allow solvent

to

dry

on

surface,

as a

resi-

due will remain.

(6) Blow assembled faring surfaces free of solvent with oil-free air. (7) Solvent cleaned surfaces shall be dry and free of all visible soils. Iridescent surfaces of 5.

improper cleaning and

shall be cleaned

are

evidence

again.

ABRASIVECLEANING OFMETALS A.

I

General

Requirements

(1) Oily sive

or

greasy parts shall be vapor

degreased

per

paragraph 3, Vapor Degreasing, prior

to abra-

cleaning.

(2) Parts shall be abrasively cleaned only immediately preceding final finishing to prevent corrosion. (3) Significant surface defects shall not be removed by abrasive cleaning. (4) Where a significant loss of metal cannot be tolerated and/or a smooth finish is required, a size 180 grit or finer abrasive shall be used. When heavy layers of dirt, scale, or oxides are to be removed and the surface is to receive

subsequent finishing

or

processing,

abrasive may be used for cleaning. grit be used with either hand or power tools. All abrasives (5) may their within be Parts must (6) original permissible tolerances after abrasive 150

a

metallic brush

or

size

or coarser

cleaning.

(7) Compressed air used for blowing off dust, drying parts, or for abrasive blast cleaning shall be essentially free from moisture, oil, and other foreign solid particles. loose particles shall be removed from parts by a jet of air immediately upon completion of All (8)

cleaning. Care shall be exercised that surfaces adjoining the surface to be abrasively are not impaired by any phase of the cleaning process. Abrasive Cleaning with Papers, Cloths, Wools, and Brushes (1) Abrasive cleaning of small areas shall be accomplished by using one of the applicable abrasives indicated in Figure 1. (2) During the life of an abrasive material, the abrasive material shall be used for the cleaning of one class of materials only. The following classes of metals shall be used: (a) Carbon and low alloy steel. abrasive

cleaned

B.

(b) Corrosion resistant steels. (c) Aluminum and aluminum alloys. (d) Copper and copper alloys.

EFFECTIVITY:

ALL

51-30-04

Page 8 SRM-4

lun 1/95

Leariet ~j Learjet

STRUCTURAL REPAIR MANUAL 6.

CHEMICAL FILM TREATMENT OF ALUMINUM AND ALUMINUM ALLOYS

NOTE: A.

Equivalent processes meeting the requirements of MIL-C-5541, Class 1A,

may be used.

Materials

(1) Turcoat Accelagold manufactured by Turco Products, Wilmington, California: 0.5

ounce per galTurcoat of 2.0 0.5 to ounce lon of water. Maintain aging solution in the range Accelagold per gallon of water with pi-I of 1.7 to 1.9. When the pH cannot be maintained in the specified range with

the addition of

required Turcoat Accelagold:

(a) Raise the pH by adding ammonium hydroxide. (b) Lower the pH by adding nitric acid. B.

Procedure NOTE:

apply chemical film treatment to parts or assemblies having joints or crevices or any type of configuration that will entrap solution unless those areas are positively

Do not

other

masked off.

(1) Vapor degrease all parts covered with significant quantities of oil

or

grease per

paragraph 3,

Va-

por Degreasing, or solvent clean per paragraph 4, Solvent Cleaning.

(2) Immerse parts in solution per step A. for 0.5 to 6.0 minutes at 400 to 1000F (4.40 to 370C). (3) Rinse parts in room temperature water (40" to 1000F [4.4" to 370C1) and then in warm water (100" to 1400F [370 to 600C1). (4) Dry parts in still or circulating air in the temperature range of 60" to 1400F (15" to 600C). CAUTION:

DO NOT WIPE PARTS FOR ANY REASON UNTIL THEY HAVE DRIED 24

HOURS.

(5) Apply required paint CAUTION:

to treated surfaces within 12 hours after

drying.

HANDLE TREATED PARTS SO AS TO AVOID FINGERPRINTING PRIOR TO PAINTING.

(6) Scratched or otherwise impaired small areas may be touched up as follows: (a) Strip chemical film from area with a Scotch-Brite pad, or equivalent. (b) Swab or brush small quantities of Turcoat Accelagold solution over the duce

a

satisfactory

the chemical film, along the produce a continuous film.

(c) Apply the solution far

as

necessary to

(d) Using a sponge (e) Dry the treated 600C).

EFFECTIVITY:

ALL

or

stripped

area

to pro-

chemical film. over

brush rinse treated

area

in still

or

area

circulating

periphery

of the

stripped

area,

only

as

I

thoroughly with water. air in the

temperature

range of 60" to 1400F (150 to

51-30-04

Page 9 SRM-4

Jun 1/95

STRUCTURAL REPAIR MANUAL MATERIALS TO BE CLEANED Carbon

Aluminum

Corrosion

Low

Alloy Steel

ABRASIVES

Its

Resistant Steel

Magnesium Its Alloys

Alloys

Copper Its Alloys

Acceptable

Acceptable

Acceptable

Acceptable

Acceptable

Recommended

Acceptable

Acceptable

Acceptable

Acceptable

Acceptable

Recommended

Recommended

Recommended

Recommended

Steel Wool

Acceptable

Prohibited

Prohibited

Prohibited

Prohibited

Aluminum Wool

Prohibited

Prohibited

Acceptable

Prohibited

Prohibited

Acceptable

Recommended

Acceptable

Prohibited

Acceptable

Recommended

Prohibited

Prohibited

Prohibited

Prohibited

Steel Brush

Acceptable

Recommended

Acceptable

Acceptable

Acceptable

Monel Brush

Acceptable

Acceptable

Recommended

Recommended

Recommended

Sandpaper Emery Paper or

Cloth

Aluminum Oxide

Paper

or

Cloth

Stainless Steel Wool

Carbon Steel Brush Stainless

Abrasives and Their

Figure

Usage

1

MATERIALS TO BE CLEANED Carbon

Corrosion

Low

Resistant Steel

Alloy Steel

TYPE OF GRIT

Aluminum

Aluminum

Alloys

Magnesium Magnesium Alloy

Steel

Recommended

Prohibited

Prohibited

Prohibited

Silica

Acceptable

Acceptable

Acceptable

Acceptable

Garnet

Acceptable

Acceptable

Acceptable

Acceptable

Aluminum Oxide

Acceptable

Recommended

Recommended

Recommended

**Blast

cleaning permitted only

on

aluminum

or

magnesium alloy castings.

Blast

EFFECTIVITY:

SRM-I

ALL

Cleaning Grits Figure 2 51-30-04

Page 10 May 15/92

Learjet STRUCTURAL REPAIR MANUAL 7.

APPLYING SANDING SURFACER TO LAMINATED FIBERGLASS PARTS A.

Materials

(1) Andrew Brown Co. system: (a) P-900 Skyspar Surfacer (b) C-903 Converter (c) T-262 Thinner (2) Bostik system: (a) No. 464-3-1 Cat-A-Lac Hi-Build (b) CA-142 Catalyst

Primer Surfacer

(c) TL-52 Thinner or methyl ethyl ketone (MEK) (3) No. 49)(2 Neutral Patching Paste, Presto Chemicals Inc., Sun Valley, CA (4) Toluene(TT-T-548) (5) 320 grit abrasive paper (wet or dry) B.

Surface

(1) (2) (3) (4) (5) (6) (7)

Preparation

dampened with toluene, thoroughly clean the laminated fiberglass surface. produce a slightly roughened surface. Clean sanding residue from the area with a clean cloth dampened with toluene. Dry surface thoroughly.

With

a

clean cloth

Scuff sand the surface to

Mask off areas not intended to receive surfacer.

patching paste per manufacturer’s instructions. Apply patching paste to surface with a plastic scraper to fill pin holes, dents, abrasions, scratches. Squeegee away excess patching paste, leaving depressions filled flush with the surface. (8) Allow patching paste to dry thoroughly. (9) Sand patching paste smooth with 320 grit abrasive paper. (10) Thoroughly clean the filled surface with a clean cloth dampened with acetone to remove sanding Mix

residue.

(11) Dry surface thoroughly. C.

Applicationof Sanding Surfacer (1) Andrew Brown Co. System one part converter. Stir thoroughly and allow mixture to using. (b) Thin as required with thinner for spraying. (c) Spray a crosscoat of sanding surfacer on the prepared laminated fiberglass surface.

(a) Mix four parts surfacer with

sit

one

hour before

NOTE:

pot life of the mixed sanding surfacer is approximately only the amount of material that can be used within this time.

The

(2) Bostik System (a) Mix three parts surfacer with one part catalyst. Stir thoroughly. (b) Thin catalyzed material to a viscosity of 25 seconds (No. 2 Zahn

24 hours.

Catalyze

cup) using Bostik thinner

or

MEK.

(c) Strain thinned material through suitable paint strainer prior to spraying. (d) Spray a crosscoat of sanding surfacer on the prepared laminated fiberglass surface. NOTE:

EFFECTIVITY:

SRM-4

ALL

The

pot life of the mixed sanding surfacer is approximately eight only the amount of material that can be used within this time.

hours.

Catalyze

51-30-04

Page 11 Jun1/95

~Learjetl STRUCTURAL REPAIR MANUAL (3) Cure Andrew Brown Co. surfacer Cure Bostik surfacer at

sanding. can

be accelerated

by heating sanding

(4) Wet sand the cured

at

temperature (60"F [15"C] or above) for 12 hours before temperature for two to six hours before sanding; the cure

room

room

to 1000 to 1500F

surfacer in the

(370

to

650C) for

general

two to three hours.

direction of air flow with 320

grit

abrasive

paper.

(5) All surface imperfections, blemishes, and the additional to

8.

an

sanding

surfacer must be

absolute minimum while

applied

weave

to

completely obscured or sanding surfacer thickness

of the fabric must be

imperfect

meeting the requirements

areas.

of this

Hold

step.

APPLYING EPOXYPRIMER A.

Precautions

(1) The following precautions shall be adhered to when applying epoxy primer. (a) Clean and proper equipment shall be used. (b) The coating material shall be uniform, free of skins, lumps, gelled, or coarse particles. (c) Suitable ventilation and safety precautions shall be provided in the work area. (d) The finish area shall be free of dust and severe temperature change which will adversely af-

application and cure of the coating. requirements listed for the coating shall be strictly maintained. (f) Every attempt shall be made to produce a lint free, smooth, good quality finish. fect the

(e) Thickness B.

Material

(1) Super Koropon Fluid Resistant Primer, Green; Mfg.: Desoto, Inc., Garland, TX (a) 515)(400 Primer Base (b) 910)Nominal Material Thickness "T"

0.025

0. 032

0.040

(Minimum) Countersink

Angle

"A"

100"

Installation

EFFECTIVITY: sI1M~

ALL

(f2")

0.050

0.063

r,~73 nE’P-1 1-

Specifications for Flush Tension Head Rivets Installed High and Shaved Flush Figure 16 51-40-02

Page 20 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

0.008 Maximum

0.005

Maximum Sheet

Maximum

Gap Between Rivets and Dimpled Sheets Figure 17

3/32

1/8

5/32

3/16

1/4

Max.

0.165

0.211

0.272

0.339

0.462

Min.

0.160

0.206

0.267

0.334

0.457

Max.

0.010

0.010

0.010

0.010

0.010

Min.

0.004

0.004

0.004

0.004

0.004

Head Protrusion

Max.

0.008

0.008

0.008

0.008

0.008

After

Min.

0.002

0.002

0.002

0.002

0.002

NOMINAL RIVET DIAMETER Countersink Diameter Refer to

figure 11,

"Countersink for and

Liquid-

Gas-Tight Holes"

Head Protrusion Prior to

Driving

Driving

Countersink

Angle 100"

figure 11, "Countersinks Liquid- and Gas-Tight Holes"

Refer to for

(f1/20)

Flush Tension Head Rivets Protrusion Specifications For Liquid- and Gas-Tight Installations

Figure EEFECTIVITY: SRM~

ALL

18

51-40-02

Page 21 May 15/92

Learjet STRUCTURAL REPAIR MANUAL Below Flush

Unacceptable for all Flush Head Driven Area

d

Rivets

not

filled than

Rivet

the

Countersink

completely

extends

40 head

more

percent of circumference

Rivet:

or

Dimple

Countersink

for Plush

Rivets

not

Area

completely filled

or

Dimple

13nacceptable for Flush Shear

land the driven head

on

double

Head Rivets

flush rivets)

filled

extends

head

the

circumference

but

allo~s

insertion inch

0.001

of

less

percent of

than 40

feeler

gauge

at

point

any

Countersink

completely

not

Area

Dimple

or

Rivet

Unacceptable for

Flush Sheer Head Rivets

Area

not

of

the

does

not

0.001

at

any

or

circumference

head

of

Countersink

completely filled than 40 percent

less

extends

allow the inch

and

insertion

feeler

gauge

point.

Dimple

Rivet

Acceptable

for Plush Sheer Head Rivets

Acceptance Specifications for Flush Head Figure 19 EFFECTIVITY:

ALL

Driven Rivets

51-40-02

Page 22 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL used to attach most external skin panels on the Learjet. Before driving, S-194 rivets installed in countersinks shall appear as follows and as shown in Figure 20. (a) Slightly exposed countersink is visible.

(12) Crown flush rivets S194

are

(b) Edge of rivet head is always low. (C) Crown is always high (0.008 inch [.2032 mm] high, maximum). (d) Countersink diameters are per Figure 11. After driving, S-194 rivets shall appear and

as

shown in

Figure

(e) Visible exposed countersink is acceptable. (f) Edge of rivet head can be same height as rivet head

(g)

Crown shall be flush to

crown to

8

high per 51-40-04.

All the above conditions must exist for rivet installation

9

1[-

Tf

S-194

dimple

S-194 RIVET BEFORE DRIVING

follows

slightly below skin surface.

(h) Rivet heads shall not be shaved. (i) A 0.001 feeler cannot be installed between rivet head and countersink NOTE:

as

20.

at

any

point.

acceptance.

(I

II/G3

Rivet has in butt.

S-194 RIVET APTW

DRIVING

Acceptance Specifications for S-194 Crown Flush Rivet Installation Figure 20

EFFECTIVITY: SRM4

ALL

51-40-02

Fage 23 May 15/92

Learjet STRUCTURAL REPAIR MANUAL (13) Shaving of flush shear head rivets is

not allowed.

(14) Shaving of flush tension head rivets

to meet surface flushness

requirements

of 51-40-04 is al-

lowed.

(15) Flush tension head rivets installed in a liquid- or gas-tight area that have been driven high and shaved flush, shall be checked for loss of tensile strength per Table 2.

Nominal Rivet Diameter Minimum Head Diameter after

FLUSH SMEAR HEAD RIVETS

RIVET SHAVING

CHECKING DIMENSIONS

Shaving

3/32"

1/8"

5/32"

3/16"

1/4"

0.160"

0.206"

0.267"

0.334"

0.450"

Table 2

(16) Flush tension head rivets that have been driven high and shaved flush head rivet, shall be checked for loss of shear strength per Table 3.

CHECKING DIMENSIONS

RIVET SHAVING

Nominal Rivet Diameter Minimum Head Diameter after

Shaving

to function

as a

flush shear

FLUSH TENSION HEAD RIVETS

3/32’

1/8"

5/32"

3/16"

1/4"

0.1 48"

0.196"

0.247"

0.302"

0.395"

Table 3

(17) Cracked Driven Heads (a) Cracks in driven heads

are

2117-T4 rivets

NOTE:

undesirable and must be

are

kept to a minimum.

driven in hard condition;

therefore,

a

large percentage

will have

cracks if driven 1.5 times the shank diameter. For this reason, care should be taken to keep the driven head to 1.3 times the shank diameter per Figure 14.

diagonal

(b) Cracks caused

on

the sides of driven heads which

by upsetting the

be evaluated

1) 2) 3)

EFFECTIVITY: SRM-I

as

rivet material

run

beyond

at

a

450

angle

to the flat

the limit of its

surface of the head

ductility. Diagonal

are

cracks shall

follows:

superficial cracks are allowable in all cases regardless of their numbers. Intersecting superficial cracks are also acceptable. Rivets having as many as three diagonal cracks which do not intersect are acceptable. Rivets with severe cracks are not acceptable and should be replaced. Hairline

ALL

or

51-40-02

Page 24 May 15/92

Learjet I

STRUCTURAL REPAIR MANUAL by a lap in rivet wire, and the other caused by overheat treating the rivets. It is very important to distinguish between these two types. 1) Cracks due to lap in rivet wire appear infrequently. The surface exposed by the cracks will be smooth and dull in appearance and will be only a few thousandths deep (0.005 to 0.015 [.0127 to .381 mm]). These cracks are acceptable. 2) When cracks from overheating appear, they are usually found in a large percentage of the rivets being driven. This cracking is due to excessive temperatures being reached during the heat treatment of the rivet. These cracks are not acceptable, and rivets having these vertical cracks on either head shall be rejected. The batch which was overheated should be segregated and scrapped because the ductility cannot be restored by reheat treatment. (18) Bell-shaped driven heads are formed by use of too light a bucking bar or by rocking the bucking bar. Rivets which show evidence of this condition should be rejected since the rivet hole is poorly filled and the head has very little bearing surface on the sheet. (19) Shanked Rivets Fart Separation (a) A maximum of 0.015 inch (.381 mm) shanking (part separation) is permissible for the rivet adjacent to intermediate material as shown in Figure 22. (6) Sheet separation shall be less than 0.002 inch (.0508 mm) adjacent to universal, brazier, and (C) There

are

two

types of vertical cracks:

countersink driven rivets with

Figure

22. If

a

a

one

caused

0.008 inch (.2032 mm) maximum between rivets

0.002 inch (.0508 mm) feeler gauge

rivet shall be considered shanked and is not

can

as

shown in

be inserted to the shank of the rivet, the

acceptable~

For sheet

separation

in

dimpled

ma-

terial, see Figure 17. In the case of riveting dissimilar metals, where tape is used between the sheets, the total separation of the metallic sheets shall not be greater than the thickness of the tape plus the maximum separation permitted above. The allowable sheet separation of fay F.

sealed joints is 0.004 inch (.1016 mm) at the shank of the rivet. MechanicallyExpanded Blind Rivets (1) Blind rivets are intended for use where access is available to only one side of the work. (2) Blind rivets are installed with special tools in holes specified in Figure 5. (3) Head gapping on the visible side shall be checked with a 0.002 inch (.0508 mm) feeler gage for both countersunk and protruding head blind rivets. Rivets with more than 0.002 inch (.0508 mm) gap on more than 40 percent of the head circumference are not acceptable. flushness of the stem break on installed wiredraw bulbed Cherrylock blind rivets (fiush head The (4) and protruding head) shall be in accordance with Figure 23. (5) The flushness of the collar on installed wiredraw bulbed Chenylock blind rivets shall be in accordance with Figure 23. (6) The flushness of the stem break on installed Chenymax blind rivets shall be in accordance with Figure 24. (7) The flushness of the stem break and collar on installed Huck "Conical Keystone" and Huck "General Purpose" (NAS 1919 and 1921) blind rivets shall be in accordance with Figure 25. (8) A slight collar "flash" caused by the pressure necessary to install the collar is acceptable within the limit shown in Figure 26 for all Cherry and Huck rivets. (9) Shaving of installed blind rivets shall be limited to removal of stem and/or removal of collar down to flush with the head of the rivet.

(10) Blind rivets

EFFECTIVITY: SRM-4

ALL

can

be removed in

a

similar

The head of the rivet shall not be shaved. manner to

that

specified

for solid rivets.

51-40-02

Page 25 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Intermediate

Material

0.032-Inch Maximum. No

joggle

or

shim

re-

quired by drawing.

0.015

Inch

Adjacent

Maximum Rivet

Shanking

(~ivet

Intermediate

Material

Only)

to

0.032-Inch

iLess

than

0.002

Inch

0.008

Inch

Max.

r

0.008

Inch

Max.

fLess

than

0.002

Inch

t

f Less

Shanking and

EFFECTNITY:

Max.

ALL

than

0.002

Inch

Separation Tolerances Figure 21

Sheet

51-40-02

Page 26 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL G.

Huck Lockbolts

(1) The lockbolt and collar used shall be

as

originally

installed. The collars

are

lubricated when

re-

ceived from the manufacturer and should be stored away from heat, dirt, and grit until used. (2) Grip length adjustment of the lockbolts may be accomplished by the use of washers (1/32 inch minimum thickness). For aluminum and steel material, one AN960PD aluminum washer may be or one AN960 cadmium plated steel washer may be used under the collar. The thickness of the washers shall not exceed 1/16 inch. (3) Final hole sizes for lockbolts shall be as specified in Figure 7. (4) Lockbolts shall be installed with tools recommended by the manufacturer. The swaging die for

used under the head

lockbolt collars shall not be

tipped

more

than 3

degrees from the lockbolt axis during driving.

(5) The end of the ’broken-off" portion of the pull pin does not require corrosion protection. (6) Collars cracked after swaging shall be rejected. (7) The presence of gaps which allow the insertion of a 0.004-inch (.1016 mm) feeler gage between the countersunk or protruding head and the bearing surface shall not be accepted when more than 40 percent of the head circumference has such a gap. In all cases, the cause of the production of gaps shall be eliminated if NOTE:

possible.

of doubt, lockbolts may be checked for proper swaging of the collar and breakpull pin with the lockbolt inspection gage. See vendor supplied Huck catalog for proper gage (Huck Mfg. Co., 6 Thomas, Irvine, CA 92714).

In

case

off of the

Stem

(Ref.)

.015

(Max.)

t

Collar

Stem Flushness

EFFECTIVITY: sRM4

ALL

(Ref.)

Specifications for Cherrylock Blind Figure 22

Rivets

51-40-02

Page 27 May 15/92

Learje

STRUCTURAL REPAIR MANUAL

(Ref.)

Stem

.020

.015

Max.

7

(Ref.)

Collar

Collar Flushness

*0.015

.010

t

inch

Specifications for Cherrylock Figure 23

for

-4

(0.125 inch)

Blind Rivets

diameter

c´•"’"

1 .020

Stem Flushness Specifications for

I

I

only.

_1 1

1*.020

Cherrymax Blind Rivets

Figure 24 EFFECTIVITY: sruur-4

ALL

51-40-02

Page 28

May

15/92

Learjet STRUCTURAL REPAIR MANUAL

c

A

RIVET SIZE

"A"MAX.

"B"MAX.

"C"MAX.

1/8

0.012

0.016

0.008

5/32

0.015

0.020

0.010

3/16

0.018

0.024

0.012

Stem and Collar Flushness Huck Conical

Keystone

Specifications for Purpose Blind Rivets

and General

Figure 25

Flash

~20

Allowable Flash

EFFECTTVITY: SRM-4

ALL

on

Inch

Max"’

Cherry and Figure 26

Huck Blind Rivets

51-40-02

Page 29 May 15/92

Learjet STRUCTURAL REPA~R MANUAL H.

HuckBlind Bolts

(1) Final hole size for Huck blind bolts shall be as given in Figure 6. (2) Huck blind bolts are supplied lubricated. They shall not be degreased or re-lubricated. They shall be stored away from heat, dirt, and grit. (3) Dip bolt used in a wet fuel area in Pro-Seal 890 (MIL-S-8802) sealant immediately prior to installation.

(4) Huck blind bolts shall be installed with tools recommended by the manufacturer. The driving tool shall be held

its axis coincides with the axis of the fastener and

so

to the

perpendicular

sur-

face.

(5) The end of the bolt at the break-off point shall be touched up with epoxy primer. (6) Where possible, the blind side of the installation shall be inspected to see that proper blind head is formed. (See Figures 27 and 28.) Touch up blind side with Pro-Seal 890 (MIL-S-8802) or ProSeal 870 (MIL-S-81733) where possible. Use Pro-Seal 890 in wet fuel

NOTE:

(7) Gaps which allow the insertion of

protruding

head and

a

areas

only.

0.004 inch (.1016 mm) feeler gage between the countersunk or acceptable when more than 40 percent of the

surface shall not be

bearing

head circumference has the gap.

(8) Gapping under the manufactured heads of fasteners is undesirable from a quality standpoint. In all cases when gapping occurs, steps shall be taken to eliminate the cause. (9) The flushness of the locking collar and spindle of the Huck blind bolt fastener as driven shall be in accordance with

(10) Shaving of either the collar ble. I.

Fasteners with either collar

29.

Figure

quirements per Figure 30 shall

replaced. and/or the spindle

Shaving of the fastener head

a

wet

fuel

spindle

not

meeting

flushness

re-

to flush with the head of the fastener is

area

pennissi-

is not allowed,

Jo-Bolt Blind Bolts (NAS 1669 and NAS 1670) (1) The ~o-Bolt used shall be as originally installed. (2) Jo-Bolts are supplied lubricated. They shall not stored away from heat, dirt and grit. (3) Dip bolt used in

or

be

in Pro-Seal 890

be

degreased

re-lubricated.

or

shall be

They

(MIL-S-8802) sealant immediately prior

to installa-

tion.

(4) 10-Bolts shall be installed with tools recommended by the manufacturer. The held

so

driving tool

shall be

its axis coincides with the axis of the fastener.

(5) The end of the bolt

at the break-off

point shall be touched up with epoxy primer.

(6) Where possible, the blind side of the installation shall be inspected for properly driven collars.

Any

crack in

(MILS-8802) NOTE:

a

collar is

or

cause

for

rejection of the

Use Pro-Seal 890 in wet fuel

(7) Gaps which allow the insertion of

protruding

fastener. Touch up blind side with Pro-Seal 890

Pro-Seal 870 (MIL-S-81733) where

head and

bearing

a

areas

possible.

only.

0.004 inch (.1016 mm) feeler gage between the countersunk

surface shall not be

acceptable

when

more

than 40

or

percent of the

head circumference has the gap.

(8) Gapping under the manufactured heads of fasteners is undesirable from a quality stand point. In all cases when gapping occurs, steps shall be taken to eliminate the cause. (9) The stem breakoff limits for flushness with the skin surface shall be per Figure 30. If stem breakoff is outside of these limits, either the fastener used is out of grip length or it did not drive prop-

erly.

Stem breakoff

the limits

EFFECTIVITY: sRM4

ALL

a

too short

higher

than the limits will

generally

indicate

a

too

long

fastener and below

fastener. In either case, the fastener shall be removed and

replaced. 51-40-02

Page 30 May 15/92

Learjet STRUCTURAL REPAIR MANUAL Nom

je

Bol t

AS CLINCHED

Die.

PROTRUSION OF BLIND HEAD

NOMINAL

I

f

MIN.

MAX.

DIAMETER OF

DIAMETER

(Inches)

(Inches)

BLIND HEAD

(5/32) (3/16)

0.120

0.201

Max. dia.

-06

0.146

0.231

clinched blind

-08

(1/4)

0.188

0.279

head shall not

-10

(5/16) (3/8)

0.224

0.319

exceed

0.264

0.364

dia. of

-05

-12 As

as

max.

mfg. head.

LAs Clinched

Clinched

Protrusion of

AS CLINCHED

BOLT

Dia.

Blind

of

Blind

Head

Head

Dimensional

rJ> Allowable or

surface

discontinuities

formed

blind head

Longitudinal

Requirements for Clinched Figure 27

Blind Head

fractures

in are

-0.010

area as

of

follows:

max.

Circumferential -0.005

max.

Acceptable

(Providing requirements of figure 29 are met)

(Anytime

the

bolt

extrudes

out

and

land

on

the

bolt

sleeve over

the

pin)

Blind Head

Shapes Figure 28

EFFECTIVITY: SRM-4

ALL

51-40-02

Page 31 May 15/92

Learjet Learietl STRUCTURAL REPAIR MANUAL A A

A

Inspection A...Maximum

A

allowable

Locking Collar Position

locking

of

distance

NOMINAL

of

collar

COLLAR POSITION

FASTENER

above

head.

"B"

(MAX´•) (Inch)

(MAX.) (Inch)

5/32

0.017

0.010

3/16

0.022

0.012

1/4

0.029

0.015

5/16

0.037

0.019

3/8

0.045

0.023

(Same inspection procedure

fastener

SPINDLE POSITION

)1A(I

DIAMETER

below

or

is used for oversize

diameter.)

BTop

Top Land

Land

B

s~

~I

Inspection B...Maximum allowable

distance

Plushness

EFFE~TIVITY: SRM-4

ALL

of

of

top of

Spindle Position land

Requirements for Huck Figure 29

on

pin

above

or

below

fastener

head

Blind Bolt Installation

51-40-02

Page 32 May 15/92

Learjet

STRUCTURAL REPAIR NIANUAL

I

NOM. DIA. 0.164

PART NUMBER NASI 669-08

t

"A"

PART NUMBER

+0.000

NAS1670-08

+0.088 0.200

NAS1 669-3

NAS1 669-4

NAS1 6703

+0.010

NAS1 669-5

NAS1 670-4

+0.047

0.375

NAS1 669-6

+0.010 -0.078

NAS1 670-5

+0.043 +0. 146

+0.010 -0.073

+0.135 0.312

+0.010 -0.068

+0.098 0.260

"B"

1

+0.049

+0.010 -0.083

NAS1 670-6

+0.152

+0.010 -0.093

NOTE: "A" is above skin surface, "B" is below skin surface.

Flushness

EFFECTIVITY: sIzM~

ALL

Specifications for Jo-Bolt Installation Figure 30 51-40-02

Page 33 May 15/92

Learjet ~Learierl

STRUCTURAL REPAIR MANUAL J.

Hi-Loks

(1) The Hi-Lok pin and collar used shall be as originally installed except as substituted. (Refer 70-00, Figure 202.) (2) Collars as received are lubricated. Degreasing or additional lubrication is not allowed. (3) In inaccessible areas where space or location will not permit the use of specified collars, may be substituted

as

to 51-

a

nut

shown in Table 4.

SUBSTITUTED NUT

SPECIFIED COLLAR

INSTL TORQUE

(In Lbs) HL70-5, HL90-5A, HL91-5 HL72-5, HL86-5 HL79-6, HL84-6, HL90-6A, HL94-6 HL72-6, HL86-6, HL87-6, HL87-6W, HL93-6 HL70-8, HL79-8, HL90-8A, HL94-8 HL72-8, HL87-8 HL90-10A, HL94-10, HL86-10

MS21 042-08

15

25

MS21 042-08

30

40

MS21 042-3

25

35

MS21 042-3

40

50

MS21 042-4

60

80

MS21 042-4

115

130

MS21 042-5

130

160

Table 4

(4) All Hi-Lok Bolts ant

prior to

to be used in

a

wet fuel

area

shall be coated with Pro-Seal 890 (MIL-S8802) seal-

installation.

(5) Final hole size and countersink for Hi-Loks shall be as specified in Figures 9 and 13. (6) Hi-Loks shall be installed with tools recommended by the manufacturer. (7) Washers used for

grip adjustment

shall be AN960 cadmium

plated

steel.

(8) When installing a standard Hi-Lok collar, the use of one (1) washer, 0.032 inch (.812 mm) maximum thickness, under the collar is allowable. When (9) installing the MS21042 substitute nut, with bolt head and all material in "sheared-up" condition, use washers to "cover-up" a minimum of two (2) "imperfect" bolt threads prior to installing the nut. Maximum allowable quantity of washers is two (2) per fastener. Maximum allowable thickness of individual washer(s) is 0.063 inch (1.6 mm). (10) At all protruding head style bolt locations, prepare the edge of the hole adjacent to the bolt head as

shown in

Figure 31.

(11) The presence of gaps which allow the insertion of a 0.004 inch (.1016 mm) feeler gage between the countersunk or protruding head and bearing surface, shall not be acceptable when more than 40

percent of the head circumference has the gap. (12) The pin protrusion after installation shall be within the limits specified in Figure 32. (13) After assembly, the maximum collar gap allowables NOMINAL DIAMETER

are

per Table 5.

COLLAR GAP (Maximum)

5/32

0.003

3!16

0.004

114

0.005

5/16

0.006

3/8

0.007

7/16

0.008

1/2

0.009

TableS

EFFECTIVITY: SRM-4

ALL

51-40-02

Page 34 May 15/92

Leariet Learjet

STRUCTURAL REPAIR MANUAL

pin sizes a, -6 -8 [f10] chamfer optional)

0.010 ~0.005) Radius for

(0.010

~0.005]

x

45"

0.015 (~0.005) Radius for

(0.010 ~0.005]

Hole

x

45"

pin sizes -10

thru -16

[+10] chamfer optional)

Edge Preparation Specification for Hi-Lok Installation Figure 31 I

j

P

P1

j HINmnn

L~Y ~I\\ \\1

GRIP

h~ \I

h\\\\\r

Y//~/1

P~XIMUM

Y~I

GRIP

t

t Minimum

Grip

Maximum

(Maximum Protrusion)

Grip

(Minimum Protrusion)

MINIMUM

FASTENER

PROTRUSION

MAXIMUM

PROTRUSION "Pt"

DASH NUMBER

NOMINAL DIAMETER

-5

5/32

0.302

0.384

-6

3/16

0.315

0.397

-8

1/4

0.385

0.467

-10

5/16

0.490

0.572

-12

3/8

0.535

0.617

-14

7/16

0.625

0.707

-16

1/2

0.675

0.757

Hi-Lok Pin Protrusion Allowables

Figure 32

EFFECTIVITY: SRM4

ALL

51-40-02

Page 35 May 15/92

Leariet Learjetl

STRUCTURAL REPAIR MANUAL FASTENER SUBSTITUTION 1.

GENERAL A.

When

adapting

necessary to

use

shown in this manual to suit actual conditions, it may be found different fasteners than those originally used. This may be due to nonavailability of

the

typical repairs

particular fastener, restricted access, or other difficulties not foreseen in the original repair. Make selection of substitute hardware per figures 1 thru 8. The following the fastener part number is used to identify the length, diameter, finish, or other fastener definitions. These identifications must be the same as the original hardware. a

B.

C.

SPECIFIED HARDWARE B100-T Blind Huck Bolt

(NAS523

Pt)

Code

BPT Blind Huck Bolt

(NAS523

Code

UB100-T Blind Huck Bolt

Diameter and

(NAS523 Code

length

N)

(NAS523

Code

length to

TX)

UB100-T Blind Huck Bolt

Diameter and

(NAS523 Code

length

UBP-T Blind Huck Bolt

Diameter and

TX)

(NAS523 Code

length

TX)

grip

to be the same

Diameter and

length

TY)

Diameter and grip length to be the same

(NAS523 Code

TX)

(NAS523 Code

TX)

TX)

MS90354U (NAS523 Code

TX)

MS90353U

8P-T Blind Huck Bolt

MS90354

same

TY)

TY)

(NAS523 Code

grip

to be the

(NAS523 Code

(NAS523 Code MS90354U

same

B100-T Blind Huck Bolt

TY)

MS90353

same

grip

be the

TY)

TY)

grip

to be the

Diameter and

UBP-T Blind Huck Bolt

Code

(NAS523 Code

RESTRICTIONS

e

MS90353

(NAS523

I

TX)

MS90354U

(NAS523 Code

SUBSTITUTE HARDWARE

e

MS90353U

(NAS523 Code

1

grip

to be the same

Diameter and grip to be the same

length I

Diameter and

length

grip

to be the

same

NAS6203-()D NAS6204-( )D NAS6205-()D NAS6206-( )D NAS6207-( )D NAS6208-()D

NAS464P3-() NAS464P4-() NAS464P5-() NAS464P6-( NAS464P7-()

NAS464P&()

Bolt and Blind Bolt Substitutions

Figure 1(Sheet´• 1) EFFECTIVITY:

ALL

51-40-03

Pagel SRM-(

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL

NAS464P9-( NAS464P10-( NAS464P12-( NAS464P14-(

1 i

NAS464P17-(

NAS6209-( )D NAS6210-( )D NAS6212-( )D NAS6214-()D NAS621-( )D

NAS 1608-(

NAS 1603-( )R thru NAS 1608-()R

1703-() thru NAS 1708-(

NAS 1703-( )R thru NAS 1708-()R

thru

NAS 1603-(

NAS

RESTRICTIONS

SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

Diameter and

length

j

grip

to be the same

Diameter and

length

grip

to be the same

HT4005-(

Diameter and

grip

NAS 4703-() thru NAS 4716-(

NAS 4803-() thru NAS 4816-(

Diameter and

grip

HT4013-3-3

NAS 1581 A3H3

NAS

1220-(

length

Diameter and

length NAS 1669-

NAS 1669-

L

to be the

NAS 1669-

DL

Diameter and

L

NAS 1669-(

DL

NAS 1669-

DL

Diameter and

)L()

grip

grip

to be the same

Diameter and

length

same

to be the same

Diameter and

length NAS 1669-(

grip

to be the

length NAS 1669-

grip

to be the same

length NAS 1669-

same

grip

to be the same

NAS 1670-

NAS 1670-

L

Diameter and grip length to be the same

NAS 1670-

NAS 1670-

DL

Diameter and

NAS 1670

NAS 1670-

length ()L()

DL

NAS 1669-(

DL(

Diameter and

length NAS 1670-

L

grip

to be the same

grip

to be the same

Diameter and grip length to be the same

Bolt and Blind Bolt Substitutions

Figure 1 (Sheet 2)

EFFECTIVITY:

ALL

51-40-03

Page 2 Jun 1/95

SRM-I

Leariet

STRUCTURAL REPAIR MANUAL HL10

i

i

RESTRICTIONS

SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

HL10(

Pin

i

Diameter and

Hi-Lok

length

Lubricant

HL11- i

i

HL11(

Pin

i

optional

Diameter and

Hi-Lok

length

length

i

i

HL13(

Pin

optional

Diameter and

Hi-Lok

i

length

i

HL18(

Pin

i

i

length

IPin

HL19-

HL20- i

i

Pin

I

Hi-Lok

HL19(

HL20(

i

i

Hi-Lok

I

)Pin

HL21(

Hi-Lok

i

Diameter and

(-5)-()AIC 08L.proC

Air Industries

HL70-(

Hi-Lok Collar

HL70(

HL70-(

Hi-Lok Collar

HL79-(

i

Hi-Lok Collar

Hi-Lok Collar

grip

to be the same

Diameter and

length

HL18-( )-()Pin

grip

to be the same

Diameter and grip length to be the same

length HL21-(

same

optional

Diameter and

Hi-Lok

grip

to be the

Lubricant HLla- i

grip

to be the same

Lubricant HL13

optional

Diameter and

Hi-Lok

HL12(

Pin

i

grip

to be the same

Lubricant

HL12-(

grip

to be the same

grip

to be the same

htgnelpirg

to be the same

Diameter to be the

Substitutable in

Hi-Lok Collar

HL86G-(

HL79-(

Hi-Lok Collar

HL79(

HL79-5 Hi-Lok Collar

HL82-( )Hi-Lok HL86-(

i

Hi-Lok Collar

HL70-5 Hi-Lok Collar

Collar

Hi-Lok Collar

Hi-Lok Collar

)A

HL86G-(

same

same

diameter, except

HL72-(

I

Diameter and

-5 diameter

Diameter to be the

same

Diameter to be the

same

Lubricant

optional

II

Collar

Hi-Lok Collar

HL87-5 Hi-Lok Collar

HL86-5 Hi-Lok Collar

HL90-( )A Hi-Lok Collar

HL90(

i )A Hi-Lok Collar

Lubricant

optional

Lubricant

optional

Diameter to be the

same

Hi-Lok Substitutions

Figure 2 EFFECTIVITY:

ALL

51-40-03

Page SRM-4

3

Jun 1/95

STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

SUBSTITUTE HARDWARE

locking feature, length, material, and finish

Thread size,

NAS1832

SL601-( Shur-Lok Blind Threaded Honeycomb Insert

Shur-Lok

to be the same

locking feature, length, material, and finish

Thread size,

NAS1833

SL602-(

Through

Threaded

to be the same

Insert

Hole size,

NASi834(

SL603-( Shur-Lok

RESTRICTIONS

length and

material to be the

Spool Type

same

Insert

NAS1834(

SL604-( Shur-Lok CSK Spool Honeycomb Insert

)II.(

length and

material to be the

Type

NAS1836

Thread size,

length,

Shur-Lok Blind Threaded

SLGOI-(

NAS1832

Hole size,

same

locking feature,

material and finish

locking feature, and finish material, length,

Thread size,

to be the same

SL602-

NAS1833

Thread size,

locking feature,

length, material,

and finish

to be the same

SLsa3-(

NAS1834(

locking feature, length, material, and finish

Thread size,

to be the same

NAS1834(

)K

SL604-(

Thread size,

locking feature,

length, material, and finish to be the same

locking feature, length, material, and finish

Thread size,

NAS1836(

to be the same

Honeycomb Insert Substitutions Figure 3

I

ALL

1/95 1-40- 3

Page 4 Jun

Learjet

STRUCTURAL REPAIR MANUAL SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

RESTRICTIONS

AN320

hns14145

Size to be the

same

AN320

MS14145L

Size to be the

same

AN340

MS35649

Material 8 size to be

same

AN345

MS35650

Material 8 size to be

same

AN364-( )C

MS21042-(

AN364-( )D

MS21083D(

MS20341-(

MS35649

Material 8 size to be

same

MS20341-(

MS35650

Material 8 size to be

same

I

AN364D

MS21083D(

MS20341

MS35649

Material 8 size to be

same

MS20341-

MS35650

Material 8 size to be

same

MS20364

MS21042

Size to be the

same

MS20364

MS21083N

Size to be the

same

MS20364

A

MS21083N

Size to be the

same

MS20364

C

MS21042

Size to be the

same

MS20364D

MS21083D

Size to be the

same

MS20365

MS21042

Size to be the

same

Nut Substitutions

Figure 4 (Sheet 1)

EFFECTIVITY:

ALL

51-40-03

Page5 SRM-4

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

MS20365

SUBSTITUTE HARDWARE

RESTRICTIONS

MS21044N

Size to be the

same

MS20365

A

MS21044N

Size to be the

same

MS20365

C

MS21042

Size to be the

same

MS20365B

MS21044B

Size to be the

same

MS20365D

MS21044D

Size to be the

same

MS210244N

MS21042

Size to be the

same

MS21042

Size to be the

same

MS21083N

MS21042

Size to be the

same

MS35650-3395

MS35650-3395T

Size to be the

same

MS21045

or

L

NAS395

1

NAS395

3

Size to be the

same

NAS396

1

NAS396

3

Size to be the

same

Size to be the

same

MS21042

NAS679

Nut Substitutions

Figure 4 (Sheet 2)

EFFECTIVITY:

ALL

51-40-03

Page 6 SRM-4

Jun 1/95

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

RESTRICTIONS

SUBSTITUTE HARDWARE

MS21047

NAS 680

Material 8 size to be the

same

MS21049

NAS 681

Material 8 size to be the

same

MS21051

NAS 682

Material 8 size to be the

same

MS21053

NAS 683

Material

size to be the

same

MS21055

NAS 684

Material 8 size to be the

same

MS21057

NAS 685

Material 8 size to be the

same

MS21059

NAS 686

Material 8 size to be the

same

MS21061

NAS 687

Material 8 size to be the

same

MS21062

NAS 687

Material 8 size to be the

same

MS21069

NAS 697

Material 8 size to be the

same

MS21071

NAS 696

Material 8 size to be the

same

MS21073

NAS 698

Material 8 size to be the

same

MS21075

NAS 1068

Material 8 size to be the

same

MS21086

NAS 1067

Material 8 size to be the

same

NAS680A(

MS21047L(

NAS680C(

MS21046-(

NAS680C( )M

MS21048L(

NAS680C(

MK

MS21048L()K

NAS680X(

MS21

NAS681A(

MS21049L(

NAS681C(

MS21

NAS681C()M

MS21050L()

NAS681C(

MK

1

047-(

050-(

MS21050L( )K MS21049-(

NAS681X(

Nutplate Substitutions Figure 5 (Sheet 1)

EFFECTIVITY:

SRM-4

ALL

51-40-03

Page 7 Jun1/95

Learjet STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

SUBSTITUTE HARDWARE

NAS682A(

MS21

NAS682C()

MS21052-(

NAS682C ()M

MS21052L(

NAS682C(

MK

i

051L()

MS21052L( )K

NAS682X(

MS21051-(

NAS683A

MS21053L(

NAS683C(

MS21054-(

NAS683C( )M

MS21054L(

NAS683C ()MK

MS21054L()K

NAS683X(

MS21053-(

NAS684A(

MS21055L(

NAS664C(

MS21056-(

NAS684C()M

MS21056L(

MK

NAS684C(

RESTRICTIONS

MS21056L()K

NAS684X(

MS21055-()

NAS685A(

i

MS21057L()

NAS685C

M521058-(

NAS685C()M

MS21058L(

NAS685C ()MK

MS21058L( )K

NAS685X

MS21059-()

NAS686A(~

MS21060L(

NAS686C()

MS21060-(

NAS686C()M

MS21060L(

Nutplate Substitutions Figure 5 (Sheet 2) EFFECTIVITY:

ALL

51-40-03

Page 8 SRM-4

Jun 1/95

Learjet Learjet

STRUCTURAL REPAIR MANUAL SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

NAS6866C()MK

I

MS21060L()K

NAS686X(

MS21059-(

NAS687A(

MS21 061L(

NAS687C()

MS21062-(

NAS687C()M

I

MS21062L()

NAS687C ()MK

MS21062L( )K

NAS687X(

MS21061-(

NAS696A(

MS21 071L(

NAS696C()

MS21072-(

NAS696C( )M

MS21072L(

NAS696C( )MK

MS21072L( )K

NAS696X()

MS21071-(

NAS697A()

MS21069L(

NAS697C

MS21070-(

NAS697C()M

MS21070L(

NAS697X(

MS21069-(

NAS698A(

MS21073i(

NAS698C(

MS21074-(

NAS698C( )M

MS21074L(

MK

NAS698C(

NAS698X()

RESTRICTIONS

MS21074L( )K MS21073-(

Nutplate Substitutions Figure 5 (Sheet 3) EFFECTZVITY:

ALL

51-40-03

Page 9 Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

MS21086L()

I

NAS1067A( NAS1O67C(

MS21087-(

NAS1067C()M

MS21087L( MS21087L( )K

MK

NAS1067C(

RESTRICTIONS

NAS1067X(

MS21086-(

NAS1O68A(

MS21075L(

NAS1O68C(

MS21076-(

NAS1O68C( )M

MS21076L(

NAS1068X(

MS21075-(

LHA228-

MF60O1-

Size to be the

same

LHA27M2860-

MF6331-

Size to be the

same

221HA27M22-

MF6300-

Size to be the same ("F" or "RM" prefix optional)

52LHA227-(

MF6000-(

Size to be the

MF6000-

RM52LHA227-

Size to be the

same

MF6001-

LHA228-

Size to be the

same

MF6300-

22LHA27M22-

Size to be the

same

MF6331-

LHA27M2860-

Size to be the

same

hnl4sog

M14700E

450"F Max

M146OOH

M14700HE

450"F Max

M14710E

450"F Max

hn14610H

M14710HE

4500F Max

M14620

M14720E

4500F Max

M14620H

M14720HE

450"F Max

same

("RM" prefix optional)

I

M1461O

Nutplate Substitutions Figure 5 (Sheet 4) EFFECTIVITY:

SRM-4

ALL

51-40-03

Page 10 Tun1/95

Learjet Leariet STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

SUBSTITUTE HARDWARE

RESTRICTIONS

M14635H-(

M14735HE

4500F Max

M14600H

M14700HE

4500F Max

M14640

M14740E

450"F Max

M14640H

M14740HE

450"F Max

M14700

M14700E

450"F Max

M14740

M14740E

450"F Max

14600

M14700E

4500F Max

14600H

4600H

Thread size to be the same (approx. 3x weight penalty)

14600H

14700HE-(

450"F Max

14610H

14710HE

4500F Max

14620H-(

14720HE

4500F Max

14650H-(

14750H-( )E

4600

470E

450"F Max

4600H

4700HE

450"F Max

Nutplate Substitutions Figure 5 (Sheet 5) EFFECTIVITY:

ALL

51-40-03

Page 11 SRM-4

Jun 1/95

Learjet IL~l-i´•tl

STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

SUBSTITUTE HARDWARE

Avdel 1204

CR2Ei62 Widedraw

Diameter and

(NAS 523 Code

same

Cherrylock (NAS523 CODE ADD)

CR3214

CR2245 Bulbed

CR2164

Cherrylock AGH)

CR3245

CR2248 Bulbed

Cherrylock

CR3242

CR2249 Bulbed

CR2662

(NAS523 CODE

ARD)

CR3242

Cherrymax (NAS523 CODE ARD) e

CR3243

Cherrymax

Cherrymax CODE ARD)

CR3243

Cherrymax

I

the

Cherrymax

Diameter and

(NAS523 CODE

ACX)

the

Cherrymax

(NAS523 CODE

(BAC

R15FP

CR2249 Bulbed

ARO) E(

Cherrylock

NAS1398B

CR2263 Wiredraw

(NAS523 CODE

RK)

NAS1398D

CR2163 Wiredraw

(NAS523 CODE

RL)

NAS1399C

(NAS523 CODE CR2662 Wiredraw

(NAS523 CODE

RS)

NAS1399D

(NAS523

(NAS523 CODE

CODE

RP)

NAS17388

(NAS523 CODE

AAO)

NAS17398

AAT)

NAS17388

AAO)

NAS17398

AAT)

Cherrylock RS)

the

Diameter and

Diameter and

Diameter and

(NAS523 CODE

(NAS523 CODE

(NAS523 CODE

Cherrylock AAO)

the

Cherrylock PV)

the

Cherrylock ARE)

the

Cherrylock ARD)

the

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

grip length

to be

same

the

(NAS523 CODE

grip length

same

Cherrylock

CR2248 Bulbed

(NAS523 CODE

the

to be

same

PR)

CR2249 Bulbed

(NAS523 CODE

Cherrylock PW)

Diameter and

(NAS523 CODE

CR2248 Bulbed

(NAS523 CODE

the

grip length

same

CR2162 Wiredraw

CR2249 Bulbed

(NAS523 CODE

Cherrylock RK)

to be

same

Diameter and the

grip length

same

Diameter and the

to be

same

CR4622 Wiredraw

CR3252

grip length

same

Diameter and

I

to be the

same

Diameter and the

length

same

Diameter and the

(NAS523

Cherrylock PZ)

Diameter and the

Cherrymax (NAS523 CODE ATK)

PV)

(NAS523 CODE

Cherrylock RS)

Cherrymax (NAS523 CODE ASK)

(NAS523 CODE

(NAS523 CODE

RESTRICTIONS

same

Diameter and same

Diameter and same

Diameter and same

Diameter and same

Rivet and Blind Rivet Substitutions

Figure 6 EFFECTIVITY:

ALL

51-40-03

Page 12 SRM-4

Jun 1/95

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL SPECIFIED HARDWARE

AN507

R

RESTRICTIONS

SUBSTITUTE HARDWARE

MS24693

S

Size and

length to be the same

AN507B

R

MS24693

BE

Size and length to be the

AN507C

R

MS24693

C

Size and

length

to be the same

Size and

length

to be the same

I

same

AN507DD

R

MS24693

A

AN507PB

R

MS24693

CB

Size and

length

to be the

AN507UB

R

MS24693

B

Size and

length

to be the same

Size and

length to

AN509

AN509 AN509

R

R

AN509C

R

AN509DD AN515 AN515

R

R

same

be the

same

MS24694

S

Size and length to be the

same

MS24694

C

Size and

length to

be the

same

MS24694

A

Size and

length to be the

same

MS35206

Size and

length to

be the

same

MS35206

Size and

length to

be the

same

AN515B

R

MS35214

Size and

length to be the same

AN515C

R

MS51957

Size and

length

to be the same

MS35213

Size and

length

to be the

MS35207

Size and

length to be the same

R

AN515DD AN520

R

be the

same

to be the

same

be the

same

Site and length to be the

same

AN520B

R

MS35215

Size and

length to

AN520C

R

MS51953

Size and

length

MS35219

Size and

length to

R

AN520DD AN 530-

RF

AN 530-

R

Material, finish, diameter and

AN 507

MS24693

length AN 509

MS24694

same

R

to be the

same

Material, finish, diameter and

grip length to

be the

same

Screw Substitutions

Figure 7 (Sheet 1) EFFECTIVITY:

ALL

51-40-03

Page SRM-4

13

Jun 1/95

Leariet ~Learjet STRUCTURAL REPAIR MANUAL SUBSTITUTE HARDWARE

SPECIFIED HARDWARE

I

MS27039

NAS 220

RESTRICTIONS

thru

Material, finish, diameter and

NAS 226 AN 515

MS35206-(

grip length R

to be the

Diameter and

same

length

to be

the,

length

to be

the,

length

to be

the,

length

to be

the,

length

to be

the,

length

to be

the,

same

AN 520

MS35207

R

Diameter and same

AN 5158

MS35214

8

Diameter and same

AN 5208

MS35215-(

R

Diameter and same

AN 515C

MS51957

I

R

Diameter and same

AN 520C

MS51958

8

Diameter and same

NAS220-( )thru

MS27039(

Diameter, grip length, and material to be the

NAS226

same

NAS8702

NAS8702U

Grip length

to be the

same

NAS8703

NAS8703U

Grip length

to be the

same

AOL4200

NAS1221

E

Material, diameter and grip

length FAS4200

NAS1221

E

to be the same

Material, diameter and grip

length

to be the same

Screw Substitutions

Figure 7 (Sheet 2) EFFECTIVITY:

ALL

51-40-03

Page SRM-4

14

Jun 1/95

STRUCTURAL REPAIR MANUAL

SPECIFIED HARDWARE

SUBSTITUTE HARDWARE

RESTRICTIONS

AN935

MS35338

Material 8 size to be the

same

AN936

M535333

Material 8 size to be the

same

AN960D-

AN960JD-

Size and thickness to be the same

AN960JD-

AN960PD-

Size and thickness to be the same

MS35333

AN936A

Material 8 size to be the

same

MS35335

AN936B

Material 6 size to be the

same

MS35338

AN935

Material 8 size to be the

same

Washer Substitutions

Figure 8 EFFECTIVITY:

SRM-4

ALL

51-40-03

Page 15 Jun1/95

Learjet

STRUCTURAL REPAIR MANUAL COUNTERSINKING i.

GENERAL A.

For all-around purposes, the micro-stop countersink, fitted with a removable cutter, has been the most efficient countersinking tool for use with portable equipment.

B.

micro-stop countersinking tool rotates on a bearing inside an adjustable locking piece assembly. The foot piece (or stop, as it is often called) threads onto the ~shaft bearing, enabling depth adjustments to be made. Markings, indicating depth differentials in 0.001-inch increments, surround the bevelled circumference of the locking sleeve to aid in depth adjustments. The adjustment is made by pulling the sleeve back and turning the stop to deepen or to shallow the cut. The sleeve is then dropped back into its original position to effect a lock.

proved

The shaft of the sleeve and foot

C. D.

NOTE: E.

The

Ensure that the

locking splines intermesh; only then is the adjustment securely locked.

stop countersink may be adjusted

precautions are

or

set up

on

the

part to

be countersunk

provided

the

following

taken:

(1) Ensure that the adjustable foot piece is extended far enough that the cut will not be too deep. (2) Gradually increase the depth adjustment until the depth and diameter of the hole are the same

as

the size of the fastener head.

(3) If

at all

doubtful of the accuracy of the

adjustment, try

the countersink

piece

on a

of scrap sheet

stock before

F.

G.

using. pilot pin guides the spinning cutter as it cuts into the material. The pilot pin should be approximately 0.002 inch less in diameter than the fastener hole. This allows the cutter to spin without binding in the hole. Cutter-pilots which are more than 0.002 inch smaller than the hole size will allow the cutter to wobble, resulting in a lop-sided countersink. Cutters are available in a variety of cutting angles. 100-degree cutters are most frequently used. The cutting angle is stamped on each cutter as shown in Figure i. The

CAUTION:

ENSURE THAT THE CUTTER IS TIGHTENED IN THE COUNTERSINK SHAFT BEFORE USING THE STOP COUNTERSINK.

H. I.

When the

Keep

the

stop countersinking tool

following

is used, it should be held

rules in mind when

(1) Before using, check countersink

using

the

cutter for

stop

as

shown in

Figure

1.

countersink:

pilot size, sharpness, degrees

of cutter, and true

run-

ning. (2) (3) (4) (5) (6) (7) (8)

Back up the countersink to a safe depth of cut, then Hold countersink at a 90-degree angle to material.

to

proper

setting.

Take full

depth of cut each time. Apply pressure directly behind countersink. Face on the stop countersink must be highly polished to prevent marring the material. Select the size and length fastener to be installed and use it to judge depth of countersink. Do not allow the stop to spin on the material.

EFFECTIVITY: SRM-4

gradually increase depth

ALL

51-40-04

Page 1 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Holding

of

Countersink

Microstop

Adjusting

Tool

of

Microstop

Countersink Tool

Countersink Cutter

Micro-Stop Countersink Figure 1

NOTE: Countersink dimensions in the table are given in terms of the maximum diameter, because this is the most si~nificant dimension in order to avoid too tersink which may produce the riveted material.

a

knife-edge

Minimum countersink diameters

the

are

deep

a coun-

condition in

determined

by

1000

~r

A

1~

a~ i

aerodynamic flushness requirements.

practice, the proper depth of the countersink is determined by driving a test rivet in a scrap piece of metal. The depth adjustment of the micro-stop countersink tool is gradually increased until a countersink depth is obtained that provides the required flushness of a driven rivet. Once the proper countersink adjustIn actual

ment has been established in this manner, the tool

be used for

can

MAXIMUM RIVET

COUNTERSINK

DIAMETER

DIAMETER "A"

1/8

0.200

5/32

0.250

3/16

0.305

1/4

0.405

countersinking on the actual job.

Maximum Countersink Diameter for Shear Head Rivets

Figure 2

EFFECTIVITY:

ALL

51-40-04

Page 2 SRM~

May 15/92

Learjet STRUCTURAL REPAIR MANUAL

DIMPLING MAXIMUM TOTAL SHEET THICKNESS FOR

COUNTERSINKING

DIMPLING WITH STATIONARY SQUEEZERS COIN DIMPLING

Minimum

Joint Rivet

Minimum

Thickness

Minimum

Maximum

Surface

for Sub-CSK

Thickness

Thickness

or

Sheet

When Outer

Screw

Thickness

Sheet Is

Size

For Csk

3/32 1/8 5/32

Conventional

1 or 2

Single

Two

Dimpled

Dimpling

Sheets

Sheet

Sheets

0.032’

0.050

0.040

0.020

0.050

0.063

0.040

0.063

0.050

0.020

0.063

0.063

0.050

0.071

0.063

0.020

0.071

0.071

3/16

0.063

0.080

0.071

0.025

0.071

0.071

1/4

0.071

0.112

0.063

0.032

0.071

0.080

RIVETS

SCREWS 5-32

0.050

0.076

0.050

0.020

0.050

0.063

8-32

0.050

0.084

0.063

0.020

0.071

0.071

10-32

0.063

0.095

0.071

0.032

0.071

0.071

1/4-28

0.071

0.121

0.063

0.032

0.071

0.080

0.071

0.147

5/16-24

0.025 minimum sheet thickness may be countersunk for 3/32 rivets for attachment of skins

specified by repairs

as

well

as

nutplates

when

within this manual.

Maximum and Minimum

Requirements for Countersinking and Dimpling for Flush Rivets and Screws

Figure 3 EFFECTIVITY: SRM~

ALL

51-40-04

Page 3 May 15/92

Learjet ~LearjetJ

STRUCTURAL REPAIR MANUAL MS20426 RIVET DIAMETER SHEET GAGE

1/8

5/32

3/16

114

5/16

3/8

0.040

0.181

0.242

0.309

0.432

0.520

0.650

0.045

0.175

0.236

0.303

0.426

0.514

0.644

0.050

0.170

0.230

0.297

0.420

0.508

0.638

0.056

0.166

0.223

0.290

0.413

0.501

0.631

0.063

0.161

0.216

0.282

0.405

0.493

0.623

0.071

0.158

0.210

0.272

0.395

0.483

0.613

0.080

0.154

0.204

0.263

0.385

0.473

0.603

0.090

0.151

0.199

0.254

0.373

0.461

0.591

0.100

0.149

0.195

0.248

0.361

0.449

0.579

0.112

0.147

0.191

0.242

0.349

0.435

0.565

0.125

0.145

0.188

0.236

0.339

0.422

0.549

0.140

0.143

0.185

0.231

0.330

0.411

0.531

0.160

0.141

0.182

0.226

0.320

0.399

0.512

0.180

0.140

0.179

0.222

0.313

0.389

0.497

0.190

0.139

0.178

0.221

0.310

0.386

0.491

0.200

0.138

0.177

0.219

0.307

0.382

0.485

0.224

0.137

0.175

0.216

0.301

0.375

0.474

0.250

0.136

0.173

0.213

0.296

0.369

0.464

HEAD FLUSH WITH SURFACE

Sheet

Average

Hole

Diameter

Gage

i

Average Hole Diameter of Countersunk Holes Figure 4 EFFECTIVITY: sI1M-a

ALL

51-40-04

Page 4 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Measure

This

NOTE:

Flushness

at

Point

Tolerance limits for the lower

portions of the wing, fuselage, and tail surfaces are the same as the edge of stainless steel nose cup is Zone 1. The

corresponding upper surfaces. Inside nacelle to aft interior of the inlet duct is Zone 2. Rivets

or screw

heads

protruding

heads below the surface

Flushness The heads of flush

on

rivets,

contour to within the

screws,

ZONE

2

3

SRM4

and Hi-Loks

on

are

considered

positive.

Rivets

or screw

negative. as

shown:

the exterior of the aircraft shall be flush with the local skin

tolerances:

DRIVEN

BLIND

RIVETS

SCREWS

RIVETS, HI-LOKS

CAMLOKS

+0.001

+0.002

-0.000

-0.005

+0.005

+0.002

+0.005

-0.000

-0.005

-0.010

+0.005

+0.005

+0.010

-0.000

-0.005

-0.020

Requirements and Tolerances Figure 5 (Sheet 1 of 6)

Flushness

LES1054J

EFFECTIVITY:

above the surface

considered

sharp contours shall be measured

following

1

are

ALL

51-40-04

Page 5 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Zone I

f~

Zone 2 Zone3

I

I

Requirements and Tolerances Figure 5 (Sheet 2 of 6)

Flushness

EFFECTIVITY:

MODEL 23/24SERIESAIRCRAFT

51-40-04

Page SRM-4

6

May.15/92

Learjet ~tl STRUCTURAL REPAIR MANUAL

Zonel Zonel

~j

ZaneBI

I

0000

Requirements and Tolerances Figure 5 (Sheet 3 of 6)

Flushness

EFFECTIVITY: SRM-4

MODEL 25 SERIES AIRCRAFT

51-40-04

Page 7 May 15/92

STRUCTURAL REPAIR MANUAL

Zone 1

~il

Zone 2

Zone3

L_I

0000

Requirements and Tolerances Figure 5 (Sheet 4 of 6)

mushness

LESl054r

EFFECTIVITY: SRM~

MODEL

28/29SERIESAIRCRAFT

51-40-04

Page 8 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Zone 1 Zone 2

Zone 3

1

I

00000

LESl054r

EFFECTIVITY:

Requirements and Tolerances Figure 5 (Sheet 5 of 6)

mushness

MODELSI SERIESAIRCRAFT

51-40-04

Page SRM~

9

May 15/92

Learjet

STRUCTU RAL REPAIR MANUAL

Zone

Zone 2 Zone 3

1

I

0000

LES1054J

EFFECTIVITY: sua~

Plushness

Requirements and Tolerances Figure 5 (Sheet 6 of 6)

MODEL 35/36SERIESAIRCRAFT

51-40-04

Page 10 May 15/92

Learjet STRUCTURAL REPAIR MANUAL AIRCRAFT SUPPORT FOR ALIGNMENT AND REPAIR ALIGNMENT AND SYMMETRY INSPECTION (See

i.

A.

STRUCTURAL IDENTIFICATION

Figure 1.)

Toolsand

Equipment

NOTE:

Equivalent substitutes may be used in lieu of the following:

PART NUMBER

NAME

Scale, 24-inch

MANUFACTURER

USE

Commercially available

Required for point AR

Commercially available

Required for points 3L, 3R,

Machinist type with adapter and level

an

bubble

Scale, 48-inch Machinist type with an

5L, 6L, 5R, and

adapter and level

6R

bubble

Check

6226 Parts 1 thru 4

Contour Boards

2420000

Clinometer

wing and

horizontal

(Wing)

12126 Parts 1 thru 4

stabilizer

2332000-1 (Tail)

contour

2471004

Check

angle

of incidence Steel

Tape,

25 foot

Commercially available

Measure from

points 3LU to

Lightweight Steel Tape

9L, 3RU

to

9R,

and distance between

landing

gear

Commercially available

Plumb Bob

Marking locations

Commercially available

Transit

Elevation

readings Commercially available

Spirit Level

EFFECTIVITY: SRM-4

ALL

Preliminary leveling

51-50-00

Page 1 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL B.

alignment data can be of value in locating deformed structure after a hard landing or seturbulence and/or maneuvers. It should not, however, be considered a criterion for determining structural integrity. In some instances, field checks indicate that an aircraft is out of the tolerances presented, but experience shows that the aircraft may be aerodynamically acceptable because its fly-

The aircraft vere

C.

D.

ing qualities, performance, and handling characteristics meet established criteria. A thorough and searching inspection should be made of the airframe, with particular attention given to fittings where heavy weight masses are carried. A sampling of fasteners may be removed to be examined for evidence of shear and tension deformation. Buckling of stressed skins, which did not exist before the hard landing or high-G maneuver, is cause for careful inspection of the substructure and of the pressurized skins for crack propagation. Skin buckling in itself is not necessarily detrimental structurally if the buckles do not cross a row of rivets and have not loosened any rivets. When adequate inspection reveals the structure to be sound and functional checks of the controls and landing gear (after hard landings) are normal, a check flight will be made. If the results of the structural inspection and flight test are satisfactory, the aircraft is acceptable for flight status. If flight tests indicate the aircraft is either laterally or directionally out of tolerances, and cannot be corrected by rerigging (within the tolerances given in the applicable maintenance manual), a complete alignment check should be made, and results of the alignment check and the flight test should be forwarded to Learjet Field Service for evaluation.

SURFACE ALIGNMENT INSPECTION

2.

A.

Geometry Check (1) The geometry check as illustrated All measurements

B.

are

in

Figure 1 can be made with the aircraft resting on the ground. points illustrated with a steel tape.

taken from the

Elevation Check

(1) To satisfactorily perform

an

elevation check, the aircraft must be drained of all fuel. To

ensure

readings are obtained, an engineer’s level or transit must be used. Preliminary leveling with a spirit level may precede the actual leveling of the aircraft with a transit to place the aircraft in an approximately level position. that correct

EFFECTIVITY: srzM-4

ALL

51-50-00

Page 2 May 15/92

Learjet L~arjet STRUCTU RAL REPAIR MANUAL 3.

LEVEL AND ELEVATION INSPECTION PROCEDURES

A.

Moc~el 23/24 Series Airmaft

Alignment and Symmetry Inspection Personnel must not be

NOTE:

permitted

on or

in the aircraft while the

alignment inspection

is

in progress.

Aircraft shall be

parked

inside

hangar and hangar

doors shall be closed

during

this in-

spection. (1) Level aircraft laterally, longitudinally, and check aircraft elevation, as follows: (a) Defuelaircraft. (Refer to Section I in the appropriate Leajet Service Manual for defueling instructions.) (b) Place aircraft on jacks with landing gear fully extended and clear of hangar floor. Aircraft door shall be closed. (Refer to Section I in the appropriate Learjet Service Manual for jacking

procedures.) (c) Perform preliminary aircraft leveling as follows: 1) Level. laterally by placing level across inboard of the inboard seat rails to obtain

(d) Perform final aircraft leveling 1) Position transit, mounted Shoot

3)

Insert

top surface of

one

level.

follows:

tripod (approximately 24 inches high), at the right aft side required to shoot all check points. lateral leveling points 3L and 3R. Place adapter point in screw heads when hold-

of aircraft

2)

as

seat rails. Place level on

longitudinal leveling. Adjust jacks to

on a

as

ing scale at these locations. phillips head screwdriver through

scale

adapter

and hold in

screw

head at frame

28.

4) 5) 6)

Shoot

longitudinal leveling point BR.

Remove radome

Shoot

cover

and insert scale

adapter through right tooling hole in frame

NOTE:

The

EXAMPLE:

following is an example for leveling an aircraft.

1

Frame Number

2

*Reference Point

3

Scale

4

2+3

5

~4

Reading

23.96 35.46

+11.00

35.46

34.96

0.50

0.50

point

37.00 (frame 28

SRM-4

NOTED

larger

than frame 1

34.96, the forward end of the aircraft (frame 1) is 0.50

Adjust nose jack as required Reference

1

28

Since frame 28 measurement is 35.46 and is ment at

EFFECTIVITY:

1.

longitudinal level point AR.

too low.

for level condition.

23.96 is the distance between WL 13.039 (frame 1 screw

measure-

tooling hole)

and WL

head).

51-50-00

Page 3 May 15/92

STRUCTURAL REPAIR MANUAL NOTE:

Accurate elevations and ond decimal is

7)

required.

recording of check points 5L, 5R, 6L and 6R to the secLocate all scales for large numbers to be at bottom.

Shoot and record elevations of check

NOTE:

See

1 for

Figure

points

points 5L, 6L, 5R and

to locate contour board

6R.

on

upper

wings

and horizontal

stabilizer.

8)

Place contour boards on

wings

at

across

upper

dence at each station in

9)

wing surfaces at points referenced

points specified degrees and on

Place contour board

on

contour

boards;

use a

in

Figure 1. Locate angle of inci-

clinometer and record

minutes.

stabilizer at BL 19.40. Actuate stabilizer until clinometer

board) indicates the stabilizer leading edge is 0030’ down. checks shall be made with the stabilizer in this position. on

contour

10) Place contour boards Locate at

across

points specified

on

upper stabilizer surface at all contour

boards;

use a

points

(placed

All incidence

referenced in

Figure

1.

clinometer and record incidence in de-

grees and minutes.

(e) Measure and record distances from 3LU to 9L and 3RU to 9R. (f) Drop a plumb bob from left main landing gear (LG), right main landing gear (RC), and nose landing gear (NG) to hangar floor and mark locations on hangar floor. Remove Plumb bobs.

(g)

Measure and record distances from 3LU to 9L and from 3RU to 9R.

(h) Remove contour boards, clinometer, and levels from aircraft. (i) Move aircraft, then measure and record distances from NG to LG, from LG

to

RG, and from

RG to NG.

(j)

EFFECTIVITY:

Remove aircraft from

jacks and secure aircraft as desired.

MODEL 23/24 SERIES AIRCRAFT

51-50-00

Page 4 SRM~

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

I\

I II\

3RU-9R

3LU- 9L

3RU

nn

~I

~1 3LU

1: LG

(Opposite)

SYMMETRY CHECK ALIGNMENT WING TO HORIZONTAL STAB. POINTS

DISTANCE

3LU to 9L

D

3RU to 9R

ALIGNMENT

SYMMETRY CHECK

LANDING GEAR POINTS

DISTANCE

NG to LG NG

to

RG

LG to RG

(TYPICAL) Aircraft

Alignment and Symmetry inspection Figure 1 (Sheet 1 of 3)

MODEL23/24 SERIESAIRCRAFT SRM4

5150-00

Fage 5 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

BL 65.60 BL 50.20 BL BL 19.

BR

,o WS 53.15--/

~C

WS 92.52

AR

~3

WS 157. WS 181.1

WING STATION

ANGLEOF

I

LH WING

53.15

STABILIZER INCIDENCE

INCIDENCE RH WING

I

I

i BUFF LINE

1

I

I

LBL19.40

I

I

I

LBL34.80

92.52

1

157.48

1

I

I

I

LBL50.20

181.10

1

I

I

I

LBL65.60

INC.

I

BUTT LINE

INC.

RBL 19.40

I

I

RBL34.80

I

I

RBL50.20

I

I

RBL65.60

ELEVATION CHECK POINTS

POINTS

I

ACTUAL

I

ELEVATION

ELEVATION

I

DIFFERENCE

5L

5R 6L 6R

(TYPICAL) Aircraft

EFFECTIVITY: SRM-4

Alignment and Symmetry Inspection Figure 1 (Sheet 2 of 3)

MODEL 23/24 SERIES AIRCRAFT

51-50-00

Page 6 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

3RU

51’´• ´•´•I´•´•

9R

[SldnSplife)

(TYPICW

BOTTOM OF HORIZONTAL STABILIZER

CTYPICAL)

6R

6L

Opposite TOP OF WING TIP

oo

r

)PylonAccess

OUTED

gR--i

5R 5L

Opposite

FWD

(TYPICAL)

ol

BOTTOM OF WING TIP

(TYPICAL)

UNDERSIDE OF RIGHT PYLON Frame 28

(ReD

--BR AR

(Framel Tool Hole)

(TYPICAL) RIGHT SIDE OF FIISELAGE

NOSE (RADOME REMOVED

Aircraft

EFFECTIVITY:

Alignment and Symmetry Inspection Figure 1 (Sheet 3 of 3)

MODEL 23/24 SERIES AIRCRAFT

51-50-00

Page SRM-Q

7

May 15/92

Learjet

SIRUCTURAL REPAIR MANUAL B.

Mode2 25 Series Aiucraft

Alignment and Symmetry Inspection Personnel must not be

NOTE:

permitted

in the aircraft while the

on or

alignment inspection

is

in progress.

parked

Aircraft shall be

inside

hangar

and

hangar

doors shall be closed

during

this in-

spection. (1) Level aircraft laterally, longitudinally, and check aircraft elevation, as follows: (a) Defuel aircraft. (Refer to the appropriate Learjet Service/Maintenance Manual for instructions.)

(b) Place aircraft

with

jacks

on

defueling

landing gear fully extended and clear of hangar floor. Aircraft appropriate Learjet Service/Maintenance Manual for jack-

door shall be closed. (Refer to the

ing procedures.) (c) Perform preliminary aircraft leveling as follows: 1) Level laterally by placing level across inboard of the inboard seat rails to obtain

(d) Perform final aircraft leveling 1) Position transit, mounted

as

seat rails. Place level

longitudinal leveling. Adjust jacks

on

top surface of

one

to level.

follows:

tripod (approximately 24 inches high), at the right aft side required to shoot all check points. lateral leveling points 3L and 3R. Place adapter point in screw heads when hold-

of aircraft

on a

as

2)

Shoot

3)

ing scale at these locations. Insert phillips head screwdriver through

scale

adapter

and hold in

screw

head at frame

27.

4) 5) 6)

Shoot

longitudinal leveling point BR.

Remove radome

Shoot

cover

longitudinal

NOTE:

The

EXAMPLE:

and insert scale

level

adapter through right tooling hole in frame

following is an example for leveling an aircraft.

1

Frame Number

2

.Reference Point

3

Scale

4

2+3

5

64

Reading

27

35.46

+11.00

35.46

34.36

1.10

1.10

point

36.40 (frame 27

SRM-4

larger

than frame 1

34.36, the forward end of the aircraft (frame 1) is 1.10

Adjust nose jack as required

EFFECTIVITY:

1

23.36

Since frame 27 measurement is 35.46 and is ment at

Reference

1.

point AR.

too low.

for level condition.

23.36 is the distance between WL 13.039 (frame 1 screw

measure-

tooling hole)

and WL

head).

MODEL25 SERIESAIRCRAFT

51-50-00

Page 8 May 15/92

Learjet STRUCTURAL REPAIR MANUAL NOTE:

ond

7)

recording of check points 5L, 5R, 6L and 6R to the secdecimal is required. Locate all scales for large numbers to be at bottom.

Accurate elevations and

Shoot and record elevations of check NOTE:

See

Figure

1 for

points

points 5L, 6L, 5R and 6R.

to locate contour board on

upper

wings

and horizontal

stabilizer. across upper wing surfaces at points referenced in Figure i. Locate wings at points specified on contour boards; use a ciinometer and record angle of incidence at each station in degrees and minutes. 9) Place contour board on stabilizer at BL 19.40. Actuate stabilizer until clinometer (placed All incidence on contour board) indicates the stabilizer leading edge is 0030’ down. checks shall be made with the stabilizer in this position. 10) Place contour boards across upper stabilizer surface at all points referenced in Figure 1. Locate at points specified on contour boards; use a clinometer and record incidence in de-

8)

Place contour boards on

grees and minutes.

(e) Measure and record distances from 3LU to 9L and 3RU to 9R. (O Drop a plumb bob from left main landing gear (LG), right main landing gear (RG), and nose landing gear (NG) to hangar floor and mark locations on hangar floor. Remove plumb bobs.

(g)

Measure and record distances from 3LU to 9L and from 3RU to 9R.

(h) Remove contour boards, clinometer, and levels from aircraft. (i) Move aircraft, then measure and record distances from NG to LG, from LG

to

RG, and from

RG to NG.

(j)

EFFECTIVITY: SRM-4

Remove aircraft from

jacks and

secure

MODEL 25 SERIES AIRCRAFI~

aircraft

as

desired.

51-50-00

Page 9 May 15/92

Learjet

STRUCTURAL REPAIR MAMUAL 9R

111\

3RU-9R

3LU-9L

3RU

II ~Y

qi 3LU

a

RG LG

(Opposite)

NC

j-/

ALIGNMENT

SYMMETRY CHECK

WING TO HORIZONTAL STAB. POINTS

DISTANCE

3LU to 9L 3RU to 9R

ALIGNMENT

SYMMETRY CHECK

LANDING GEAR POINTS

DISTANCE

NG to LG NG to RG LG to RG

Aircraft

EFFECTTVITY: SRM~

Alignment and Symmetry Inspection Figure 1 (Sheet 1 of 3)

MODEL25 SERIESAIRCRAFT

51-50-00

Page 10 May 15/92

E~ Learjet ~´•rptl STRUCTURAL REPAIR MANUAL

BL 65.60 BL 50 BL 34.80

BL 19.40

BR

x

x

O

AR--\ Ws92.52---( WS 157. WS 181.10

WING

ANGLE OF

STATION

INCIDENCE

STABILIZER INCIDENCE

RH WING

LH WING

I

IBUTTLINE

I

BUTTLINE

I

I

RBL19.40

I

I

RBL34.80

INC.

53.15

1

I

I

I

LBL19.40

92.52

1

I

I

I

LBL34.80

157.48

1

I

I

I

LBL50.20

RBL 50.20

181.10

I

I

I

I

LBL65.60

RBL 65.60

INC.

ELEVATION CHECK POINTS

POINTS

I

ACTUAL

I

ELEVATION

ELEVATION

I

DIFFlERENCE

5L 5R 6L

6R

Aircraft

EFFECTNITY: SRM~

Alignment and Symmetry Inspection Figure 1 (Sheet 2 of 3)

MODEL 25 SERIESAIRCRAFT

51-50-00

Page 11 May 15/92

Lear

STRUCTURAL REPAIR MANUAL i´•

3RU 9R

(SldnSplice) BOTTOM OF_HORIZOIV~AL STABILrZER

bR 6L

(TYPICAL)

Opposite

TOP OF WING_TIP ooo

~d0

Oe@b~

000

do o

o

o

~T,

r

OUTED

)-Py~on Access

3R´•´•

5R SL

a,

Opposite

n,

FWD

a

9

(TMJrCAL)

ooooo

ol

(TYPICALI

BOTTOM OF WING TIP

UNDE~RSIDE: OF RIGHT PYLON Frame 28

...:I;

i

(c---- BR AR

(Rame 1 TooI Hole)

O

Q

(TYPICAL) RIGF~ SIDE OF FUSE~AGE

Aircraft

EFFECTIVITY: SRM-P

NOSE_(RADOMB REMOVED

Aiignmenf and Symmetry Inspection Figure 1 (Sheet 3 of 3)

MODEL 25 SERIES AIRCRAFT

51-50-00

rage 12 May 15/92

Learjet STRUCTURAL REPAIR MANUAL C.

Model 28/29 Series Aircraft

Alignment and Symmetry Inspection Personnel must not be

NOTE:

permitted

on or

in the aircraft while the

alignment inspection

is

in progress.

Aircraft shall be

parked

inside

hangar and hangar

doors shall be closed

during this

in-

spection. (1) Level aircraft laterally, longitudinally, and check aircraft elevation, as follows: (a) Defuel aircraft. (Refer to Chapter 28 in the appropriate Learjet Maintenance Manual for defueling instructions.)

(b) Place aircraft

on

landing gear fully extended and clear (Refer to Chapter 7 in the appropriate Learjet

jacks

door shall be closed.

with

of

hangar

floor. Aircraft

Maintenance Manual for

jacking procedures.) (c) Perform preliminary aircraft leveling as follows: 1) Level laterally by placing level across inboard seat rails. Place level on top surface of one of the inboard seat rails to obtain longitudinal leveling. Adjust jacks to level. (d) Perform final aircraft leveling as follows: 1) Position transit, mounted on a tripod (approximately 24 inches high), at the right aft side of aircraft as required to shoot all check points. 2) Shoot lateral leveling points 3L and 3R. Place adapter point in screw heads when holding scale at these locations. 3) Insert phillips head screwdriver through scale adapter and hold in screw head at frame 27.

4) 5) 6)

Shootlongitudinal levelingpointBR. Remove radome

cover

and insert scale

adapter through right tooling hole in frame

1.

Shootlongitudinal level pointAR. NOTE:

The

EXAMPLE:

following is an example

1

Frame Number

2

*Reference Point

3

Scale

4

2+3

5

44

Reading

for

leveling an aircraft.

27

1

23.36 35.43

+11.00

35.43

34.33

1.10

1.10

Since frame 27 measurement is 35.43 and is

larger

than frame 1

measure-

34.33, the forward end of the aircraft (frame 1) is 1.10 too low. nose jack as required for level condition.

ment at

Adjust Reference

point 23.36 is

36.40 (frame 27

EFFECTIVITY: SRM-I

screw

the distance between WL 13.039 (frame 1

tooling hole)

and WL

head).

MODEL 28/29 SERIES AIRCRAFT

51-50-00

Page 13 May 15/92

Learjet Learjet

STRUCTURAL REPAIR MANUAL NOTE:

7)

recording of check points 5L, 5R, 6L and 6R to the secrequired. Locate all scales for large numbers to be at bottom.

Accurate elevations and ond decimal is

Shoot and record elevations of check NOTE:

See

1 for

Figure

points

points 5L, 6L, 5R and

6R.

to locate contour board on

upper

wings

and horizontal

stabilizer.

8)

Place contour boards on

9)

wings

at

across

points specified

upper on

wing surfaces at points referenced

contour

boards;

use a

in

Figure 1. Locate angle of inci-

clinometer and record

dence at each station in

degrees and minutes.

Place contour board

stabilizer at BL 19.40. Actuate stabilizer until clinometer

on

board) indicates the stabilizer leading edge is -1030’ down. checks shall be made with the stabilizer in this position. on

contour

10) Mace

contour boards across

Locate at

points specified

on

upper stabilizer surface at all contour

boards;

use a

points

(placed

All incidence

referenced in

Figure

1.

clinometer and record incidence in de-

grees and minutes. (e) Drop a plumb bob from left main landing gear (LG), right main landing gear (RG), and nose landing gear (NG) to hangar floor and mark locations on hangar floor. Remove plumb bobs.

(f)

Measure and record distances from

point 9L to points 3LU, 4LW, 5LW, 6LW, point 9R to points 3RU, 4RW, 5RW, 6RW, and 7RW.

Remove contour boards, clinometer, and levels from aircraft. (h) Move aircraft, then measure and record distances from NC to LG, from LG

and nW, and

(g)

to

RG, and from

RG to NC;.

(i)

EFFECTIVITY: SRM´•I

Remove aircraft from

jacks and

secure

MODEL 28/29 SERIES AIRCRAFT

aircraft

as

desired.

51-50-00

Page 14 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL -r:

9R

~r

’3~9L

9R-3RU

/----9L-3LU

i

9R-4RW---\

J~M

/---9L-4LW

II-I\

9R-5RW----------\ 9R

9R-7RW------~

I I I

/--9L-7LW

7LW 6R

5RW

5LW

iln 4RW

4LW 3RU

3LU

B

n

Re LG

ALIGNMENT

Opposite

SYMMETRY CHECK

WING TO HORIZONTAL STAB. DISTANCE

POINTS

I

ALIGNMENT

DISTANCE

POINTS

SYMMETRY CHECK

LANDING GEAR

9LtoBLU

9Rto3RU

9L to 4LW

9R to 4RW 9Rto5RW

9L to 5LW

9Lto6LW

I

I

9Rto6RW

9LtonW

I

I

9Rto7RW

POINTS

I

sud~

I

NG to LG NG to RG

I

Aircraft

EFFECTIVITY:

I

DISTANCE

I

I

LG to RG

Alignment and Symmetry Inspection Figure 1 (Sheet 1 of 4)

MODEL 28/29SERIESAIRCRAFT

51-50-00

Page 15 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL BL 55.

BL 50.2 BL 34. BL 19.

BR

30

WS 53. 15 WS 92.52

WS 157.48 WS 181. 1 WS 213.60

WING

STATION

I I

ANGLE OF

LH WING

1

53.15

STABILIZER INCIDENCE

INCIDENCE

I

I

I BUTF LINE

I

I

I

LBL19.40

RBL 19.40

RH WING

INC.

I

BUTTLINE

92.52

1

I

I

I

LBL34.80

RBL 34.80

157.48

1

I

I

I

LBL50.20

RBL 50.20

191.10

1

I

I

I

LBL65.60

RBL 65.60

INC.

213.60 ELEVATION CHECK POINTS ACTUAL

LEVELING POINT ELEVATIONS

POINTS

FRAME 1 AR*

I

I

I

5L

FRAME 27 BR

I

I

I

5R

L WING 3L

I

I

I

6L

R WING 3R

I

I

I

6R

I

ELEVATION

I I

ELEVATION DIFFERENCE

LONGITUDINAL

LATERAL

Aircraft

EFFECTNITY:

Alignment and Symmetry Inspection Figure 1 gheet 2 of 4)

MODEL 28/29 SERIES AIRCRAFT

51-50-00

Page SRM´•4

16

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

6L

Opposite

AR(Framel 01

Tool Hole)

000 010

60

oo

o

olo

0

8 o~o

o

o

o

a

o

Pylon

pq

Access

NOSE (RAD_OME_REMOVET)) 5n

FWD

5L

Opposite

oo

Frame 28

Frame 27

(Ref)

(ReD

Sp""’

I

Frame 26

(Iief) (Skin splice)

Pylon

00C)00 ol

o

O

0

0

o

UNDERSIDE OF RIGHT PYLON WL 36.40

BR

(Screwhead)

FWDI RIGHT SIDE OF FUSELAGE

Aircraft

EFFECTIVITY: SRM-4

Alignment and Symmetry Inspection Figure 1 (Sheet 3 of 4)

MODEL28/29 SERIESAIRCRAET

51-50-00

Page 17 May 15/92

Learjet STRU~TURAL REPAIR MANUAL ~tuo

BL 80.35

6RW

(Ref)

6LW

(Skin

Opposite Splice) 7RW 7LW

9R

9L

(Skin

Opposite Splice)

Opposite Splice)

(Skin

Winglet Sta 44.87 (Ref)

CFWD

UNDERSIDE OF RIGHT HORIZONTAL STABILIZER

Winglet Sta

17.817

(ReO 4RW

5RW

Opposite (Skin Splice)

5LW

4LW

Opposite Winglet Sta 6.00 (Ref)

LOOKING OUTBOARD AT RIGHT WINGLET

WS 181.10

(Ref) WS 181.10

(Ref)

3R

3RU 3LU

o

8

o

a

3L

Opposite

o

O o

s,~NBD

rINBD

o

e

a

a

Opposite

o

cs

FWD

a

FWD

Leading Edge

Leading Edge

UPPER SURFACE OF WING

Aircraft

EFFECTIVITY: sRM-b

V

~Scrupper

UNDERSIDE OF WING

Alignment and Symmetry Inspection Figure 1 (Sheet 4 of 4)

MODEL 28/29SERIESAIRCRAFT

51-50-00

Page 18 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL D.

Model 31 Series Aircraft

Alignment and Symmetry Inspection Personnel must not be

NOTE:

permitted

on or

in the aircraft while the

alignment inspection

is

in progress.

parked

Aircraft shall be

inside

hangar and hangar

doors shall be closed

during this

in-

spection. (1) Level aircraft laterally, longitudinally, and check aircraft elevation, as follows: (a) Defuel aircraft. (Refer to Chapter 28 in the appropriate Learjet Maintenance Manual for defueling instructions.) Cb) Place aircraft

landing gear fully extended and clear (Refer to Chapter 7 in the appropriate Learjet with

jacks

on

door shall be closed.

of

hangar

floor. Aircraft

Maintenance Manual for

jacking procedures.) (C) Perform preliminary aircraft leveling 1)

Level

laterally by placing

level

as

3)

inboard seat rails. Place level

longitudinal leveling. Adjust jacks

on

top surface of

one

to level.

follows:

tripod (approximately 24 inches high), at the right aft side of aircraft as required points. Shoot lateral leveling points 3L and 3R. Place adapter point in screw heads when holding scale at these locations. Insert phillips head screwdriver through scale adapter and hold in screw head at frame on a

to shoot

2)

follows:

across

of the inboard seat rails to obtain

(d) Perform final aircraft leveling 1) Position transit, mounted

as

all check

27.

longitudinal leveling point BR.

4)

Shoot

5) 6)

Remove radome

Shoot

cover

longitudinal

NOTE:

The

and insert scale

level

point

following is an example

1

Frame Number

2

*Reference Point

3

Scale

4

2+3

Reading

5 EXAMPLE:

point

36.40 (frame 27

EFFECTIVITY: SRM-4

in frame 1.

for

leveling an aircraft.

27

1

23.36 35.46

+11.00

35.46

34.36

1.10

1.10

Since frame 27 measurement is 35.46 and is larger than frame 1 measurement at 34.36, the forward end of the aircraft (frame 1) is 1.10 too low.

Adjust Reference

adapter through right tooling hole

AR.

nose

jack

as

required

for level condition.

23.36 is the distance between WL 13.039 (frame 1 screw

tooling hole)

and WL

head).

MODEL31 SERIESAIRCRAFT

51-50-00

Page 19 May 15/92

Learjet STRU~TURAL REPAIR MANUAL NOTE:

7)

recording of check points 5L, 5R, 6L and 6R to the secrecluired. Locate all scales for large numbers to be at bottom.

Accurate elevations and ond decimal is

Shoot and record elevations of check NOTE:

See

1 for

Figure

poi"ts

points 5L, 6L, 5R and

to locate contour board

6R.

on

upper

wings

and horizontal

stabilizer.

8)

Place contour boards

across

upper

wing

surfaces at

wings at points specified on contour boards; dence at each station in degrees and minutes. on

9)

Place contour board

points

use a

referenced in

Figure

clinometer and record

1. Locate

angle of inci-

stabilizer at BL 19.40. Actuate stabilizer until clinometer

(placed leading edge is -20 (+0; -15’) down. All incidence checks shall be Inade with the stabilizer in this position. 10) Mace contour boards across upper stabilizer surface at all points referenced in Figure 1. Locate at points specified on contour boards; use a clinometer and record incidence in deon

on

contour board) indicates the stabilizer

grees and minutes. (e) Drop a plumb bob from left main landing gear (LG), right main landing gear (RG), and nose landing gear (NG) to hanger floor and mark locations on hangar floor. Remove plumb bobs.

(f)

Measure and record distances from

(g)

point points 3RU, 4RW, 5RW, 6RW, and 7RW. Remove contour boards, clinometcr, and levels ~om aircraft.

point

9L to

points 3LU, 4LW, 5LW, 6LW,

and nW, and

9R to

(h) Move aircraft, then

measure

and record distances from NC to

LG, from LG

to

RG, and from

RG to NG.

(i)

EFFECTIVITY: sr~M1!

Remove aircraft from

jacks and

secure

MODEL31 SERIESAIRCRAFT

aircraft

as

desired.

51-50-00

Page 20 May ’15/92

Learjet

STRUCTURAL REPAIR MANUAL ~-----9L

II

9R-3RU

\P~

9L-3LU 9L-4LW

9R-4RW~

S)LSLW

9R-5RW~

II I

9R-6RW~

~9L-6LW

\I I I \I

9R-7RW~

I

7RW~

5RW/

I

\V

\~iT(

\IVI I

I

II

L_7

II

/7LW

II

V~6LW

I

4RW

5LW

\Il

-1

I

4LW

i’

3LU

RU

RC LG OPPOSITE

NG

SYMMETRY CHECK ALIGNMENT WING TO HORIZONTAL STAB.

DISTANCE

POINTS

I

ALIGNMENT

DISTANCE

POINTS

SYMMETRY CHECK

LANDING GEAR 9Lto3LU

I

I

9RtoSRU

9Lto4LW

I

I

9RtoQRW

9L to 5LW

POINTS

9RtoSRW

I

I

I

DISTANCE

NG to LG

NG to RG 9L to 6LW

9R to 6RW

9L to nw

9Rto7RW

I

Aircraft

EFFECTIVITY:

I

I

LG to RG

Alignment and Symmetry Inspection Figure 1 (Sheet 1 of 4)

MODEL31 SERIESAIRCRAF~

51-50-00

Page SRM-P

21

May 15/92

Learjet STRUCTURAL REPAIR MANUAL

BL 65. BL 50.20

BL BL 19.

BR

3R

O AR

O

O

CI

O

/Z~

32~

~3L

WS 53.1 WS 92.52

WS 157.

WS 181.10 WS 213.60 i

WING

I

ANGLE OF

STATION

I

INCIDENCE LH WING

I

STABILIZER INCIDENCE

RH WING

I

I PUTT LINE

INC.

I

BUTTLINE

53.15

1

I

I

I

LBL19.40

I

I

RBL19.40

92.52

1

I

I

I

LBL3Q.80

I

I

RBL34.80

157.48

1

I

I

I

LBL50.20

I

I

RBL50.20

181.10

1

I

I

LBL65.60

I

I

RBL65.60

INC.

213.60 ELEVATION CHECK POINTS

LEVELING POINT ELEVATIONS

POINTS

FRAME 1 AR"

I

I

I

5L

FRAME 27 BR

I

I

I

5R

I

I

I

6R

I

ACTUAL

I

ELEVATION

ELEVATION

I

DIFFERENCE

LONGITUDINAL 6L

LWWG3L

LATERAL

R WING 3R

AiTrraft

EFFECTIVITY: SRM4

Alignment and Slymmehy Inspection Figure 1 (Sheet 2 of 4)

MODEL31 SERIESAIRCRAFT

51-50-00

Fage 22 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

(Skin

Frame28

Frame27

Frame26

(Ref)

(Ref)

(Ref)

Splice) Pylon (Skin

6R

/I

6~

ii

Opposite

WL36.40-

Splice)

..1..

(Ref) ooo

o

oo

do

´•lo

r

o

BR

o

o o

OUTED

1_1

o

(Screwhead)

Access

Pylon

RIGHT SIDE OF FUSELAGE

5R 5L

FWD

Opposite

II.

ooo~oo ooooo

(TYPICAL)

UNDERSIDE OF RIGHT PnON

AR

(Frame 1 Tool Hole)

O

Q

NOSE (RADOME REMOVED

Aircraft

EFFECTIVITY: SRM-4

Alignment and Symmetry Inspection Figure 1 (Sheet 3 of 4)

MODEL31 SERIESAIRCRAFT~

51-50-00

Page 23 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL 3~3

BL80.35 (Ref)

6RW 6LW

(Skin

Opposite Splice) 7RW 7LW

9R 9L

Opposite

(Skin Splice)

Opposite

(Skin Splice)

Winglct Sta 44.87 (Ref)

CFWO

UNDERSIDE OF RIGHT

HORIZONTAL STABILIZER

Winglet Sta

17.817

(Ref)

4RW

5RW

Opposite (Skin Splice)

4LW

5LW

Opposite Winglet Sta

6.00

(Ref)

LOOKING OUTBOARD AT RIGHT WINGLET

WS 181.10

WS 181.10

(Ref)

(Ref) 3R

3RU O

~o

3LU

o

o

3L

Opposite

ol~

o

o

o O

o

ao e

cs

B~e a

rINBD

s,

a

e

a

INBD

o

g

FWD

FWD

Leading Edge

LeadingEdge-/

UPPER SURFACE OF WING

Aircraft

EFFECTIVITY: SRM~I

Opposi~e

o

V

~Scrupper

UNDERSIDE OF WING

Alignment and Symmetry Inspection Figure 1 (Sheet 4 of 4)

MODEL31 SFRIFSAIPCPAFT

51-50-00

Page 24 May 15/92

Learjet ~LBarjet

SIRUCTURAL REPAIR MANUAL E.

Model 35/36 Series Airmaft

Alignment and Symmetry Inspection Personnel must not be

NOTE:

permitted

on or

in the aircraft while the

alignment inspection

is

in progress.

parked

Aircraft shall be

inside

hangar and hangar

doors shall be closed

during

this in-

spection. (1) Level aircraft laterally, longitudinally, and check aircraft elevation, as follows: (a) Defuel aircraft. (Refer to Chapter 28 in the appropriate Learjet Maintenance Manual for defueling instructions.) (b) Place aircraft

jacks

on

with

landing gear fully extended and clear Chapter 7 in the appropriate Learjet

door shall be closed. (Refer to

of

hangar

floor. Aircraft

Maintenance Manual for

jacking procedures.) (c) Perform preliminary aircraft leveling as follows: 1) Level laterally by placing level across inboard

seat rails. Place level

on

top surface of

of the inboard seat rails to obtain longitudinal leveling. Adjust jacks to level. (d) Perform final aircraft leveling as follows: 1) Position transit, mounted on a tripod (approximately 24 inches high), at the of aircraft

2)

Shoot lateral

ing 3)

to shoot all check

as

required leveling points

right aft

one

side

points.

3L and 3R. Place

adapter point

in

screw

heads when hold-

scale at these locations.

Insert

phillips

head screwdriver

scale

through

adapter

and hold in

screw

head at frame

27.

4)

Shootlongitudinal levelingpointBR.

5) 6)

Remove radome

Shoot

cover

longitudinal

NOTE:

The

EXAMPLE:

and insert scale

level

point

following is an example

1

Frame Number

2

*Reference Point

3

Scale

4

2+3

5

~4

adapter through right tooling hole

Reading

for

leveling an aircraft.

23.36

35.46

+11.00

35.46

34.36

1.10

1.10

point

36.40 (frame 27

EFFECTIVITY: SRM-4

larger

than frame 1

34.96, the forward end of the aircraft (frame 1) is 1.10

Adjust nose jack as required Reference

1

27

Since frame 27 measurement is 35.46 and is ment at

measure-

too low.

for level condition.

23.36 is the distance between WL 13.039 (frame 1

screw

in frame 1.

AR.

tooling hole)

and WL

head).

MODEL35/36SERIES AIRCRAFT

51-50-00

Page 25 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL NOTE:

Accurate elevations and ond decimal is

7)

rccluired.

recording of check points 5L, 5R, 6L and 6R to the secLocate all scales for large numbers to be at bottom.

Shoot and record elevations of check NOTE:

See

Figure

1 for

points

points 5L, 6L, 5R and

to locate contour board

6R.

on

upper

wings

and horizontal

stabilizer.

8)

Place contour boards

across upper wing surfaces at points referenced in Figure i. Locate wings at points specified on contour boards; use a clinometer and record angle of incidence at each station in degrees and minutes. 9) Place contour board on stabilizer at BL 19.40. Actuate stabilizer until clinometer (placed on contour board) indicates the stabilizer leading edge is -1040’ down. All incidence checks shall be made with the stabilizer in this position. 10) Place contour boards across upper stabilizer surface at all points referenced in Figure 1. Locate at points specified on contour boards; use a clinometer and record incidence in deon

grees and minutes.

(e) Drop

a plumb bob from left maiII landing gear (LG), right main landing gear (RG), and nose landing gear (NG) to hangar floor and mark locations on hangar floor. Remove plumb bobs. (f) Measure and record distances from point 9L to 3LU, and from point 9R to 3RU. (g) Remove contour boards, clinometer, and levels from aircraft.

(h) Move aircraft, then

measure

and record distances from NG to

LG, from LG

to

RG, and from

RG to NG.

(i)

EFFECTIVITY: SRM41

Remove aircraft from

jacks and

secure

MODEL 35/36SERIES AIRCRAFT

aircraft

as

desired.

51-50-00

Page 26 May 15/92

Leariet ~Learptl STRUCTURAL REPAIR MANUAL la´•-- st

9R---?r;

II I\

3RU- 9R

3LU- 9L

I 3LU

RG

LG(Opposite)

F~

I

NG

ALIGNMENT

SYMMETRY CHECK

WING TO HORIZONTAL STAB. DISTANCE

POINTS 3LU to 9L 3RU to 9R

ALIGNMENT

SYMMETRY CHECK

LANDING GEAR

I

POINTS

I

DISTANCE

NG to LG NG to RC LG to RG

Aircraft

EFFECTIVITY: srzM~

MODEL

~Alignment and Symmetry Inspection Figure 1 (Sheet 1 of 3)

35/36SERIESIURCRAF~

51-50-00

Page 27 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

BL 65.

si 50.20 BL BL 19.40 BR

O

O

O

WS 53.15 WS 92.52"

~e

WS 157.48

AR.

WS 182.1

WS 205.1

ANGLE OF

WING STATION

I

INCIDENCE LHWING

I

STABILIZER INCIDENCE

RHWING

I

BUTL LINE

I

RBL19.40

I

I

RBL34.80

I

I

RBL50.20

53.15

1

I

I

I BUTT LINE

92.52

1

I

I

I

LBL19.40

I

157.48

1

I

I

I

LBL34.80

181.10

I

I

I

I

LBL50.20

I

I

LBL65.60

I

213.60

INC.

INC.

RBL65.60

ELEVATION CHECK POINTS

POINTS

I

ACTUAL

I

ELEVATION

ELEVATION

I

DIFFERENCE

5L 5R 6L 6R

Aircraft

Em~ECTTVITY: SRM-4

Alignment and Symmetry Inspection Figure 1 (Sheet 2 of 3)

MODEL 35/36SERTES AIRCRA~

51-50-00

Page 28 May 15/92

STRUCTURAL REPRIR MANUAL

~R (Skin

(TYPICAL)

FWD

1~1 Splice)

BO’ITOM OF HORIZONTAL STABILIZER

3RU

Tip Tank (TYPICAL)

6R 6L

Opposite

TOP OF WING TIP EXTENSION

~90@ o~o

FWD

r

OUTED

~Pylon Access 5R

5L

Opposite

FWD

Tip Tank (TYPICAL) oo

ol

BOTTOM OF WING TIP EXTENSION

(TMJICAL)

UNDERSIDE OF RIGHT PYLON Frame 27

(Ref)

BR

~3

AR

(Frame

1

Tool Hole)

(TYPICAL)

g~a ~-e

NOSE (RADOME REMOVED

RIGHT SIDE OF FUSELAGE

Aircraft

EFFECTIVITY:

Alignment and Symmetry Inspection Figure 1 (Sheet 3 of 3)

MODEL 35/36SERIES AIRCRAFT

51-50-00

Page 29 s~M-a

May 15/92

Learjet STRUCTURAL REPAIR MANUAL 4.

SUPPORT A.

See

EQUIPMENT FOR AIRCRAFT REPAIR

Figure 2

NOTE:

for aircraft support

equipment.

Equivalent substitutes may be used in lieu

NAME

PART NUMBER

of the

following:

MANUFACTURER

USE

Jack Pad

2370102-4 (1 ea)

Learjet Inc.

Jacking aircraft

Jack Pads

2572006-3 (2 ea)

Learjet Inc.

Jacking aircraft

Tailstand

2471016-1

Learjet Inc.

Jacking aircraft

Tailstand*

3170002

Learjet Inc.

Jacking aircraft

Tripod Tacks

02-0526-0100 (3 ea.)

Tronair

Jacking aircraft

(Minimum capacity

Holland, OH

of10,0001bs.)

Spreader Bar

2311600-500

Learjet Inc.

Aircraft

Wing Mating Dolly

2420000

Learjet Inc.

Wing support

Wing Transfer Dolly

2300001

Learjet Inc.

Wing support

Pylon Jack Adapters**

3170003 (2 ea.)

Learjet Inc.

Jacking aircraft without wings Or engines

Commercially available

Jacking aircraft without wings or

Pylon Jacks (5 ton, height 64")

support

engines Keel Beam

Dolly

Learjet Inc.

Keel beam sup-

port

Engine Stand

PME 500006

Learjet Inc.

Engine support

Engine Hoist

04-0308-0112

Tronair

Engine lift

Holland, OH

Engine Sling

OHME 2650000

Learjet Inc.

Engine lift

Model 31 Series Aircraft only Model 31/35/36 Series Aircraft onlu

EFFECTIVITY: SRM-4

ALL

51-50-00

Page 30 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

~jC

Jack

lack

Nose Jack Pad

Wing Jack

Pad

(TYPICAL)

WINGIACK

NOSETACK

Aircraft

Support Equipment Figure 2 (Sheet 1 of 5)

EFFECTIVITY: SRM-4

ALL

51-50-00

Page 31 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Adjusting Nut

Spreader Bar

Mounting Pad

(Install spreader bar between keel beam mounting Dads

on

fuselage)

SPREADER BAR

Jack

WING TRANSFER DOLLY

Aircraft

Support Equipment Figure 2 (Sheet 2 of 5)

EFFECTIVITY: SRM-4

ALL

51-50-00

Page 32 May 15/92

Learjet Learjet

STRUCIURAL REPAIR MANUAL

Safety Pin

WING MATING DOLLY

Keel Beam

Wheel Well Doors

KEEL.BEAM SUPPORT DOLLY

Aircraft

Support Equipment Figure 2 (Sheet 3 of 5)

EFFECTIVITY:

ALL

51-50-00

Page 33 May 15/92

Learjet

STRU~TURAL R~PAIR MANUAL Engine Hoist

Engine Sling I

Forward

Sling

Arms (Attach

Sling Arms Equally Spaced From \Centerline)

AN6-28 Bolts

Sling Arm (Centered on Engine

Aft

1

(2

Required)

Centerline) AN6-8 Bolts (2 Required)

qli! ~ic Two holes

are

provided

for attachment of

hoist. The forward hole is for

engines

without thrust reversers and the aft hole is for engine with thrust reversers.

Forward

Engine

Mount (Slave)

NAS1307-3H Bolt AN960-716 Washer

(2

Required)

Engine Stand I~F Do Not Remove

Engine

Mount from Aircraft

(TYPICAL) Aircraft Support

Equipment Figure 2 (Sheet 4 of 5)

EFFECTIVITY: SRM-4

MODEL 31/35/36 SERIES AIRCRAFT

51-50-00

Page 34 May 15/92

Learjet STRUCTURAL RE:PAIR MANUAL

Pylon Jack Pad

PYLON TACK

Aircraft

Support Equipment Figure 2 (Sheet 5 of 5)

EFFECTIVITY:

MODEL 31/35/36SERIES AIRCRAFT

51-50-00

Page 35 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL REPAIRS-GENERAL 1.

GENERAL A.

of the airframe structure

are similar in design and fabrication. Typical repairs to compiled in this section to eliminate the duplication of repairs under each applicable component. Repairs in this section apply to the member shown regardless of location on the aircraft structure (except as limited) and will include only those parts or members necessary to show the typical situation. Typical repairs may be accomplished individually, or combined with other repairs for a major repair. Technique and material variation is permissible only so far as to facilitate fabrication and ensure the original strength and usefulness of the affected component. It is the responsibility of the aircraft owner/maintenance facility to determine qualifications of maintenance personnel performing inspections and repair procedures as well as to ensure all aircraft log books are properly updated following any maintenance or repair to aircraft structure. As always, a clean environment and good general shop practices shall be exercised at all times. Prior to, and after performing, any repairs on the aircraft structure, ensure serviceability and reliability of repair. If serviceability and/or reliability of repair remains in question or if guidance is needed in making this determination, contact Learjet Field Service for additional information. Repairs for structure not included in this section does not necessarily indicate that the structure involved is non-repairable, but that the application of a typical repair procedure to theoretical damage has not yet been developed. For repair procedures pertaining to items not covered in this section, refer to that items respective chapter. If material added in the course of a repair obstructs drainage holes, the holes must be continued through the repaired member unless this is likely to cause structural weakness. If the original holes cannot be used new drainage holes must be made as near as possible to the original ones. The drainage efficiency of a repaired component must be checked during the course of repair. Any drainage holes in the original structure must be duplicated in the replacement structure. Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. Cracks in any fitting or forging are not allowed. Fittings or forgings with bushings shall be repaired. All parts fabricated by the repair facility shall be identified for future reference. Marking of parts shall be accomplished in a manner which does not effect the serviceability and reliability of the part. Classification of Repairs (1) Specific Repairs (a) Repairs of this type are specifically designed for structure/components named in the appropriate Allowable Wear and Repair Data Index and/or in that structure/components specific chapter. (2) Typical Repairs (a) Typical repairs are evolved from the characteristics of the materials, with no particular reference to location or class of structure. Repairs of this type may be used singly or in combination to cover a wide variety of damage within the limits given in the appropriate repair figures. Typical repairs must not be used in restricted areas, or for damaged structure for which specific repairs are issued. (3) Temporary Repairs (a) With the approval of the local airworthiness regulatory authority and Learjet Inc., temporary repairs may be made to allow the aircraft to return to base. The effect of damage on structural strength and airworthiness characteristics such as systems operation must be considered. Temporary repairs must be replaced by permanent repairs before the aircraft is released for normal operational duty.

Many components

these and other items have been

B.

C.

D.

E.

F.

G.

H.

I.

EFFECTIVITY:

ALL

51-70-00

Page SRM~

1

Jan 15/93

~Learjki STRUCTURAL REPAIR I.

MANUAi

Support of Structure During Repair (1) Prior to, and during extensive repair operations involving the removal or replacement of large areas of skin plating, frames, stringers, struts, or other heavily stressed members, it is essential to support the surrounding aircraft structure so that the original contours and relative positions of components are maintained. Support must be sufficient to relieve the load on the damaged area while maintaining the position of the surrounding structure and components. (2) Support equipment should preferably be constructed of welded or bolted steel frame, with a suitable cushioning material applied to those parts intended to come into direct contact with the aircraft. control surface is extensive, it is advisable to remove the control surface and inspect for possible hidden damage. The control surface, or a suitable jig, must be temporarily installed during repair to check the alignment and position of hinge fittings and sup-

(3) When damage

to

an area near a

porting structure. (4) For information pertaining to lifting and shoring refer

to the

applicable Learjet Maintenance Man-

ual.

T.

K.

Checking Alignment (1) Before repairs are started, take measurements between reference points on adjacent or opposite parts unaffected by the damage. Compare these measurements with related points on the repair area to determine the extent of distortion. Damage involving major components orlarge portions of the aircraft requires alignment and /or symmetry checks of the aircraft before and after repairs. Refer to the appropriate section, in this chapter, for additional information pertaining to aircraft alignment and /or symmetry checks. TypicalRepair Procedure NOTE:

If

serviceability and/or reliability of any part or repair remains in question or if guidance is making this determination, contact Learjet Field Service for additional informa-

needed in tion.

(1) Investigate and assess damage. (2) Clean up damage to a regular geometric shape. (3) Identify material specification, heat treatment and thickness of damaged structure. (4) Determine which parts of damaged area are loaded in tension or shear, or in combined tension and shear. (Refer to step L´•) (5) Select a typical repair applicable to the existing damage. (6) Select the proper fasteners which correspond to the type of repair and material being used. (7) Lay out fastener pattern, using proper edge distance, pitch and spacing between rows and deter-

required. Prepare repair members (i.e., doubler and filler) Apply surface treatment. Attach repair members and seal as required. Replace any insulation required. mine the number of fasteners

(8) (9) (10) (11) (12)

I

as

required.

Restore aircraft to normal.

EFFECTTVITY:

ALL

52-70-00

Page:! SRM-4

Jan 15/93

Learjet/ I Learjet STRUCTURAL REPAIR MANUAL L.

Struch~ral

Loading

(1) Caps and flanges of spars, ribs, frames and beams are considered to be in tension or compression. (2) Skin panels, together with spar, rib, frame and beam webs, are assumed to be in shear. Addition-

ally, skins may carry tension or compression loads. In the case of compression, loads are assumed only by a small width of skin along the line of fasteners attaching skin to sub-

to be carried structure.

(3) Stringers may be in tension or compression. (4) If the direction of loading cannot be established, the material must be assumed to be in tension. For purposes of fastener requirement calculation, no distinction is made between tension and

compression. 2.

LIMITATIONS AND INSPECTIONS A.

Limitations

DRILLING, MODIFICATIONS, OR ANY TYPE OF WORK THAT CREATES A

WARNING:

BREAK IN THE PRESSURE SECTION IS THE RESPONSIBILITY OF THE OWNER AND/OR MAINTENANCE FACILITY PERFORMING THE WORK. OBTAINING APPROVAL OF THE WORK IS, THEREFORE, THEIR RESPONSIBILITY.

(1) Repairs described in this section manual. Before

are

to

commencing any repair,

comply

given in other sections of this appropriate chapters of this manual for perti-

with instructions

refer to the

damage information. applied to repairs in this section must be followed unless Learjet engineering authori-

nent structural

(2) Limitations

ty

to the

contrary is given.

(3) Repairs must perform its/their specific function, such as fuel or air tightness. (4) Repairs must not interfere with any moving parts. (5) Repairs must be equal to or greater in strength than the original structure.

Technique and material variation is permissible only so far as to facilitate fabrication and ensure the original strength and usefulness of the affected component. Inspections (1) Following any repair or maintenance procedures on the aircraft structure/components, ensure inspection records pertaining to any specific repair-related procedure are identified, properly documented and closely adhered too.

(6) B.

3.

MATERIALSAND PROCESSES A.

Materials

(1) Repair materials and required

treatments

terial and treatment variation is

or

processes will be listed in the repair procedure. Mafar as to facilitate fabrication and ensure the

permissible only so

original strength and usefulness of the affected component. B.

Processes

(1) Precautions against corrosion, such

as

chemical surface

surfaces, and insulating dissimilar metals

chapter, for chemical process and C.

protective

treatment

priming of faying appropriate sections, in this

treatments,

must be taken. Refer to the

specifications.

Fastener Selection

(1) Refer

EFFECTIVITY:

to the

ALL

appropriate section, in this chapter, for information pertaining to fastener selection.

51-70-00

Page 3 SRM-4

Jun 1/95

Learjet Learjet STRUCTURAL REPAIR MANUAL TYPICAL REPAIR

i.

APPLICATION OF LOCTITE A.

determining the kind of Loctite to use in a given application. Use only the given applications. compounds Application of Loctite shall be accomplished at temperatures above 60"F to ensure proper curing. Use

Figure

201

as an

recommended B. 2.

MAINTENANCE PRACTICES

aid in

in their

APPLMNG LOCTITE A.

Prepare Surface (1) Clean all parts to which Loctite is to be applied. Surfaces must be clean and free of dust, grease, condensation, moisture and other contaminants. (2) Parts that are plated, hardened, anodized, or passivated must be treated with Locquic primer

B.

C.

grade T, prior to applying Loctite sealant or compound. The Locquic primer odor must be completely gone before applying Loctite. Apply Loctiteto Bearings (1) If Loctite type has not been specified, selection is to be made from Figure 201. (2) Clean mating surfaces with 1,1,1 trichloroethane (MIL-T-81533). (3) Apply Loctite evenly to both mating surfaces. Exercise care to keep Loctite out of the bearing. Excessive Loctite may be wiped off with a rag moistened in 1,1,1 trichloroethane (MIL-T-81533). (4) Press bearing into bearing housing and keep aligned until Loctite cures. Assembly may be heated for 30 minutes at 1800F to accelerate curing time. Apply Loctite to Threaded Fasteners (1) If Loctite type has not been specified, selection is to be made from Figure 201. (2) Clean threaded surfaces with 1,1,1 trichloroethane (MIL-T-81533). (3) Apply Loctite to threads by brushing, dipping, tumbling, or running applicator NOTE:

over

the threads.

Loctite may be applied to either the nut or bolt; however, for blind hole applications, coat the sides of the blind hole and the first two threads of the male fastener.

(4) Assemble parts and torque using normal torque. (5) Excessive Loctite may be removed using a rag moistened with 1,1,1 trichloroethane (MIL-T81533).

EFFECTIVITY: SRM-4

ALL

51-70-00

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Cure

Application Screw

Locking

Torque

Strength

Loctile

Product

Osp nlling Ability

(cP)

In/Lb

Product

Color

Inehea

Mean

Brealtaway

Psi Shear

222

Purple

0.003

2.000

40

Visco4ity

900

Tamp. Range OF

to

E

300

Cure

Speed

Recom-

~SRoomTemp.on

Steel No Primer

Steel With Primer

Fixture

-65

Screwlock

Speed

@RoomTemp.on

Full

Fixture

mended Primer

Full

20

24

5

24

T

I

Minutes

Hours

Minutes

Hours

pption4

20

24

5

24

T

I

Minutes

Hours

Minutes

Hours

(Optional)

20

24

5

24

T

1

Minutes

Hours

Minutes

Hour

(Optional)

E~ EH

Nut

Locking

Stud

Locking

242

Blue

0.003

2.000

60

1.600

´•65

Nutlbck

to

c\l

300

271

Red

0.005

500

225

2,500

-65

Studlock

to

A

300

AVV

Bearing and Bushing Retention

RC BBO

Green

0.007

1,250

Bushing

Steel

-55

10

24

5

~Q

T

4.000

to

Minutes

Hours

Minutes

Hours

(Optional)

Mo~nt

300

Bearing

Aluminum

Mount

600

RC 35 RC´•10

Plastic

504

Gasket

Gasket

10

to

Eliminator

2.000,000

3[10

Orange

0.015

1,000.MN)

1.300

-65

I

90

12

Minutes

Hours

Not Required

None

Plastic Gashet

ISPG

t~mse

EFFECTIVITY:

Applications af Loctite Figure 201 ALL

51-70-00

Fal;e202 May 15/92

Leariet Learjet STRUCTURAL REPAIR MANUAL 3.

INSTALLING OVERSIZEFASTENERS A.

Oversized Fasteners Installation At

Existing Holes

(1) Determine maximum diameter of existing hole. (2) Refer to oversized charts and select closest oversized fastener that will drilled to

specified

provide

a

clean hole when

tolerances.

(3) Drill out damaged hole to oversize determined in step A.(2). (4) If original hole was cracked, dye penetrant inspect to ensure that crack is removed. (5) Apply epoxy primer, and install new fastener of proper grip length. B.

Limitations

(1) The number of oversized fasteners

EFFECTIVITY: SRM´•4

ALL

must not exceed 20% of

original attaching pattern.

51-70-00

Page 203 May 15/92

Learjet STRUCTURAL REPAIR MANUAL HI-LOKS REWORK HOLE SIZE

REPLACEMENT HI-LOK NOMINAL DIA.

PART

NUMBER HL1 8-5 HL19-5 HL20-5 HL21-5 HL50-5 HL51-5

5/32

HL18-6 HL19-6 HL20-6 HL21-6 HL50-6 HL51-6

3/16

HL1 8-8 HL19-8 HL20-8 HL21-8 1-1150-8 HL51-8

1/4

HL18-10 HL19-10

5/16

ORIGINAL HOLE SIZE

(-o.oooo)

(+0.0010) 0.1895

(-o.oooo)

(+0.001 0) 0.2495

(-o.oooo)

HL18-14 HL19-14 HL20-14 HL21-14 HL50-14 HL51-14

7/16

HL1 8-16 HL19-16 HL20-16 HL21-16

1/2

NOTE:

If fastener fit is too

1/64

Oversize

HL62-6 HL63-6 HL64-6 HL65-6 HL56-6 HL57-6

HL218-6 HL219-6 HL220-6 HL221-6 HL68-6 HL69-6

HL62-8 HL63-8 HL64-8 HL65-8 HL56-8 HL57-8

HL218-8 HL219-8 HL220-8 HL221-8 HL68-8 HL69-8

I I

1/32 Oversize

1 1

0.190 0.187

0.2031 0.2001

0.2187 0.2157

0.2656 0.2626

0.2812 0.2782

0.3281 0.3251

0.3437 0.3407

(+0.0010)

HL62-10 HL63-10

HL218-10 HL21 9-10

(-o.oooo)

HL64-)0 HL65-10

HL220-10 HL221-10

HL56-10 HL57-10

HL68-10 HL69-10

HL62-12 HL63-12 HL64-12 HL65-12 HL56-12 HL57-12

HL21 8-12 HL219-12 HL220-12 HC221-12 HL68-1 2 HL69-12

HL62-14 HL63-14 HL64-14 HL65-14 HL56-14 HL57-14

HL218-14 HL219-14 HL220-14 HL221-14 HL68-14 HL69-14

0.4531 0.4501

0.4687 0.4657

HL62-16 HL63-16 HL64-16 HL65-16

HL218-16 HL219-16 HL220-16 HL221-16

0.51 56 0.51 26

0.5312 0.5282

0.31 20

HL51-10 HL18-12 HL1 9-12 HL20-12 HL21-12 HL50-12 HL51-12

1132

Oversize HL18-6 HL19-6 HL20-6 HL21-6 HL50-6 HL51-6

(+0.001 0) 0.1635

HL20-10 HL21-10 HL50-10

3/8

1/64 Oversize

(+0.001 0) 0.3745

(-o.oooo)

(+0.001 0) 0.4370

(-o.oooo)

(+0.001 0) 0.4995

(-o.oooo)

0.3906 0 .3876

1

0.4062 0.4032

tight, enlarge hole within specified tolerance.

Optional to use HL18 and HL19 oversize fasteners in place of specified HL50 and HL51 (respectively) replacements, provided fasteners meet installation requirements outlined in 51-40-01.

LES1097AU

Oversized Fasteners Installation At

Figure EFFECTIVITY: SRM-4

ALL

oversize

Existing Holes

202 (Sheet 1 of 5)

51-70-00

Page 204 May 15/92

Learjet

STRUCTU RAL REPAIR MANUAL

STANDARD AND OVERSIZE

COUNTERSINKS FOR 1000 FLUSH HEAD HI-LOK BOLTS

FLUSH TENSION HEAD BOLT

FLUSH SMEAR HEAD BOLT

1/32 O.S.

STD. C-SK

1164 O.S.

NOMINAL

DIA.

C-SK DIA.

1/32 O.S. C-SK DIA.

C-SK DIA.

1/64 O.S. C-SK DIA.

C-SK DIA.

BOLT

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

DIA.

D

D 0.3280

STD.

D

-5

(5/32)

0.2588

-6

(3/16)

0.2991

0.2991

0.3278

0.3789

0.3789

0.3789

-8

(1/4)

0.3923

0.3923

0.4235

0.5042

0.5042

0.5042

-10

(5/16)

0.4710

0.4710

0.5026

0.6311

0.6311

0.6311

-12

(3/8)

0.5579

0.5579

0.5891

0.7580

0.7580

0.7580

0.6650

0.6650

0.6962

0.8848

0.8848

0.8848

0.7510

0.7510

0.7822

1.0104

1.0104

1.0104

-14(7/16)

D The head height of all Hi-Lok bolts

common to an

aerodynamic surface

outlined in 51-04-04. The head height of all Hi-Lok bolts not or minus 0.010 inch height from the adjacent surface.

SRM~

aerodynamic

surface

requirements deviate plus

can

Oversized Fasteners Installation At Existing Holes Figure 202 (Sheet 2 of 5)

sits

EFFECTIVITY:

must meet the installation

common to an

ALL

51-70-00

Page 205 May 15/92

Learjet STRUCTURAL REPAIR MANUAL PART

DIA.

NUMBER

1/64 Over

3/16

NAS464-3

NAS2903

1/4

NAS464-4

NAS2904

5116

NAS464-5

3/8

1/64Over

1/32 Over

NAS3003

0.2031/0.2001

0.21 87/0.21 57

NAS3004

0.2656/0.2626

NAS2905

NAS3005

0.328110.3251

NAS464-6

NAS2906

NAS3006

0.3906/0.3876

0.4062/0.4032

7/16

NAS464-7

NAS2907

NAS3007

0.4531/0.4501

0.4687/0.4657

1/2

NAS464-8

NAS2908

NAS3008

0.5156/0.5126

0.531 2/0.5282

3/16

NAS563

NAS2903

NAS3003

0.2031/0.2001

0.2187/0.21 57

114

NAS654

NAS2904

NAS3004

0.2656/0.2626

0.281 2/0.2782

5/16

NAS655

NAS2905

NAS3005

0.3281/0.3251

0.3437/0.3407

3/8

NAS656

NAS2906

NAS3006

0.3906/0.3876

0.4062/0.4032

7/16

NAS657

NAS2907

NAS3007

0.4531/0.4501

0.4687/0.4657

1/2

NAS658

NAS2908

NAS3008

0.5156/0.51 26

0.531 2/0.5282

3/16

NASI 153

NAS1 703

NAS1 603

0.2031/0.2001

0.21 87/0.21 57

1/4

NAS1154

NAS1 704

NAS1 604

0.2656/0.2626

0.281 2/0.2782

5/16

NAS1 705

NAS1 605

0.3281/0.3251

0.3437/0.3407

3/8

NAS1155 NAS1156

NAS1 706

NAS1 606

0.3906/0.3876

0.4062/0.4032

7/16

NAS1157

NAS1 707

NAS1 607

0.4531/0.4501

0.4687/0.4657

1/2

NASI 158

NAS1 708

NAS1 608

0.5156/0.5126

0.531 210 .5282

5/32

B100-T5

3/16

BP-T5 B100-T6 e100-T8 BP-T8

1/4

NAS1202 NAS1 203 NAS1 204

#8 3/16 114

I

I I I I I I

BP-TG

1/32 Over

I I I I I I

I

I

OB1 00=r5

0.281 2/0.2782

0.3437/0.3407

1

0.185/0.182

1 I I I

1 1 1 1

OBP-T8

I

1

0.281/0.278

NAS1203

I

i

0.190/0.187

OBP-TS OB1 00-T6 OBP-T6

0.185/0.182

0.220/0.217 0.220/0.217 0.281/0.278

osl oo-Ta

NAS1 703R

NAS1 603R

0.2031/0.2001

0.21 87/0.21 57

NAS1 704R

NAS1 604R

0.2656/0.2626

0.281 2/0.2782

NAS1 605R NAS1 606R

0.3281/0.3251

0.3437/0.3407

0.3906/0.3876

0.4062/0.4032

NAS1 607R

0.4531/0.4501

0.4687/0.4657

NAS1 608R

0.5156/0.51 26

0.531 2/0.5282

NAS1 603 NAS1 604 NAS1 605

0.2031/0.2001

0.21 87/0.21 57

0.2656/0.2626

0.281 2/0.2782

0.3281/0.3251

0.3437/0.3407 0.4062/0.4032

3/8

NAS1 205 NAS1 206

7/16

NASI 207

1/2

NAS1 208

NAS1 705R NAS1 706R NAS1 707R NAS1 708A

3/16

NAS1 503

NAS1 703

1

1/4

NAS1 504

el

5/16

NAS1 505

NAS1704 NAS1 705

3/8

NAS1 506

NAS1 706

NAS1 606

0.3906/0.3876

7/16 1/2

NAS1 507

NAS1 707 NAS1 708

NAS1 607 NAS1 608

0.4531/0.4501

0.4687/0.4657

0.5156/0.5126

0.531 2/0.5282

3/16

NAS2803

NAS1 703

NAS1 603

0.2031/0.2001

0.21 87/0.21 57

1/4

NAS2804

NAS1704

NAS1 604

0.2656/0.2626

0.281 2/0.2782

5/16

NAS2805 NAS2806 NAS2807

NAS1 705

NAS1 605

0.3281/0.3251

0.3437/0.3407

3/8 7/16

NAS1 706

0.3906/0.3876

0.4062/0.4032

NAS1 707

NAS1 606 NAS1 607

0.4531/0.4501

0.4687/0.4657

1/2

NAS2808

NAS1 708

NAS1 608

0.51 56/0.51 26

0.531 210 .5282

5/16

NAS1 508

Oversized Fasteners Installation At Existing Holes Figure 202 (Sheet 3 of 5)

5129

EFFECTIVITY: sRM-4

REWORK HOLE SIZE

REPLACEMENT

BOLT NOMINAL

ALL

51-70-00

Page 206 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL "D" DIAMETER

THREAD

UNJF-3A

BOLT PART

"T"

(EXCEPT NOTED)

AS

MAX.

MIN.

REF

NAS2903

0.1900-32

0.2026

0.2016

0.338

NAS2904

0.2500-28

0.2651

0.2641

0.425

NAS2905

0.31 25-24

0.3276

0.3266

0.469

NUMBER

NAS2906

0.3750-24

0.3901

0.3891

0.578

NAS2907

0.4375-20

0.4526

0.4516

0.594

NAS2908

0.5000-20

0.5151

0.5141

0.735

NAS2909

0.5625-18

0.5771

0.5761

0.840

NAS2910

0.6250-18

0.6396

0.6386

0.902

NAS2912

0.7500-16

0.7646

0.7636

1.041

NAS2914

0.8750-14

0.8896

0.8886

1.184

NAS2916

1.000-12

1.0146

1.0136

1.309

NAS291 6A

1.0000-14’

1.0146

1.0136

1.291

NAS2918

1.1250-12

1.1396

1.1381

1.458

NAS2920

1.2500-12

1.2646

1.2631

1.646

/-3 1

I!´•

’_t

"NS-3A

Bolt, Shear

Hexagon Head,

0.0156 Oversize

Shank, Alloy Steel

160-180 KSI Ultimate Tensile

"D" DIAMETER

THREAD BASIC

DOCUMENT

UNJF-3A

(EXCEPT NOTED)

"T"

AS

MAX.

MIN.

REF

NAS3003

0.1900-32

0.2182

0.21 72

0.338

NAS3004 NAS3005

0.2500-28

0.2807

0.2797

0.425

0.31 25-24

0.3432

0.3422

0.469

NUMBER

NAS3006 NAS3007 NAS3008

0.3750-24

0.4057

0.4047

0.578

0.4375-20

0.4682

0.4672

0.594

0.5000-20

0.5307

0.5297

0.735

NAS3009

0.5625-18

0.5927

0.5917

0.840

NAS3010

0.6250-18

0.6552

0.6542

0.902

NAS3012

0.7500-16

0.7802

0.7792

1.041

NAS3014

0.8750-14

0.9052

0.9042

1.184

NAS3016

1.0000-12

1.0302

1.0292

1.309

NAS301 6A NAS3018

1.0000-14*

1.0302

1.0292

1.291

1.1250-12

1.1552

1.1537

1.458

NAS3020

1.2500-12

1.2802

1.2787

1.646

.f

’NS-3A

Bolt, Shear

Hexagon Head,

0.0312 Oversize Shank,

Alloy

Steel

160-180 KSI Ultimate Tensile

Oversized Fasteners Installation At Existing Holes Figure 202 (Sheet 4 of 5)

EFFECTIVITY:

ALL

51-70-00

Page 207 May 15/92

Learjet STRUCTURAL REPAIR MANUAL PART NUMBER

"D" DIA., 0.0156

(NONLOCKING UNDRILLED)

OVERSIZE SHANK

NOMINAL 0.0156

THREAD

OVERSIZE

SIZE

MAX.

MIN.

NAS4703-*~

0.1900-32

0.2026

0.2016

NAS4704-*~

0.2500-28

0.2651

0.2641

NAS470A1-~

0.2500-28

0.2651

0.2641

NAS4705-’~

0.31 25-24

0.3276

0.3266

NAS4706-’~

0.3750-24

0.3901

0.3891

NAS4707-’~

0.4375-20

0.4526

0.4516

NAS4708-*~

0.5000-20

0.5151

0.5141

NAS4709-’~

0.5625-18

0.5771

0.5761

0-^I~

0.6250-18

0.6396

0.6386

NAS471 2-’~

0.7500-16

0.7646

0.7636

NAS4714-*~

0.8750-14

0.8896

0.8886

6-’I~

1.0000-12

1.0146

1.0136

NAS471

NAS471

"D"

0.0312

DIA., 0.0312

OVERSIZE SHANK

OVERSIZE NAS4703-’i~

0.1900-32

0.2182

0.21 72

NAS4704-’~

0.2500-28

0.2651

0.2797

NAS470AI-~ NAS4705-’~

0.2500-28

0.2807

0.2797

0.31 25-24

0.3432

0.3422

NAS4706-’~

0.3750-24

0.4057

0.4047

NAS4707-~

0.4375-20

0.4682

0.4672

NAS´•1708-~

0.5000-20

0.5307

0.5297

NAS4709-*~

0.5625-18

0.5927

0.5917

NAS471 0-’~

0.6250-18

0.6552

0.6542

2-’j~

0.7500-16

0.7802

0.7792

NAS471 4-’~

0.8750-14

0.9052

0.9042

NAS471

1,9000-12

1.0302

1.0292

NAS471

Grip dash

number in 0.0625-inch increments

.f 14-201A

EFFECTNITY:

Existing Holes Figure 202 (Sheet 5 of 5)

Oversized Fasteners Installation At

ALL

51-70-00

Page 208 May 15/92

Learjet STRUCTURAL REPAIR MANUAL 4.

INSTALLING BUSHINGS IN OVERSIZED HOLES A.

Bushings Installation At Oversized Holes (1) Determine the original hole ID (bore) of damaged part. (2) Refer to standard bushing chart and select bushing with

Standard

the closest ID (bore) of the

original

hole

size.

Length of required bushing will vary with application. length and deburred when necessary.

NOTE:

(3) Refer

to standard

bushing chart,

determine the hole size (steel

ing selected in step A. (2). (4) Drill out damaged hole to hole size determined in (5) Install bushing with wet epoxy primer. B.

step

Standard

or

bushing may be

aluminum)

cut to

to match the bush-

A. (3).

Limitations

procedures specified in paragraph A., Repair Data figures in 51-71-00.

(1) Rework of oversized holes, using the

specified

in the Allowable Wear and

are

limited to those

HOLE STEEL

ALUMINUM

HOLE DIAMETER

HOLE DIAMETER

BUSHING OUTSIDE DIAMETER SIZE

NOMINAL

DASH NO.

BORE

MAXIMUM

MINIMUM

MINIMUM

MAXIMUM

MINIMUM

MAXIMUM

3

0.1900

0.3136

0.3131

0.3123

0.3129

0.3123

0.3129

4

0.2500

0.3761

0.3756

0.3748

0.3754

0.3748

0.3754

5

0.3125

0.4386

0.4381

0.4373

0.4379

0.4373

0.4379

6

0.3750

0.5013

0.5006

0.4998

0.5004

0.4997

0.5003

7

0.4375

0.5638

0.5631

0.5622

0.5629

0.5622

0.5628

8

0.5000

0.6265

0.6257

0.6248

0.6255

0.6247

0.6254

9

0.5625

0.6892

0.6882

0.6873

0.6880

0.6872

0.6879

10

0.6250

0.8142

0.8132

0.8122

0.8130

0.8120

0.8129

11

0.6875

0.8767

0.8757

0.8747

0.8755

0.8745

0.8754

12

0.7500

0.9393

0.9383

0.9372

0.9381

0.9370

0.9379

14

0.8750

1.0648

1.0638

1.0627

1.0636

1.0625

1.0634

16

1.0000

1.1898

1.1888

1.1875

1.1885

1.1873

1.1883

18

1.1250

1.3148

1.3138

1.3125

1.3135

1.3122

1.3132

20

1.2500

1.4399

1.4389

1.4375

1.4385

1.4372

1.4382

Interference Fit Hole Sized For NAS 75,

Standard

EFFECTIVITY:

ALL

76, 77, 537, 538 (BACBP8Y, U, W, X)

Bushings Installation for Oversized Figure 203

Holes

51-70-00

Page 209 May 15/92

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL REAMER SIZE

TOL

0.0625 0.0730

+0.0010

0.0937 0.1220

-0.0010

1

I

REAMER SIZE

TOL

0.2640*

+0.0010 -0.0010

1

I

1

1

1

0.1230 0.1240 0.1250 0.1260 0.1270 0.1 280

1

I

1

0.1406 0.1542 0.1552 0.1 562 0.1719 0.1850* 0.1855 0.1865 0.1870* 0.1 875 0.1880 0.1885 0.1890

1

1 1 1

I

I I I

1

1 1 1

0.1910 0.1920 0.1930 0.1990 0.2020* 0.2031

1

1

1

0.2344 0.2450* 0.2460* 0.2475* 0.2480 0.2485* 0.2490

1

I

1

1

I

1

1

I

1

1

I

1

*Piloted

reamers

1

0.2810 0.2812 0.2822 0.2969 0.3080* 0.3090* 0.31 05* 0.3115 0.3120’ 0.3125 0.3135 0.3150* 0.3240* 0.3270* 0.3281 0.3290* 0.3400’ 0.3427 0.3438

0.3450’ 0.3594 0.3710* 0.3730’ 0.3735* 0.3740 0.3750 0.3760 0.3890’ 0.3906 0.3920*

0.4020* 0.4050’ 0.4052 0.4062 0.4070’ 0.4072 0.4219 0.4360*

1

0.2500

0.2510 0.2520 0.2530* 0.2570 0.2620*

0.2802

I

1 1 1 1

1

I I

1 1

I

1 1

+0.0010 -0.0010

1

1 1 1 1

1

+0.0020 -0.0020

1

I I I i

1 1 1 1

I

0.4364

+0.0010 -0.0010

1

0.4375 0.4385

1

1

1

I

1

I

TOL

0.4520*

+0.0020

0.4531 0.4670* 0.4677

-0.0020

1

I

1

1

I

1

1

_I

1

1 1

I

1

1

I

1 1

+0.0020 -0.0020

1.1562

1.1250

1

I

1

1.1875

0.4688 0.4697 0.4844

1 1

I I

1 1

1.2188

1

I

1

1.2812

0.4980* 0.4990

1 1 1 1 1 1

I I 1 I I I

1 1 1 1 1 1

1.3125 1.3438 1.3750

1 1

I

1 1

1.5625

1

1.5938

0.5000

I

+0.0020 -0.0020 +0.0030 -0.0020

1.5000

I I

1 1 1

0.6542

1

I

1

1.6875 1.7188 1.7500 1.7812

0.6719

1

I

1

1.8125

0.6875

1

1

1

1.8438

0.7031 0.7188 0.7344 0.7500

1

I

1

1.8750

1

I

1

1

I

1

1.9062 1.9375

1

I

1

0.7656 0.7812

1

I

1

1 1

I I

1 1

0.8281

1

I

1

0.8438 0.8594 0.8750 0.8906 0.9062 0.9219 0.9375 0.9631 0.9688

1

I

1

1.0000 1.0156 1.0312 1.0469 1.0625

+0.0040 -0.0020

1.4062 1.4375 1.4688

1 1 1

I

i

1.2500

0.5625 0.5781 0.5938 0.6094 0.6250 0.6406

0.9844 1

1.0938

I

0.7969 0.8125 1

1 1

1

0.5140* 0.5156 0.5300* 0.5312

TOL

REAMER SIZE

1

0.5678

0.3447

0.2150* 0.2180* 0.2188 0.2190*

1

0.3430’

0.1895 0.1900

0.2656 0.2670* 0.2770’

REAMER SIZE

1.6250 1.6562

1.9688 2.0000 2.0625 2.2500

2.3125 2.3750 2.5000

+0.0040 -0.0020

+0.0030

1

-a.

+0.0040 -0.0020

cannot be used.

Standard Reamer Size

Figure 204

EFFECI~IVITY: SRM-4

ALL

51-70-00

Page 210 May 15/92

Learjet STRUCTU RAL REPAIR MANUAL PRESS FITS FOR BUSHINGS IN ALUMINUM AND MAGNESIUM

TOLERANCE HOLE DIAMETER

0.2501 thru 0.5000 0.5001 thru 0.7500

0.7501 thru 1.0000 1.0001 thru 1.2500

1.2501 thru 1.5000 1.5001 thru 1.7500 1.7501 thru 2.0000 2.0001 thru 2.2500 2.2501 thru 2.5000 2.5001 thru 2.7500 2.7501 thru 3.0000

3.0001 3.2501 3.5001 3.7501

thru thru thru thru

3.2500 3.5000 3.7500 4.0000

(O.D.)

INTERFERENCE

Min.

Max.

Min.

+0.0005 +0.0006 +0.0006 +0.0007 +0.0007 +0.0008 +0.0008 +0.0009 +0.0009 +0.0009 +0.0009

0.0000

+0.0007 +0.0009 +0.0011 +0.0013 +0.0015 +0.0017

0.0012 0.0015

0.0002 0.0003

0.0017

0.0005

0.0020 0.0023

0.0006

0.0025

0.0009

+0.0019 +0.0021

0.0027 0.0030

0.0011 0.0012 0.0013

0.0034 0.0036 0.0038

0.0015 0.0017

0.0000

+0.0022 +0.0024 +0.0026 +0.0028 +0.0030 +0.0032 +0.0034 +0.0036

0.0032

+0.0010 +0.0010 +0.0010 +0.0010 +0.0011

+0.0012 +0.0015 +0.0017 +0.0020 +0.0023 +0.0025 +0.0027 +0.0030 +0.0032 +0.0034 +0.0036 +0.0038 +0.0040 +0.0042 +0.0044 +0.0046

0.0040

0.0042

0.0020 0.0022

0.0044 0.0046

0.0024 0.0025

Max. 0.0000 thru 0.2500

BUSHING

HOLE

0.0000 0.0000

0.0000 0.0000

0.0000 0.0000 0.0000 0.0000 0.0000

0.0000 0.0000 0.0000 0.0000 0.0000

Max.

Min.

0.0008

0.0018

PRESS FITS FOR BUSHINGS IN STEEL TOLERANCE HOLE DIAMETER

0.2501 thru 0.5000 0.5001 thru 0.7500 0.7501 thru 1.0001 thru 1.2501 thru 1.5001 thru 1.7501 thru 2.0001 thru 2.2501 thru 2.5001 thru 2.7501 thru 3.0001 thru 3.2501 thru 3.5001 thru 3.7501 thru

1.0000 1.2500 1.5000 1.7500 2.0000 2.2500 2.5000 2.7500 3.0000 3.2500 3.5000 3.7500 4.0000

(O.D.)

Min.

Max.

Min.

+0.0005 +0.0006

0.0000

+0.0007 +0.0007

0.0000

+0.0008 +0.0008 +0.0008 +0.0009 +0.0009 +9.0009 +0.0010 +0.0010 +0.0010 +0.0010 +0.0010 +0.0011

0.0000

+0.0011 +0.0014 +0.0016 +0.0018 +0.0020 +0.0022 +0.0024 +0.0026 +0.0027 +0.0029 +0.0031 +0.0032 +0.0034 +0.0035 +0.0036 +0.0038

+0.0007 +0.0008 +0.0010 +0.0011 +0.0013 +0.0014 +0.0015 +0.0017 +0.0018 +0.0019 +0.0021 +0.0022 +0.0024 +0.0025 +0.0026 +0.0028

Max. 0.0000 thru 0.2500

BUSHING

HOLE

0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

0.0000 0.0000 0.0000

Press Fit Hole Size for

INTERFERENCE Max.

Min.

0.0011

0.0002

0.0014

0.0003

0.0016

0.0003

0.0018 0.0020 0.0022 0.0024 0.0026 0.0027

0.0004

0.0007 0.0008 0.0009

0.0029

0.0010

0.0031 0.0032

0.0011 0.0012

0.0005

0.0006

0.0034

0.0014

0.0035 0.0036

0.0015 0.0016

0.0038

0.0017

Bushings

Figure 205 EFFECTIVITY: SRM4

ALL

51-70-00

Page 211 May 15/92

STRUCTURAL REPAIR WIANUAL 5.

APPLICATION AND USE OF STRUCTURAL ADHESIVES WARNING:

ROOM TEMPERATURE ADHESIVES (REGARDLESS OF CURE TIME) SHALL NOT BE USED TO SECURE ANY PRIMARY STRUCTURE.

A.

The

area

EFFECTTVITY: SRM~

are used and the application of the adhesive is specified Learjet maintenance manual.

in which adhesives

sections of the basic

ALL

in the

applicable

51-70-00

Fage212 May 15/92

Learjet TEMPORARY REVISION NO. 51-2 Leajet Model 20/30 Series Structural Repair

MANUAL AFFECTED:

Insert

FILING INSTRUCTIONS:

adjacent

to

Manual (SRM-Q).

51-70-01, page 201, dated Jun 1/95, and retain until further

notice. To

REASON:

clarify dent repairs to wing leading edge. Revise

INSTRUCTIONS:

paragraph i. MINOR DENT REPAIR, as follows:

AIRCRAFT SKIN DENTS 1.

TYPICAL REPAIR

MINOR DENT REPAIR A. Minor dents are dents in the aircraft skin or sutFstructure which do not exceed the limits the Allowable Damage section of each chapter. B.

Minor Dent

specified

in

Repairs

(1) Dents in the aircraft skin, where access to the dented area is restricted, can be repaired using dynamic fairing compound. (Refer to paragraph 3., for application of aerodynamic fairing

aerocom-

pound.) (2) Dents in the aircraft skin, where accessible, may be

repaired by bumping the skin back into conpainted surface has not fractured. Refinish appropriate Leajet Maintenance Manual, Chapter 20,

to ensure that the

inspected painted surface, if required. (Refer to the for painting procedures.) (3) Dents in the engine nacelle inlet areas shall Chapter 54 of this manual. tour. The

area

WARNING:

shall be

be

repaired

in accordance with the

procedures

in

DENT REPAIRS ACCOMPLISHED ON THE WING LEADING EDGE SHALL TESTED TO VERIFY AERODYNAMIC ACCEPTABILITY AND BE

FLIGHT

STALL SPEEDS. (REFER TO THE BASIC

LEARJET MAINTENANCE

MANU-

AL OR SERVICE MANUAL FOR APPLICABLE STALL WARNING FAULT

ISOLATION PROCEDURES).

(4) Dents in the

wing,

vertical stabilizer, and the horizontal stabilizer shall be

bumped

back into

con-

tour.

Z

MAJOR A.

DENT REPAIR

Major

B.

dents in the aircraft skin Damage section of each chapter.

dents

lowable

are

or

sub-structure which exceed the limits

specified

in the Al-

Major Dent Repair (1) Damaged areas shall be removed and repaired using the typical repairs as specified in 51-70-02. (2) Leading edges of the wing, vertical stabilizer, and the horizontal stabilizer shall be replaced.

1EMPORARY REVISION NO. 51-2

51-70-01

Page 1 of 1 Aug15/97

Learjet

STRUCTURAL REPAIR MANUAL AIRCRAFT SKIN DENTS i.

TYPICAL REPAIR

MINORDENT REPAIR dents in the aircraft skin

sub-structure which do not exceed the limits

A.

Minor dents

B.

Damage section of each chapter. Minor DentRepairs

are

or

specified in

the Allowable

(1) Dents in the aircraft skin, where access to the dented

dynamic fairing compound. (Refer pound.)

to

paragraph 3.,

area

for

is restricted,

application

be repaired using aeroaerodynamic fairing com-

can

of

(2) Dents in the aircraft skin, where accessible, may be repaired by bumping the skin back into

con-

inspected to ensure that the painted surface has not fractured. Refinish painted surface, if required. (Refer to the appropriate Learjet Maintenance Manual or Service Manual for painting procedures.) (3) Dents in the engine nacelle inlet areas shall be repaired in accordance with the procedures in Chapter 54 of this manual. (4) Dents in the leading edge of the wing, vertical stabilizer, and the horizontal stabilizer shall be bumped back into contour. tour.

The

area

WARNING:

shall be

I

DENT REPAIRS ACCOMPLISHED ON THE WING LEADING EDGE SHALL BE FLIGHT TESTED TO VERIFY AERODYNAMIC ACCEPTABILITY AND STALL SPEEDS. (REFER TO THE BASIC

LEARJET

MAINTENANCE MAN-

UAL OR SERVICE MANUAL FOR APPLICABLE PROCEDURES). 2.

MAJOR A. B.

DENT REPAIR

Major dents are dents in the aircraft skin or sub-structure which exceed the limits specified in the Allowable Damage section of each chapter. Major DentRepair (1) Damaged areas shall be removed and repaired using the typical repairs as specified in 51-70-02. (2) Leading edges of the wing, vertical stabilizer, and the horizontal stabilizer shall be replaced.

hi I~"that EFFECTIVITY:

SRM-Q

ALL

REVISI(IN revises this page.

51-70-01

Page 201 Jun1/95

I

Learjet ~Learjefl

S~RUCTURAC REPAIR MANUAL APPLICATION OF AERODYNAMIC FAIRING COMPOUND

3.

A.

Toolsand

Equipment

NOTE:

Equivalent substitutes may be used in lieu of the following:

NAME

PART NUMBER

White Streak Plastic Solder

MANUFACTURER*

USE

16522

Aerodynamic filler

DX-999

47695

Aerodynamic filler

H-1337-B-L (resin)

99384

Aerodynamic filler

and Cream Hardener Filler

Epocast

9615A (hardener)

Sealant

Pro-Seal 890

Products Research

(MIL-S-8802) Class B1/2

Chemical

Aerodynamic filler

Corp.

Class B-2 Class B-4 Filler

C42 No. 6372

16772

Aerodynamic filler

Filler

EC-1751

94961

Aerodynamic filler

Masking Tape

Commercially

available

General

MethylEthylKetone (MEK)

Commercially

available

General

Putty Knife

Commercially

available

General

Lint-Free Cloth

Commercially

available

General

Abrasive

Paper

No. 220

or

finer

Commercially

available

General

Abrasive

Paper

No. 320

or

finer

Commercially

available

General

Commercially

available

General

Abrasive Pad

(Nylon Wool Type) Blow Gun and

Tip

DGD501

Scales (Calibrated in Grams) Abrasive

No. 80

Paper

17431

General

Commercially

available

General

Commercially

available

General

*Refer to the Introduction Section of this manual for lists of manufacturers.

LFS1092F

EFFECTIVITY:

ALL

51-70-01

Page 202 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL B.

Filler

Preparation

(1) White Streak Plastic Solder shall be mixed with the dener to three

pounds

of base

cream

hardener at

pounds

of base

ratio of

one ounce

har-

compound.

(2) Ditzler DX-999 plastic shall be mixed with the accelerator three

a

at

a

ratio of

hardener to

one ounce

compound.

(3) Pro-Seal 890 (MIL-S-8802) shall be mixed per manufacturer’s recommendations. The ratio will vary with different classes of sealant to be mixed. (4) EC-1751 shall be mixed at a ratio of two parts gray and grey and two parts amber by volume. When

NOTE:

mixing fairing compounds,

compound. C.

Surface NOTE:

a

one

part

amber

by weight

or

three parts

folding action shall be used. Avoid trapping air in or other foreign materials to mixture.

Do not add resins, thinners,

Preparation The aircraft structure namic filler in order to

temperature shall be 65"F (180C) or above when applying aerodypromote adhesion and to prevent moisture condensation. or any other surface contaminants from each side of area to be filled.

(1) Remove all dirt, dust, grease, pencil marks, paint, be filled and for

CAUTION:

a

distance of

one

inch

along

area

to

USE EXTREME CARE WHEN REMOVING SURFACE OXIDES TO PREVENT EXCESSIVE REMOVAL OF METAL.

(2) Use #80 grit abrasive paper

to

remove

surface oxides and wash with MEK.

Dry

surface thor-

with lint-free cloth.

D.

oughly Application

Filler

NOTE:

aerodynamic filler shall be applied directly to the cleaned metal. No primer type shall be applied or allowed to remain prior to application of the filler.

The

(1) Mask off area

to be sealed

a

distance of

one

inch

of any

along each side.

(2) Apply filler with a putty knife. (3) Build area to be sealed to a maximum of l/&inch thickness paper application. Allow first application to

(4) (5) (6) (7)

cure

completely.

Sand hardened surface and blow clean with clean, dry air. Do not Apply second application of filler and allow to cure completely.

use

liquid cleaner.

Sand hardened surface with #220 abrasive paper to remove excess filler. Sand hardened surface with #320 abrasive paper until smooth and flush with Feather all edges and exercise care to prevent abrasion of adjacent metal surfaces.

(8) Blow clean dry air

over

surface until clean. Do not

use a

liquid

adjacent

cleaner. Direct air

areas.

perpendicular

pin holes. (9) Apply a thin layer of filler to fill pin holes. Repeat sanding procedure. (10) Refinish painted surface. (Refer to the appropriate Leajet Maintenance Manual, Chapter 20, painting procedures.) to the surface to

EFFECTIVITY:

ALL

remove

dust from

for

51-70-01

Page 203 SRM-4

Jun 1/95

I

LEARJET 20/30 SERIES

STRUCTURAL REPAIR MANUAL

TEMPORARY REVISION NO. 51-6 MANUAL AFFECTED:

Learjet

20/30 Series Structural

FILING INSTRUCTIONS: Insert REASON: To

as

dated

May 15/92 and

retain until further notice.

for treatment of cracks.

follows: AIRCRAFT SKIN

1.

Manual.

adjacent to 51-70-02, page 201,

incorporate procedures

INSTRUCTIONS: Revise

Repair

TYPICAL REPAIRS

SkinRepairs A.

Repair Instruction (See Figures 201 thru 203.) (1) Repair procedures are given in this section

for

repair

side of the pressure cabin. In the pressure cabin

a

of skins of the pressure cabin, and skins out-

staggered

double

row

of rivets is

required

the repair is not supported or made rigid by sub-structure. (2) Repair material and gage must be the same as original. (3) Rivet spacing shall be compatible with the original rivet pattern. As a general rule, shall be six (6) times the diameter of the rivets. (4) Drill all parts in place, remove parts, and remove burrs. (Refer to 51-40-02 for skin

rivet

when

spacing

trim

).noitanimretednoitacol

I

(5) Refer to 51-30-04 for protective treatment of metal. (6) Apply sealant as required when the repair may affect 30-02 for sealing procedures. 2.

the cabin pressure

capabilities. Refer

to 51-

Treatment of Cracks

DO NOT STOP-DRILL CRACKS IN THE PRIMARY STRUCTURE UNLESS THIS IS

CAUTION:

PERMITTED IN THE ALLOWABLE DAMAGE LIMITS.

(REFER

TO

51-70-00.)

CRACKS

IN THE PRIMARY STRUCTURE THAT ARE LARGER THAN PERMITTED IN THE

ALLOWABLE DAMAGE LIMITS CAN CAUSE THE PART TO HAVE LESS THAN THE NECESSARY STRENGTH.

A.

Stop-Drill Cracks (Refer

Figure 204.) (1) Perform a liquid-penetrant inspection to accurately find the end 20/30/55 Series Nondestructive Inspection Manual.) (2) Stop-drill cracks. (a) Use a #40 (0.098 inch [0.250 cmlf diameter drill for metal to

of the crack.

(Refer

thickness of 0.032

to the

Learjet

[0.081 cm]

or

less.

(b)

Use

a

#30

(0.128

inch

[0.325 cml)

diameter drill for metal thickness greater than 0.032

[0.081

cm].

(3) (4)

Deburr the hole and

Perform

remove

all unwanted material.

liquid-penetrant inspection

to the

Learjet (Refer (5) Apply surface treatment protection TEMPORARY REVISION NO. 51-6

SRM -4

to make

sure

that the hole has contained the end of the crack.

20/30/55 Series Nondestructive

Inspection Manual.) (Refer to 51-30-04.)

to the bare metal surfaces.

51 -70-02

Page

1 of 8

Jan 15/01

LEARJET 20/30 SERIES

STRUCTURAL REPAIR MANUAL

(6) Calculate

the total

length

that the total crack

(Refer NOTE:

to

of the crack after it is

damage

in the

a crack is in one part of a riveted assembly, remove the fasteners and put in a temporary shield made from thin stainless steel sheet. This will prevent damage to the

can

that

go into

are

behind.

stop-drill holes,

seal the

area

with sealant

or

with surface filler.

(Refer

51-30-02.)

TEMPORARY REVISION NO. 51-6 SRM -4

permitted

diameter). Make sure allowable damage limit.

Where

Where moisture to

is less than the maximum

the hole

51-70-00.)

adjacent parts

(7)

stop-drilled (include

51-70-02

Page

2 of 8

Jan 15/01

LEARJET 20/30 SERIES STRUCTURAL REPAIR MANUAL EDGE MARGIN

B

2 X RIVET dia

PATCH

2024-T3 CLAD

EDGE DISTANCE

21

2 X RIVET dia

RADIUS0.5 in [1.27 cm]

CLEAN OUT DAMAGE AREA

,I

o

SKIN

lo

Ij

RIVET SPACING

1

2 X RIVET dia

A_

DOUBLER

0.5 in

o\

/O

2024-T3 CLAD

[1.27 cm]

RADIUS

EDGE DISTANCE 2 X RIVET dia

EDGE DISTANCE 2 X RIVET dia

0.5 in

[1.27 cm] RADIUS

MINIMUM

D(ISTING SKIN

PATCH

DOUBLER

View A-A

520-517W2-201-01

Typical Insert Patch (Non-Pressurized Area) Figure 201 (Sheet 1 of 2)

TEMPORARY REVISION NO. 51-6 SRM -4

of 8 51-70-02 Page Jan 15/01 3

LEARJET 20/30 SERIES STRUCTURAL REPAIR MANUAL

RIVET SPACING 3 dia MAXIMUM

6 X RIVET. dia

J-

EDGE DISTANCE

RIVET X

M

2 X RIVET dia

DAMAGE SKIN

FILLER

’-I REPAIR DOUBLER

FILLER

REPAIR DOUBLER

SAME MATERIAL AS,

AND ONE GAUGE HEAVIER THAN DAMAGED

SKIN MATERIAL

SAME GAGE AND MATERIAL

OR EQUIVALENT

DAMAGE SKIN

820-61 7002-201 -02

Typical Insert Patch (Non-Pressurized Area) Figure 201 (Sheet 2 of 2)

TEMPORARY REVISION NO. 51-6 SRM -4

51-70-02

Page

4 of 8

Jan 15/01

LEARJET 20/30 SERIES

STRUCTURAL REPAIR MANUAL EDGE DISTANCE 2 X RIVET dia

0.5 in

[1.27 cm] PATCH

RADIUS

EDGE DISTANCE

A

B

X RIVET dia

0.5 in

2024-T3 CLAD

CLEAN OUT DAMAGE

2SUIDAR

NIKSAERA

O0O

[1.27 cm]

MINIMUM

Pb O

3~

n

/O

RIVET SPACING

r

,4-6 X RIVET dia

oo~

Oo\,

/b

O

o_o

DOUBLER

0.5 in

2024

T3 CLAD

[1.27 cm]

RADIUS

EDGE DISTANCE

EDGE DISTANCE

2 X RIVET dia

2 X RIVET dia

0.5 in

SPREAD SEALANT NENLY

APPROXIMATELY 1/32 in [0.08 cm] (REFER TO 51-30-02.)

[1.27 cm] RADIUS

MINIMUM

THICK

RIVETS

f I-I

-n

8--cl

View A-A Typical

TEMPORARY REVISION NO. 51-6 sRM -4

(Pressurized Area) Figure 202

Insert Patch

51-70-02

Page

5 of 8

Jan 15/01

LEARJET 20130 SERIES STRUCTURAL REPAIR MANUAL

DOUBLER SAME GAGE AND MATERIAL OR EQUIVALENT

ir~

c L

EXISTING

i:

EDGE DISTANCE 2 X RIVET DIAMETER MINIMUM 1

o

ed

C

RIVET SPACING 6 RIVET 4

e

DIAMETERS

L)

~y :o´•

´•::sr

rs

b7 0,05 in

A

u

20.127 cm] RADIUS

MINIMUM

CP/PICAL)

A

I

APPLY SEALANT IN CONTACT AREA; SPREAD

EVENLY APPROXIMATELY 1/32 in [0.08 cm] THICK.

(REFER TO 52-30-02)

PATCH

DOUBLER

DOUBLER

PATCH

RIVETS

View A-A 520-51~002-203-01

Over Structure

TEMPORARY RE\IISION NO. 51a SRM -4

Repair (Pressurized and Non-Pressurized Area) Figure 203

51 -70-02

15/01

LEARJET 20/30 SERIES STRUCTURAL REPAIR MANUAL

1!2 D

1!2 D

8

e

Y a

CRACKS

CENTER-PUNCH TO STOP-DRILL 1/2 DRILL DIAME~ER AWAY FROM THE ENDS OF THE CRACK AND IN LINE WITH THE CRACK DIRECTION

(USUAL)

REFER TO THE TEXT

FOR DRILL SIZES

HOW TO STOP-DRILL CRACKS

STOP DRILL, REMOVE THE CRACK, AND MAKE

SMOTHL

NO DAMAGE PERMITTED

TO SHADED AREAS AT BEND RADII OR FILLETS

r/l’

x

STOP DRILL, REMOVE THE CRACYAND

CRACK REMOVED TO A CIRCULAR

MAKE SMOOTH

HOLE 20 MINIMUM

TREATMENT FOR CRACKS IN DCTRUDED

OR FORMED SECTIONS

SM517002-2W-01

Treatment of Permitted Cracks

Figure

TEMPORARY REVISION NO. 51-6

204

(Sheet

1 of

2)

of 8 51-70-02 Page 15/01 7

Jan

SRM -4

LEARJET 20/30 SERIES STRUCTURAL REPAIR MANUAL

CRACK FROM FASTENER HOLE TO THE EDGE OF THE SKIN

CRACK FROM THE EDGE OF THE SKIN

CRACK REMOVED TO A CIRCULAR HOLE

CRACKS THAT START

g

FROM A FASTENER HOLE

n/ CRACK BETWEEN FASTENER HOLES

CRACKIN OPEN SKIN AREA

TREATMENT OF CRACKS IN SKIN NOTE

LEGEND L

X ED D

REFER TO THE APPLICABLE

MAXIMUM LENGTH MINIMUM DISTANCE EDGE DISTANCE DRILL DIAMETER OR RIVET HOLE DIAMETER

ALLOWABLE DAMAGE LIMITS

FOR THE MAXIMUM DIAMETER.

S20517002-204-M

Treatment of Permitted Cracks

Figure

TEMPORARY REVISION NO. 51-6 SRM -4

204

(Sheet

2 of

2)

51-70-02

Page

8 of 8

Jan 15101

Learjet STRUCTURAL REPAIR MANUAL AIRCRAFT SKIN i.

TYPICAL REPAIRS

SKINREPAIRS A.

Repair Instruction (See Figures 201 thru 203.) (1) Repair procedures are given in this section for repair of skins of the pressure cabin, and skins outside of the pressure cabin. In the pressure cabin a staggered double row of rivets is required when the repair is not supported or made rigid by sub-structure. ~2) Stop-drill cracks, or remove damaged area and smooth edges, before application of repair. Use #40 (0.098) stop-drill for metal thickness of 0.032 or less and #30 (0.128) stop-drill for metal thickness greater than 0.032. (3) Repair material and gage must be the same as original. (4) Rivet spacing shall be compatible with the original rivet pattern. As a general rule, rivet spacing shall be 6 times the diameter of the rivets.

(5) Drill all parts in place, remove parts and remove burrs. (6) Refer to 51-30-04 for protective treatment of metal. (7) Apply sealant as required when the repair may affect the cabin pressure capabilities. Refer 30-02 for

EFFECTIVITY:

to 51-

sealing procedures.

ALL

q

NOTE: Please

see

the

TEMPORARY RE\NSION that revises this page.

51-70-02

May 15/92Page

20’1

Learjet

STRUCTURAL REPAIR MANUAL

Patch-$i

---Existing

Skin

T’~Ri STi~ 1/2

I/

B

Doubler

B

B

/--Edge Margin 2

Rivet Dia.

x

Patch

Edge Margin 2

B

Clad

Skin)

as

B

Rivet Dia.

x

2024-T3

(Same Gage

e

~I iJ

Clean

Out

AreaDamaged Skin

e~

~,,-Rivet Spacing 6

Doubler

2024-T3

(Same Gage

as

Rivet

Dia.

Alclad

Skin)

Edge 2

1/2"

x

x

Margin Rivet Dia.

Radius

1/2"

Radius

Typical Insert Patch (Non-Pressurized Area) Figure 201 (Sheet 1 of 2) EFFECTIVITY: SRM~

ALL

51-70-02

Page 202 May 15/92

Learjet STRUCTURAL REPAIR MANUAL 3

Dia.

~------Rivet

Max

Spacing

Rivet Dia.

j

3 /X

t

Margin

I

r 3-t

f

x

1

2

x

Rivet Dia.

-t I

\I

Damaged skin

Repair Doubler

ma;eZIaEsRepair

Doubler

heavier

as,

than

material Filler

Same

and

one

gage

damaged skin

7

Rivet

I

Filler

gage as

Same

damaged skin

Typical Insert Patch (Non-Pressurized Figure 201 (Sheet 2 of 2)

EFFECTIVITY: SRM4

ALL

iDamaged

and material

Skin

Area)

51-70-02

Page 203 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL Edge Margin 2´•x Rivet Dia,

Radius

1/2"

2024-T3

~--patch

(Same Gage

Edge Margin 2

x

as

Clad

Skin)

I

A

Rivet Dia.

Out

Clean

Damaged

Area

Skin

1/2" Radius L--Rivet Spacing 4-6

x

Rivet Dia.

Edge Margin 2024-T3

Doubler

(Sane Gage

as

1

/2

CLad--~

2

x

Rivet Dia.

Skin) Radius

Sp~ead Sealant Evenly Approx.

1/32" Thick. (Refer

to

1/2‘ Radius

41-30-02.)

NAS1097AD4 Rivets

i i

U~ ~J C----------1/2

Detail A Typical Insert Patch (Pressurized Area) Figure 202

EFFECTTVITY: SRM~

ALL

51-70-02

Page 204 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Doubler 1

same

Gage and

Material

Existing

Skin

as

Skin

Edge Margin 2

x

Rivet Dia.

0.50

R.

A

Min

Rivet

Spacing

4-6

Rivet Dia.

x

Min.--J ~,´•i´•i

(Typi call

Apply

sealant

contact

in

area;

spread evenly

1/32" thick.

approx.

(Refer

Doubler

or

SRM-4

7

NAS1097AD4 Rivets

Over Structure

EFFECTTVITY:

ALL

51-30-02.)

g

Patch

S-134

to

rl~i\

Double r

Patch

Repair (Pressurized and Non-Pressurized Area) Figure 203 51-70-02

Page 205 May 15/92

Learjet STRUCTURAL REPAIR MANUAL FORMED SECTION

TYPICAL REPAIRS

SEVERED ORDAMAGED FORMED SECTIONREPAIR

i.

A.

RepairInstruction (1) (2) (3) (4)

same material and gage as original. Refer to 51-40-02 for fastener removal and installation, hole sizes, and Refer to 51-30-04 for protective treatment of metal.

Use

Restore

(5) Seal the

EFFECTIVITY: SRM-4

edge margins.

required surface finish per Chapter 20 of the appropriate Learjet Maintenance Manual. repair as required. (Refer to 51-30-02.)

ALL

51-70-03

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

2024-T3

0.063

1 /,i/

/---Cut off damaged section here.

Doubler

Ai

(Same Gage and

Doubler

9

Material Add

as

Bulkhead)

---~--J´•

´•:-:I

.i

MS20470AD4:´•si´•i:I~..Ij i

I

::~i i

III

i.i_:

´•aX~

j~

Existing

Clean and

out

sealer

old

reseal.

A

i:

Structure"

(Refer

Bamaged Section Replacement

to

51-30-02.)

TYPICAL REPLACEMENT OF

BIJLRHWD

hole

as

SECTION

Detail A

netalF.deriuqerlightening

j:iii-l MS20470AD4

Rivets i

r 0.063

2024T3

t

Doub ler

Defect----J

O.C)63

Angles

TYPICAL REPAIR OF CRACKED

2024-T42

(2

Reqd.)

Detail B

BULKBWD

Typical Bulkhead Repair Figure 201 (Sheet

EFFECTTVITY: SRM-4

ALL

1 of 2)

51-70-03

Page 202 May 15/92

Learjet ~Learietl

STRUCTU RAL REPAIR MANUAL

NAS1097AD4

Rivets

MS20470AD4 Rivets

lo_

i,

A

Length to Adjacent Stringers Approximately 7 Inches Each

Ikhead

Extend or

Defect

Side

of

Segment

to

Defect

.Detail A Typical Bulkhead Repair Figure 201 (Sheet 2 of 2) EFFECTIVITY: SRM-4

ALL

51-70-03

Page 203 May 15/92

Learjet ~tl

STRUCTURAL REPAIR MANUAL EXTRUDED SECTION

i.

TYPICAL REPAIRS

EXTRUDED SECTIONREPAIR

A.

RepairInstruction (1) (2) (3) (4) (5) (6) (7)

damaged portion of extrusion. repair parts of same gage and dimensions of original extrusion. Assemble repair parts and drill and ream fastener holes. Prepare repair parts for sealing, if required, in accordance with 51-30-02. Refer to 51-40-02 for fastener removal, installation, hole sizes and edge margins. Refer to 51-30-04 for protective treatment of metals. Restore finish in accordance with Chapter 20 of the appropriate basic Leajet Maintenance ManuCut and

remove

Fabricate

EFFECTIVITY:

ALL

51-70-04

Page 201 SRM-4

May 15/92

I

STRUCTURAL REPAIR MANUAL New

Gage,

Type, Same Butt

to

New

(Material

Section

as

and Dimensions

Original Section)

Section

Original Section

out

Clean

old

reseal.

sealer and

Angle

(Material Type,

Gage,

and

Same

as

(Refer

Dimensions

a~

to

51-30-02.)

Original

Extrusion)

Section

2

Edge Margin

r~

/I

or

o o

d

P

::s

.a~9

Angle

(Material Type,

Gage,

and

Same

5 of

Rivets

Each

as

Dimensions

Extrusion)

Side

Splice

MS20470AD4

Rivets

~Y3 ~-t-,

Detail A

NAS1097AD4

Rivets

Typical Extruded Section Repair (Pressurized and Non-Pressurized Figure 201 EFFECTIVITY: SRM-4

ALL

Area)

51-70-04

Page 202 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL Strip (Material Type and Gage same as Extruded Angle) Filler

Gage, as

(Material Type, and Dimension

Extruded

same

Angle)

’s~ ii

Clean Out

Damaged

Area

5

Rivets

Each

Side

Area

3/4" Rivet Spacing

-t

Angle

(Material Type,

Gage,

and Din\ensions

Same

Detail A

Pick up

existing

skin

as

Extruded

Angle)

rivets

MS20470AD4 Rivets

Stringer

"21 Skin

Typical Stringer Repair (Pressurized and Non-Pressurized Area) Figure 202 EFFECTNITY: SRM-4

ALL

51-70-04

Page 203 May 15/92

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL FIBERGLASS STRUCTURES -REPAIR i.

DESCRIPTION A.

Fiberglass structures used

on

the

Leajet include the radome and

dorsal inlet

fairing.

(1) On early Model 20130 Series Aircraft the radomes are constructed of 2-inch wide strips of fiberglass cloth, bonded together with a polyester-based resin. On later Model 30 Series Aircraft, and as replacement spares for the earlier model polyester-type radomes (t~er SSK 911), an epoxy-based resin, single-sandwich honeycomb-core radome is used. screws.

An erosion boot is bonded to the

For additional information

pertaining

nose

The radome is attached to the

of the radome to

prevent

nose

by

environmental erosion.

to the radome erosion boot refer to the basic

Leajet

Main-

tenance Manual.

(2) The dorsal inlet fairs the vertical stabilizer

to the

The dorsal inlet is constructed of

heat

exchanger. manently to the fuselage and verticalstabilizer. and are secured to the fuselage with screws.

2.

fuselage and permits entry of ram air for the 5-ply laminated fiberglass and is attached per-

Two bulkheads

are

riveted into the dorsal inlet

RADOME -APPROVED REPAIRS

NOTE:

These

repairs apply only to

the

nose

radome.

A.

Approved repairs for the radome include the repair of minor damage to the radome skin and replacement of radome erosion boot. For radome erosion boot removal and/or replacement refer to the basic Learjet Maintenance Manual.

B.

Prior to

radome

repair,

inside radome with

C. D.

E.

determine which

type of resin

used in radome fabrication

by strong light shinning looking polyester resin are translucent and their cores are constructed of Zinch wide strips of fiberglass cloth, which will be visible. Radomes fabricated with epoxy resin are opaque and have one-piece cores. As a general rule, minor damage is defined as damage to the radome skin only. This excludes any damage which goes into or beyond the core. Radomes which cannot be repaired per the following instructions must be replaced with a new radome per Special Spares Kit (SSK) 911. This includes any radome damaged beyond the limits set in the following instructions. Tools and Equipment beginning

NOTE:

a

was

thru from the outside. Radomes fabricated with

Equivalent substitutes may be used in lieu of the following:

MANUFACTURER

USE

Epon 828 or Epon 815

Shell Chemical

Bond radome

916

Shell Chemical

PART NUMBER

NAME

Epoxy Resin

Epoxy Hardener

Company

skin

Company

Hetron 92

Polyester Resin

Hardener for

epoxy resin

Epon 815

Pittsburg Plate Glass Co.

Bond radome skin

LES1197A LES1259A

EFEE~IVITY: SRM-4

ALL

51-70-05

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL PART NUMBER

NAME

6% Cobalt

Napthenate

Fed.

Spec.

TT-D-643

MANUFACTURER

USE

Commercially available

Used with

polyester resin MEK Peroxide

Hypodermic Syringes

Lucidol Div., Novadel Agene Co.

Used with

Commercially available

Inject adhesive

polyester resin

and Needles

F.

MixingInstructions (1) Mix epoxy resin as follows: (a) Mix by weight 100 parts of Epon 828 dener

just before using.

After

or Epon 815 epoxy resin and 20 to 25 parts of 916 harmixing, pot life is approximately 23 minutes at room tempera-

ture.

(2) Mix polyester resin as follows: (a) Mix by weight 100 parts of Hetron 92 and 0.50 part of 6% cobalt

ly mixing, add by weight G.

part of MEK peroxide. greater than one (1) inch in diameter,

napthenate.

After

thorough-

1.0

Blisters and delaminations not not closer than four (4) inches, greater in number than four (4) in four (4) square feet of surface (see Figure 201) are to be repaired follows: (1) Drill a small hole into, but not through the skin at each end of the blister or delamination.

(2) (3) (4) (5)

or as

Fill

syringe with resin and inject the blister or delamination full of resin. or delamination firmly into place and hold until resin has cured. Remove any excess resin from the surface with light sanding. Check repair for a sound bond by tapping repaired area with a coin. Any area which is not properly bonded will make a different (hollow) sound when tapped. (6) Repaint affected area of radome in accordance with Chapter 20 of the appropriate basic Learjet Press the blister

Maintenance Manual. H.

Scratches

limited to those not

more than l/&inch wide, 1/16-inch deep and 4-inches long. (See depressions are limited to those not more than I/2-inch in diameter and not more than l/lbinch deep. These defects must not be any closer than one (1) inch and there shall be no more than three defects per on~j(l) square foot of surface area. Repair the defects as follows: (1) Fill defect with resin and allow to fully cure. (2) Carefully sand the resin to a´•uniform smoothness, blending with the contour of the radome. (3) Repaint affected area of radome in accordance with Chapter 20 of the appropriate basic Leajet

are

Figure 202.)

Pits and

Maintenance Manual.

EFFECTIVITY: SRM~

ALL

51-70-05

Page 202 May 15/92

Learjet ~I STRUCTURAL REPAIR MANUAL in.

1

C’

or

dia.

or

less

Drill

small

hole

at

each end of blister

rmmmmmmmrn

Pump resin into blister with

syringe

Resin

-1

Resin

should

hole at

1

Press

into

until

resin

Lightly excess

Blister and Delamination

come

opposite

sand

out

end

place and hold fully cures

off

resin

Repair

Figure 201 EFFECTTVITY:

ALL

51-70-05

Page 203 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

4 in.

max.

length

;t

1/16 in. max. depth 1/8 in. max. width

Fill with and

in.

I

sand

Dia

resin smooth

max.

x

1/16 in.

max

depth

Fill with resin and

sand

smooth

Scratch, Pit, and Depression Repair

Figure 202 EFFECTIVITY: sRM-4

ALL

51-70-05

Page 204 May 15/92

Learjet Learjet

STRUCTURAL REPAIR MANUAL 3.

APPROVED REPAIRS

DORSAL INLET A. B.

C.

Approved repairs for the dorsal inlet include minor and major damage to the dorsal inlet fairing. Damage to the dorsal inlet forward structure shall require replacement of the dorsal inlet fairing. Toolsand Equipment Equivalent substitutes may be used in lieu of the following:

NOTE:

PART NUMBER

NAME

181

Glass Fabric

120

weight and weight

MANUFACTURER

USE

J.P. Stevens Co., Inc. New York, NY

Replace damaged skin

Epoxy Resin

Epon 828 or Epon 815

Shell Chemical

Company

Bond skin

Epoxy Hardener

916

Shell Chemical

Company

Bond skin

Clean Cloth or

or

Commercially available

Remove residue

Commercially available

Remove residue

Cheesecloth

Acetone

or

Ketone

D.

Repair blisters and delaminations, scratches, pits and depressions per instructions in step 2, except that damaged area in excess of size and depth limits given in step 2 shall be repaired as follows: NOTE:

Damage

(2) Cut

excess

of limits in

step

2 shall be combined

larger on all sides than number of plies affected minus 1.

(1) Mark off the

in

an

an area

X in the center and

NOTE:

remove

the

the first

area

to be

as one

repaired by

repair area. an

amount in inches

ply, being careful not to cut into

the

equal

remaining plies.

Rectangular cut-out area or other cut-out area having sharp comers shall whenever possible and the outside ply shall be avoided whenever possible.

be avoided

(3) Move in one (1) inch on all sides and remove second ply (if affected). (4) Proceed in this fashion until all damaged plies have been removed. (5) Sand exposed plies and wipe with a clean, lint-free cloth or cheesecloth moistened with or

acetone

ketone.

181-weight glass fabric for inner plies and 120-weight glass fabric for outer ply to lap new ply of skin 0.5 to 0.75 inch (12.7 to 19.5 mm) over corresponding ply of original skin.

(6) Cut

(7) Mix resin per step 2. F. (8) Impregnate new plies with mixed resin. (9) Place impregnated plies in damaged area, working each ply to the

EFFECTIVITY:

to

preceding ply as possible,

ALL

and to

remove excess

to make it as wrinkle-free and

each

tight

resin and air from the laminate.

51-70-05

Page 205 SRM~

May 15/92

Learjet STRUCTURAL REPAIR MANUAL NOTE:

The outermost

bridging (10) Laminate will ened

(11) Sand

cure

by heating

ply

of the

at the

original repair line.

or

gaps

in

approximately two (2)

to 1400 to 1600F

to contour with 150

grit or

outer skin must be faired to

hours at

room

a

fine

edge

temperature. Cure time

to

can

using heat gun or infrared lamps. finer abrasive paper, being careful not to sand into the

(60"C

to

710C)

prevent

be short-

a

glass

fab-

ric.

(12) Check repair for

erly

(13) Repaint affected

jet

EFFECTIVITY: SRM-4

a

sound bond

area

by tapping repaired area with a coin. Any area which is not proptapped. Chapter 20 of the appropriate basic Lear-

different (hollow) sound when of dorsal inlet in accordance with

bonded will make

a

Maintenance Manual.

ALL

51-70-05

Page 206 May 15/92

Learjet I STRUCTURAL REPAIR MANUAL CORROSION- REPAIR 1.

APPROVED REPAIRS A.

depth gauge (or equivalent), determine the extent of corrosion (material damage exceeds the allowable material thickness, as specified in the allowable age limits section of each chapter, the structural component must be replaced. (See Figure 201.) Using

age).

a

dial indicator

If material

NOTE:

Light

Corrosion

Structure is discolored

or

pitted

to

a

depth

of

approximately

damdam

0.001

inch (.0254 mm) maximum.

scaling, flaking, and pitting to a depth 0.010 inch (.254 mm). Requires structural repairs after rework of corroded areas.

Moderate Corrosion

Severe Corrosion

Structure has blisters,

Structure has

depth greater than 0.010 inch (.254

blisters, exfoliation, scaling, and pitting Requires structural repairs or replaced.

light or moderate corrosion is found, rework area per paragraph D. severe corrosion is found, the structural component must be repaired or replaced. Rework lightly or moderately corroded areas on structure as follows: (See Figures 202

B.

If

C.

If

D.

severe

mm),

CAUTION:

of

to a

and 203.)

DO NOT USE STEEL WOOL OR STEEL WIRE BRUSHES OR SEVERE ABRASIVES WHEN REWORKING STRUCTURE FOR CORROSION. USE 240 GRIT OR FINER ALUMINUM OXIDE ABRASIVE PAPER. FINISH WITH 400 GRIT PAPER.

(1) Sand corroded areas using 240 grit or finer aluminum oxide abrasive paper. (2) Blend out pits in structure as shown. WARNING:

WEAR PROTECTIVE hlZC~SK AND ENSURE THAT WORK AREA IS WELL VENTILATED WHILE CLEANING STRUCTURE WITH METHYL ETHYL KETONE (MEK).

ENSURE

THAT

MANUFACTURER’S

PUBLISHED

INSTRUCTIONS

ARE FOLLOWED WHEN USING CLEANING AGENTS AND METAL

FINISH.

(3) Clean sanded surfaces with a clean cloth soaked with methyl ethyl ketone (MEK). Immediately wipe surfaces dry using a clean, dry cloth. Do not allow solvents to be "wicked" under adjacent structure.

(4)

Apply chemical film treatment on reworked surfaces as follows: (a) Obtain Turcoat Accelagold chemical film treatment, manufactured by pany, Wilmington, CA. NOTE:

Any equivalent chemical film treatment for aluminum alloy ing it complies with MIL-C-5541 Class 1 metal finish.

Turco Products Com-

may be used

provid-

03) Brush chemical film over sanded surfaces until a satisfactory chemical film is obtained. (c) Gently sponge over chemically treated surfaces using warm water. Do not rub surfaces. Allow surfaces to air

EFFECTTVITY: sI1M~

ALL

dry.

51-70-06

Page 201 May 15/92

Learjet STRUCTURAL REPAIR MANUAL (5) Apply

a

brush coat of epoxy

NOTE:

Use either of the

primer on chemically treated

surfaces

as

follows:

primer systems described below:

Thoroughly mix

one volume of base primer #515-344 and one volume of curing solution #910-350, Super Koropon Fluid Resistant Primer available from: Desoto, Inc., P.O. Box 401268, Garland, TX 75040. Telephone (214) 276-5181.

Thoroughly mix one

volume of primer base #463-12-8 and one volume of Catalyst CA-116 Cat-A-Lac corrosion resistant primer available from: Bostik Div. Emhart Corp., 20846 S. Nortnandie Ave., Torrance, CA 90502. Telephone (213)320-6800

Thoroughly

mix

one

volume of

primer

base #438-660 and

agent #120-650 available from: Wichita Division, Pratt Wichita, KS 67201. Telephone(316) 733-1361. (a) After

of the

one

volume of

primer systems described above has been thoroughly mixed, apply over prepared surfaces. (b) Allow primer to dry at room temperature for a minimum of two hours. (6) Install all previously removed equipment. coat

one

sI~M-a

ALL

a

brush

the

(7) Return aircraft

EFFECTIVITY:

curing

Lambert, P.O. Box 2153,

to service.

51-70-06

Page 202 May 15/92

Learjet ~Learjet STRUCTURAL REPAIR MANUAL

Adjustable Dial in

Dial Face Lock

Indicator Marked

Increments of O.ODOS

Base

Point "A"

Point "B"

Corrosion Pit

Point

Conical

"C"

Point

DETAIL I

Take

readings

at

various points.

NOTE:

Depth

dial

gage

O

to

0.500

inch

range. O

Take

measurement

adjacent

readings

on

edges

corrosion

~1

damage or blended depression (Points "A" and "B"). Take several readings around of corrosion center or damage blended depression (5ee Detail II) and be

to

consider

Point

"C".

the

DETAIL II

deepest reading to Determine

depth

as

follows:

Depth =C

(A

B)

Corrosion

EFFECTIVITY: SRM-4

ALL

Damage and Rework Measurement Figure 201 51-70-06

Page 203 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Pit has been cleaned all

loose

corrosion

to

up

ertent

the

have

products

been

that removed.

~LD

CORROSION DAMAGE BE~OAE RDJORK

Rough edges

have

corrosion has

depression

has

been

been not

smoothed

removed. been

and

all

However,

shaped.

DEPRESSION ARER CORROSION REMOVAL

Blending ratio

has

and

been

accomplished

direction shown

in

in

the

figure

203.

DISH-GOT AFTER RLENOING

Blendout of Corrosion of

Single Depression Figure 202

EFFECTIVITY: sIiM~

ALL

51-70-06

Page 204 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

100-

4

CORROSION DANA(r BEFORE RMOVAL

SD

Min

0´•9’

Bottom of Dep ression After Corrosion Removal

REMOVED AND SURFACE S(OOTHED WITH SHALLOW ELLIPTICAL DISH-OUT

Generous Radius

D

(Typical)

Run-Out

Generous Radius NOTE: D

(Typical) of

Depth

Refer

Depression

specific

to

allowable

limits for maximum allowable D

Since

maximum

different

O

The

all

at

in

specified O

See

also

blending

tained

Detail

a

I

varies

depth

locations,

dish-out will

damage

EXAC(PLE a

depth.

1:5 BLEM)IH; RATIO DETAIL

I

at

maximum size

of

vary.

ratio

shall

times

unless

be

main-

otherwise

specific repair. for

example

of

blend-

ing.

Multiple Pits in Corroded Figure 203 (Sheet 1 of 2)

Blendout of

EFFECTIVITY: s~ur-4

ALL

Area

51-70-06

Page 205 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

CAUTION:

W NOI

USE STEEL

WIRE

WOOL,

STRUCTURE FOR CORROSION. SIVE PAPER.

BRUSHES, USE

OR SEVERE

210 GRIT

ABRASIVES WHEN REWDRKING

OR FINER

ALUMINUM OXIDE ABRA-

FINISH WITH 400 GRIT PAPER.

Location of

Width of Cleaned

Corrosion Pits

Up

Area

(10 limes Depth Min)

iii i

i

ij

c)

i‘

:j

r:: j VIEW LOOKIK; DOWN

VIEW IN TRUE PERSPEICTIM

Depth

~ength of Cleaned Up (ZO rimes Depth Min)

of Clean

Up

of Corrosion

Atee

CROSS SECTION VIEW

NOn

AC6PTABLE.

ACCEPTABLE

Blendout of

Multiple Pits in Corroded Area

Figure 203 (Sheet 2 of 2)

EFFECTIVITY: SRM~

ALL

51-70-06

Page 206 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL HONEYCOMB INSERT- REPAIR i.

APPROVED REPAIRS

NOTE: A.

If inserts

are

being installed

in

new

honeycomb panels,

omit

paragraph A.

RemoveDamagedInsert (1) Determine part number and maximum diameter of damaged insert. (2) Drill out insert. Clean hole with clean cloth and MEK. If old epoxy remains around perimeter of

integrity. Any epoxy not adhering to honeycomb must be removed. Requirements (1) Storage of Epoxy Potting Compound (a) All unmixed epoxy potting compound shall be stored at 450 to 800F (7.2" to 26.70C). Epoxy potting compound has a storage life of 9 months at 800F (26.70C) when maintained in unopened original package. (b) Materials stored at temperatures exceeding 800F (26.7"C) shall be used within 2 weeks. (c) Stocks shall be rotated to eliminate storage stability problems and retesting of the epoxy potting compound. (2) Mixing of Epoxy Potting Compound (a) The scales and weighing procedure shall be controlled so that the hardener is within +2%, to be sure of uniform quality. (b) Weigh into a clean, wax-free container 100 parts by weight of SLE3009 resin. Add 25 parts by weight of SLE3009 hardener. (c) Weigh into a clean, wax-free container 100 parts by weight of EA9321 Part "A". Add 50 parts by weight of EA9321 Part "B". (d) Weigh into a clean wax-free container 100 parts by weight of SLE3006 resin. Add 27.5 parts by weight of SLE3006 hardener. (e) Mix components until the color is uniform, taking care not to trap air in epoxy potting compound. Entrapped air creates porosity, thereby reducing potting strength and also causes potting material to slump as entrapped air outgasses. (f) Mix only amount of epoxy potting compound that can be used in 30 minutes. Mixed epoxy potting compound has a pot life of 30 minutes at 750F (23.90C). Excessive agitation during mixing, higher ambient temperature, or large masses of material being mixed, will reduce installation hole check it for

B.

General

pot life.

(g)

Load mixed epoxy

potting compound into a polyethylene cartridge. a sealing gun and install a 1/16-inch orifice nozzle.

(h) Load polyethylene cartridge into

LES1228E

EFFECTTVITY: SRM~

ALL

51-70-07

Page 201 May 15/92

Learjet STRUCTURAL REPAIR MANUAL Installationof

C.

Honeycomb Inserts

(1) Tools and Equipment NOTE:

Equivalent

substitutes may be used in lieu of the

PART NUMBER

NAME

Epoxy Potting Compound

Insert

SLE3009 Bulk Kit

following:

MANUFACTURER

USE

Dalco Industries 2230 Gladwick

Compton, CA 90220 Insert

Epoxy Potting Compound

Hysol EA9321

The Dexter

Corp. Hysol

Div.

15051 E. Don Juiian Road

Industry, CA 91749 Insert

Epoxy Potting Compound

SLE3006 Bulk Kit

Dalco Industries 2230 Gladwick

Compton, CA 90220 Semco

Sealing Gun

Sealant Gun Nozzles

No. 250

(for

use

with

Sealing Gun)

Polyethylene Cartridges Scales

Accuracy +2%

Solvent

EFFECTIVITY: SRM4

Methyl Ethyl Ketone (MEK) per Fed. Spec. TT-M-261

ALL

51-70-07

Page 202 May 15/92

STRUCTURAL REPAIR MANUAL (2) Honeycomb panel preparation for blind threaded inserts. (a) Drill installation hole per Figure 201 to a depth slightly greater than the length of the blind threaded insert.

(b) Refer

to

step C.5, C.6 or

C.7 for installation

procedures of insert.

Honeycomb Panel (Ref,) Installation Hole Part

way

thru

Honeycomb Panel.

I

or

I

Installation Hole

extends

surface

of

to

upper

lower

Honeycomb Panel

skin.

(Ref.)

Installation Hole Size (Dia First Dash No. per NAS 18XX

NAS 1832-( Insert

NAS 1835-(

Thread Size and Class

[Ref SL601-( )1

[Ref SL606-( )1

Insert

Inches) NAS 1836-( Insert

[Ref SL607-( )1

-06

0.1380-32

UNJC

0.561

0.566

0.452

0.457

-08

0.561

0.566

0.686

0.691

0.452

0.457

-3

0.1640-32 UNJC 0.1900-32 UNJF

0.561

0.566

0.686

0.691

0.452

0.457

-4

0.2500-28

0.686

0.691

0.749

0.755

0.499

0.504

0.686

0.691

0.811

0.817

0.842

0.847

0.874

0.880

-5 -6

UNJF 0.3125-24 UNJF 0.3750-24 UNJF

Blind Threaded Insert Installation

Figure 201 EFFECTIVITY: SRM~

ALL

51-70-07

Page 203 May 15/92

Learjet STRUCTURAL REPAIR MANUAL (3)

Honeycomb panel preparation for spool-type inserts thru clearance hole type. (a) Drill installation hole per Figure 202 to the bottom honeycomb face sheet at locations. (b) Drill bolt or screw hole through the bottom honeycomb face sheet per Figure 202. (c) With a counterbore tool, clean honeycomb core and adhesive from the bottom honeycomb face sheet.

(d) Refer

to

step C.8 for installation procedures of spool-type inserts.

:r

Installation to

upper

Holt/Screw Hole

[Ref SL603-( Per NAS

)1

Bolt

or

Hole

extends

lower

skin.

(Ref.)

(Ref.)

Installation Hole Size

1834

of

Honeycomb Panel

First Dash No. Per NAS

Hole.

surface

or

Screw

Hole Diameter

(Inch)

(Inch)

1833

[Ref SL602-(

)1

-06

0.561

to

0.566

No.

28

0,561

to

0.566

No.

19

(0.140 +0.005/-0.001) (0.166 +0.005/-0.001)

Hole

-08 -3

0.561

to

0.566

No.

12

(0.189

Hole

-4

0.686

to

0.691

-5

0.686

to

0.691

-6

0.842

to

0.847

1/4 5/16 3/8

+0.005/-0.001) (0.250 +0.005/-0.001) (0.312 +0.006/-0.001) (0.374 t0.006/-0.001)

Hole

Hole Hole Hole

Spool-Type Insert Installation Figure 202 EFFECTIVITY: SRM-4

ALL

51-70-07

Page 204 May 15/92

Learjet I STRUCTURAL REPAIR MANUAL (4)

Honeycomb Panel Preparation for Spool Type Inserts Countersunk Clearance Hole. (a) Drill Installation hole per Figure 203 thru core and both skins (upper and lower).

Installation

Completely

Hole----~

mru

Honeycomb Panel

I

Panel

Upper

(Ref.)

Skin

Honeycomb Panel Skin (Ref,)

Lower

First Dash No. Per NAS

)k(

1834-(

[Ref SL604-(

)1

Nom.

Of Insert

SRM-4

Hole Diameter

(Inch)

(Inch)

-06

0.140

0.561

to

0.566

-08

0.169

0.561

to

0.566

-3

0.196

0.561

to

0.566

-4

0.257

0.686

to

0.691

-S

0.316

0.686

to

0.691

-6

0.377

0.842

to

0.847

Spool-Type Insert (Countersunk Clearance Hole) Figure 203 EFFECTIVITY:

Installation

Clearance

Hole Diameter

ALL

Installation

51-70-07

Page 205 May 15/92

Learjet STRUCTURAL REPAIR MANUAL (5) Installing blind inserts using tab method. (See Figure 204.) (a) Remove paper backing from tab. Press adhesive side of tab up holes. Press tab down NOTE:

Tab is not

firmly so

required

onto insert

being careful

to line

that it sticks to insert.

when bottom end of blind insert is seated.

a sufficient quantity of epoxy potting compound into counterbored hole to completely fill bottom portion of hole to insure that all cells underneath insert and bottom of insert are coated with the epoxy potting compound when insert is installed. (See Detail B.) (c) Insert prepared insert assembly into honeycomb panel installation hole. Apply adequate force to ensure that the tab will adhere to top skin of honeycomb panel. (d) After all inserts have been positioned in honeycomb panel, the inserts shall be potted. Inject epoxy potting compound through one potting hole.The cavity is filled when epoxy potting compound appears in the second potting hole. All honeycomb panel inserts shall be potted

(b) Extrude

in this manner. (See Detail C.) (e) Excess epoxy potting compound may be wiped away prior

dampened (f)

(6)

to

cure

using

clean cotton cloth

with MEK solvent.

After epoxy potting compound has cured for a minimum of 24 hours at room temperature, the tab shall be removed and discarded. Cure may be accelerated by baking at 1400F (600C)

for three hours. Full cure required approximately 5 days at room temperature. Installing blind inserts using no tab (See Figure 205.) NOTE:

Bottom end of blind insert must contact inside surface of the lower face sheet of

honeycomb panel. Refer to

Step 7 for alternate shimming method ing tab method.

for installation of inserts without

(a) Extrude sufficient quantity of epoxy potting compound into counterbored hole inside surface of lower skin and underneath side of insert

us-

to ensure that

coated with epoxy

potting compound when insert is installed. 03) After all inserts have been positioned in honeycomb panel, inserts shall be potted. Inject potting compound through one of the potting holes until cavity fills and potting compound starts to extrude through the second hole. Close off extrusion of potting compound from second hole and continue injection. The cavity is properly filled when potting compound extrudes through hole in skin all around circumference of upper flange of insert. All inserts shall be potted in this manner. (c) Repeat step (5)(e). (d) Repeat step (5)(f).

EFFECTIVITY: SRM-4

ALL

are

51-70-07

Page 206 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL Insert

Tab

Insert

(Ref)

Detail A Insert

Insert

in

(Positioned

Tab

Honeycomb

Panel

(Ref)

panel.)

Epoxy Potting Compound

Detail B Potting Sealing

Gun

(Ref)--,

Holes

~d

(Ref) Insert

..e

Epoxy Potting Compound

Tab

(Ref)

Honeycomb Panel

(Ref)

Detail C Insert Installation

Using Tab Method Figure 204

EFFECTTVITY: SRM-4

ALL

51-70-07

Page 207 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

~-Masking tape optional. If used, punch holes thru

to

holes

Potting

Holes

in

match

potting

insert.

(Ref.)

Honeycomb Panel

Insert

(Ref.)

Insert Installation

Figure EFFECTIVITY: SRM-4

(Ref.)

ALL

Using No

Tab

205

51-70-07

Page 208 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL (7) Alternate Shimming Method (See Figure 206.) (a) It is permissible to use clean AN960 washers in bottom of hole

to shim insert flush with

upper surface of the honeycomb panel skin. Cb) Determine combination of washers required. (c) Remove and clean washers by wiping with clean cotton cloth dampened with MEK solvent. (d) Extrude a sufficient quantity of epoxy potting compound into the counterbored hole to com-

pletely fill bottom portion of hole to ensure that all cells underneath insert are coated with potting compound. (e) Apply potting compound to all surfaces of each washer to be used for shims and position in installation hole.

(f) Position insert into

honeycomb panel installation hole. Apply sufficient force to extrude potflange of insert as insert is pressed into its "seated" position.

up around base

ting compound (g) Repeat step (6)(b). (h) Repeat step (5)(e). (i) Repeatstep(S)(f).

or

AN

960 WASHERS

Insert Installation

Alternate

Figure EFFECTIVITY: s~M-a

ALL

Shimming Method

206

51-70-07

Page 209 May 15/92

STRUCTURAL REPAIR MANUAL (8) Installing Spool Inserts (a) Apply masking tape to cover hole in honeycomb panel skin. (b) Install insert to contact tape´• (c) Insert tab, masking tape, or no covering at all, may be used on upper side of inserts. If tab is

used, holes in tab must be lined up with insert holes. If masking tape is used, punch holes thru tape at potting insert hole locations. (d) Repeat step (5)(6). (e) Repeat step (5)(e). (f) Repeat step (5)(f). (9) Voids at either or both

potting hole locations caused by slumping or sagging of the epoxy potting compound shall be permissible providing the limits of acceptability as noted below are met. (a) Acceptable voids must be contained to the local area of each respective potting hole and shall extend all the way around the insert. allowable depth of voids, as measured thru Maximum (b) not

potting holes,

shall be 0.35 inch.

or

MASKIErG

TAPE

Insert Installation-

Spool Type

Figure 207

EFFECTIVITY: SRM-4

ALL

51-70-07

Page 210 May 15/92

Learjet STRUCTURAL REPAIR MANUAL SEAT RAIL

REPAIR

APPROVED REPAIRS

i.

All dimensions

NOTE: A.

Seat Rail

are

in inches unless otherwise

specified.

Repair (See Figure 201.)

NOTE:

(1) Tools and NOTE:

Repair procedures wise specified.

for both inboard and outboard seat rails

are

identical unless other-

Equipment Equivalent substitutes may be used in lieu PARTNUMBER

NAME

of the

following:

MANUFACTURER

Commercially available

Countersink (0.339x100O)

USE Countersink

splice

strips #12

Drill

Commercially available

Drill holes for

screws

matching nutplates Drill

#40

Commercially available

Drill holes for rivets

matching nutplates Drill

#30

Commercially available

Drill holes for rivets

Drill

#21

Commercially available

Drill holes for rivets

(2) Parts and Materials NOTE:

Equivalent substitutes may be used in lieu

of the

following:

NAME

PART NUMBER

MANUFACTURER

Segment,

S-537

Learjet Inc.

Rail

Replace damaged rail

Inboard Rail

USE

S-713

Segment,

Learjet inc.

Replace damaged rail

Outboard 2384042-6

Strap

Fabricate 0.080

2384042-4

Splice

x

Fabricate 0.080

x

locally from

2024-T3 clad

locally from

2024-0 clad

Strengthen

structure

at seat rail union

Strengthen structure at seat rail union

heat treat to T42

2384042

EFFECTIVITY:

ALL

51-70-08

Page 201 SRM-4

Jun1/95

Learjet ~3L-i´•

STRUCTURAL REPAIR MANUAL NAME

Rivet las

required)

PARTNUMBER

MANUFACTURER

MS2aQ70AD5

Commercially available

USE

Secure seat rail and

strap Rivet las

required)

MS20426AD5

Commercially available

Secure

Rivet las

required)

NAS1398B4

Commercially available

Secure diffuser/foot-

splice strip

rest

Rivet las

(3)

Commercially available

MS20426AD3

required)

Repair Procedure: (See Figure 201.) (a) Remove interior equipment and furnishings, carpet, gain access to seat rail. CAUTION:

Attach

nutplates

diffusers and floorboards

as

required

to

SEAT RAIL SEGMENT BEING REPLACED SHALL BE A MINIMUM OF EIGHT BMSTING FASTENER LOCATIONS IN LENGTH.

Cb) For inboard mounted seat rail, (c) For

cut

existing rail

between fasteners in the vertical

flange.

existing fastener locations may be picked up at each splice. outboard mounted seat rail, cut existing rail between frames preferred, at location

that

a

Ensure

minimum of four

between

flange and between seat locking holes in top of flange. Ensure that minimum of four existing fastener locations may be picked up at each splice. (d) Using a #30 drill, drill out rivets securing damaged rail segment to web. (e) Remove damaged seat rail segment. (f) Using a #30 drill, drill out four existing rivets adjacent to forward and aft union locations. (g) Cut new rail segment (S537 or S-713) to fit. fasteners in the vertical

NOTE:

Final trim rail segment to obtain

a

a

0.060 inch maximum gap at each end of rail seg-

ment.

(h) For outboard mounted seat rails, drill 5/16 holes (1.00 spacing) for seat stops in top of vertical flange. (See Detail B,Section B -B.) For inboard mounted seat rails, using measurements from removed seat rail, drill #12 holes in (i)

segment for nutplates to match floorboard attachment hole pattern. Drill #21 holes in vertical flange of rail segment to match rivet holes in web. Cleco holes new

I

(j)

seat rail

as

drilling progresses. (k) Fabricate

two 2384042-4

tener locations in

splice strips.

A

splice strip shall be a minimum

of

eight existing fas-

length.

MATERIAL NOTE:

Splices

shall be fabricated from 0.080

x

2024-0 clad aluminum, final

heat treated to T-42 and final finished to F4-1.

EFFECTlVITY:

ALL

51-70-08

Page 202 SRM~

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL (1)

Fabricate two 2384042-6 straps. A strap shall be tions in length. MATERIAL NOTE:

Straps

a

minimum of

shall be fabricated from 0.080

x

eight existing

fastener loca-

2024-T3 clad aluminum, and fi-

nal finished to F4-1.

(m) Chemically

treat

splice strips

and straps per F4-1 (refer to 51-30-04), and

identify

for future

reference.

(n) Position splice strips on

across

seat rail

joint

so

slice

strips

cover

four

existing

existing

(O) Drill four (two

strip

fastener locations strips to match

joint. Drill #21 holes in upper leg of 2384042-4 splice rivet holes in web and seat rail. Cleco holes as drilling progresses.

each side of seat rail

on

each side of seat rail

splice)

#21 holes

through lower leg of 2384042-4 splice

and web.

Countersink rivet holes in splice strips, as required. Secure splice strips to web with MS20426AD5 and MS20470AD5 rivets. inboard mounted seat rail, position and clamp -6 straps across seat rail unions on lower surFOY (r) face of seat rail horizontal flange. Ensure that straps cover four existing fastener locations on

(p) (q)

each side of seat rail unions.

(s) For outboard mounted seat mil, position and clamp -6 straps

across

four

seat rail unions

surface of seat rail horizontal flange. Ensure that straps cover existing each side of seat rail unions. For inboard mounted seat rail, drill #12 holes in straps to match floorboard

on upper fastener locations

on

(t)

seat rail, refer to step (i). (u) For inboard mounted seat rail,

nutplate

holes in

straps for floor- I board nutplates. Counter sink holes and attach floorboard salvaged nutplates to straps using MS20426AD3 rivets. Clamp straps to seat rail as described in step (r). (v) Drill #21 rivet holes through strap to match existing rivet holes in seat rail. Drill new holes I (0.75 typical spacing) through strap and new seat rail segment. (w) Secure straps to seat rail with MS20426AD5 or MS20470AD5 rivets. I remove

straps from

seat rail. Drill #40 holes in

(x) Remove clamps. Install diffusers, floorboards, carpet and other previously removed equipment and fumish-

(y)

ings. (z) Restore aircraft to normal. (aa) Update all aircraft log books.

EFFECTIVITY:

SRM-4

ALL

51-70-08

Page 203 Tun1/95

STRUCTURAL REPAIR MANUAL NOTES: 1.

r- Denotes existing fastener locations.

I~ Length to be determined at installation. I~ No finish on these surfaces. I~ Rail Configurations, notches (if any) and length to be determined specific aircraft at installation.

detail

for each

For aircraft with diffuser and footrest in-

stalled. Minimum 4 fasteners each and

I~Strap

through

splice, existing nutplate, and/or

A

added

2384042-6

rivets. (MS20426AD5)

j~ 23840423 No. 12 (0.198 Dia.) holes required to match floorboard’s

as

salvaged nutplates

MS20426AD3 Rivets (2 ea.)

r’

cS\YI

~qaP

~I

A

Web

(Ref)

I~>Strap

A

Dspsce

Rivet MS20470AD5

2384042-4

(Min. 2 required each side of gap in lower

leg and web, typical)

st 6.1

A

Rail

~Splice

(Ref) MS20426AD5

2384042-4

(Typical both sides)

0.80 Riveted MS20470AD5

(Minimum 4 places each end through splice)

1.63 0.80

x

032 Jog

Spiice (Ref)

‘Section A A (TYPICAL INBOARD MOUNTED SEAT RAIL)

Detail A Repro

EFFECTNITY:

Seat Rail Repair Figure 201 (Sheet 1 of 2)

ALL

51-70-08

Page 204 SRM-4

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL Co’

,0,41

B~J aP 2384042-6

~Rail 2384042-5

~Strap

_0~3P

7

Min. 0.47

;1

2384042-6

~l;le

CTyp) ’i

D75

´•r~

sOaC’

Rivet MS20470AD5

0~0

Rivet MS20470AD5

(Min. 2 required each

(Min, 4

side of gap in lower

end

leg and web,

places each through splice)

~Splice 23&4042-4

~Splice

Web

2384042-4

(Ref)

’Rivet MS20470AD5

existing locations each end of -4 existing locations through web and 6)

(Min. 4 and

5/16 (0.312 +0.005 /-0.000)--7 Dia. Holes

Rail

.(ReO

1.000

spacing

0.47

0.50 from EOP

~--Strap CTyp) Rivet MS20470AD5

0.16

i,

Splice

(Min. 4 existing or ran and

new

locations each end of -6

through

strap. pick up existing web locations through -5)

(Ren 0.75

RivetMS20426AD5jl OUTED

Section B- B (TYPICAL OUTBOARD MOUNTED SEAT RAIL)

Detail B Repro

Seat Rail

Repair

Figure 201 (Sheet 2 of 2) EFFECTIVITY:

ALL

51-70-081

Page 205 SRM-B

1

Jun 1/951

Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA 1.

GENERAL

General A.

B.

C.

D.

E.

The information in this section is

provided

determining the extent of wear in a providing procedures for specific component/structural

to aid the mechanic in

particular system or component, as well as repair. Original hole sizes, bushing sizes, bolt diameters, and manufactured allowable tolerances as well as repair materials and required treatments or processes will be listed in the appropriate repair procedure. Material and treatment variation is permissible only so far as to facilitate fabrication and ensure the original strength and usefulness of the affected component. It is the responsibility of the aircraft owner/maintenance facility to determine qualifications of maintenance personnel performing inspections and repair procedures as well as to ensure all aircraft log books are properly updated following any maintenance or repair to aircraft structure. As always, a clean environment and good general shop practices shall be exercised at all times. Prior to, and after performing, any repairs on the aircraft structure, ensure serviceability and reliability of repair. If serviceability and/or reliability of repair remains in question or if guidance is needed in making this determination, contact Leajet Field Service for additional information. Repairs must be equal to, or greater in strength, than the original structure. Technique and material variation is permissible only so far as to facilitate fabrication and ensure the original strength and usefulness of the affected component. Limitations applied to repairs and tolerances must be followed unless Leajet engineering authority to the contrary is given. Repairs for structure not included in this section does not necessarily indicate that the structure involved is non-repairable, but that the application of a typical repair procedure to theoretical damage has not yet been developed. For repair procedures pertaining to items not covered in this section, refer to that items respective chapter. Refer to the following sections for allowable wear and repair data: 51-71-01 51-71-02 51-71-03

51-71-04 51-71-05 51-71-06

51-71-07 51-71-08 51-71-09 51-71-10 51-71-11

51-71-12 51-71-13

51-71-14 51-71-15

EFFECTIVITY:

ALL

Passenger/Crew Upper Door

Wing-to-Fuselage Fittings Flap Fittings Spoiler Fittings Aileron System Tip Tank Fittings Landing Gear Fittings Engine Mount Fittings Rudder Control System Horizontal Stabilizer Fittings Elevator Control System Keelbeam Assembly Mach Trim System Control Column Assembly Passenger/Crew Upper Door

51-71-16

51-71-25

Nose Gear Actuator

(36-Inch)

51-71-26

Nose Gear

Passenger/Crew Lower Door

51-71-27

Nose Gear Door Mechanism

(36-Inch)

51-71-28

Flap

(24-Inch) 51-71-17

Passenger/Crew Lower Door

51-71-18

(24-Inch) Quadrant Assembly

51-71-19

MLG Fewer Brake Valve Link-

age

Uplatch

51-71-20

Main Gear Door and

51-71-21

Main Gear Shock Strut

51-71-22

Nose Gear Shock Strut

51-71-23

Main Gear Actuator

51-71-24

Main Gear Door

Uplatch Mech-

anism

Uplatch

Preselect

Assembly

51-71-00

Pagel SRM-4

Jun 6/98

Lenrjet ~L-i´•l STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

WING-TO-FUSELAGE FITTINGS

.-´•,-s~ /I‘

D

C B

A’’

a

Be

(TYPICAL)

Detail A Wing-to-Fuselage Fittings Figure EFFECTNITY:

ALL

Allowable Wear and I (Sheet I of

Repair Data

9)

51-71-01

Pagel SRM-4

Jun 6/98

Learjet LRarjet

STRUCTURAL REPAIR MANUAL WING-TO-FUSELAGE FITTINGS

o~

I 1I~P ii

ALLOWABLE WEAR AND REPAIR DATA

/12

U~

~F

\E I

1D

(On All Excent Aircraft 28-001 and Subseauent; a

29-001 and Swbseauent: 31-001 thru 31-020

a

a

IC II

/F

a

13 10

~3

~L ’9

(On Aircraft 28-001 and Subseauent: 29-001 and Subseauent: 32-021 and Subseauent)

Detail B 4-66A

EFFECTIVITY:

Wing-to-Fuselage Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 9)

NOTED

51-71-01

Page 2 SRM-I

Jun 6/98

Learjet ~Learjet( STRUCTURAL REPAIR MANUAL WING-TO-FUSELAGE FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

/kqi7 H

15

0

24

Detail C

K

J

22

Detail D 4-66A

EFFECTIVITY:

Wing-to-Fuselage Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 9) ALL

51-71-01

Page3 sRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

NO.

DESCRIPTION

Fitting, Soar

1

Bushing

NAS75-10-016

NAS75-9-016

Bushing-

3

MFD SHAFT OD

EFF.

HOLE

ID

18

A

0.5620

12

A

0.6250

MFD

ALLOWANCE

ID

NAS75-8-026

i

ID

ALLOWANCE OD

i f0.0100 0.8142

+0.0015/

+0.0000/

-0.0000

-0.0010

11

A

0.5625

0.6892

+0.0015/

+0.0000/

-0.0000

-0.00010

12

A

0.5000

0.6265

+0.0015/

+0.0000/

NAS75-7-026

11

Bolt- NAS6208-22

12

i

A

0.4375

0.5638

-0.0000

-0.0008

+0.00151

+0.00001

-0.0000 4

OD

WEAR

No. 2

2322275-1,-2, -3, -4 2

MFD HOLE

-0.0007

A

I

1

0.4995

1

1 +0.00011

I

1

0.4330

1

1 +0.00041

-0.0010 AN7-1 7A

11

I

A

12

1

B

0.4991

1

1 +0.00151

C

0.7500

1

1 ~0.0005

B

0.4370

1

1 +0.0010/ -0.0000

C

0.6875

1

C

0.4991

-0.0000

Fitting- 2311161-23

5

-0.0000

6

2311161-8

11

Bushing-

2

2311161-20

1 ~0.0005 0.6219

+0.0015/

~0.0005

-0.0000

2311161-6 7

1

Bushing-2311161-21 2311161-9

5

C

0.4875

0.5608

f0.0005

M.0005

2

C

0.6236

0.7514

+0.0000/

+0.00001

-0.0050

-0.0007

5

C

0.5625

0.6889

+0.0000/

+0.0000/

-0.0050 8

Bolt- NAS464P7L29

11

Bolt- NAS464P8L29

9

I

-0.0007

C

I

i

0.4367

1

1 +0.0000/

C

I

i

0.4991

1

1 +0.0000/

-0.0009 -0.0009 9

Fitting, Spar

No. 5

2822172-1, -2

12

D

0.5620

1

1 +0.0040/

2322278-6, -9 2322278-7, -11

6

D

0.4375

1

1 ~0.0005

7

D

0.4370

1

1 +0.0040/

13

D

0.4375

1

I rt0.0005

14

D

0.4370

1

i +0.0040/

-0.0000

-0.0000

2322278-3, -5, -9 -4,-6,-10 2322278-11,-12

-0.0000

Wing-to-Fuselage Fittings Figure EFFECTIVITY:

ALL

Allowable Wear and 1

Repair Data

(Sheet 4 of 9)

51-71-01

Page 4 SRM-I

Jun 6/98

Learjet ~i STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

10

I

I HOLE

EFF.

DESCRIPTION

I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

3

D

I

1 0.5616

1

1+0.00001

EWSB26-9-30

4

D

I

i 0.5616

1

1+0.00001

EWSB22-7-A30

5

D

I

1 0.4367

1

1+0.00001

(Alt. EWSBM26-7-30)

5

D

I

i 0.4367

1

1+0.00001

AN7-22A

10

D

I

i 0.4370

1

1-0.00001

8

E

0.5620

1

1+0.0040/

E

0.5616

1

1+0.001 5/

E

0.4370

1

1+0.0040/

E

0.5620

1

1+0.0040/

1 Bolt- EWSBM22-9-30

WEAR ID

ALLOWANCE OD

-0.0009 -0.0009 -0.0009 -0.0009

+0.0004 11

I Fitting- 2311181-7,

-8

-0.0000

2311181-3, -4

-0.0000

2311181-1,-2, -5, -6

11

2311181-7, -8

2

I

-0.0000 -0.0000 12

1 Drag Block,

Aft-

2311370-33 LH

RH

15

I

-39 LH 8 RH 241 1 371-3 LH 8 RH

1

16

(Alt. 2411371-17, -18)

13

8

2411371-5, -6 (Alt. 2411371-15, -16) 2411371-15, -16 1 Drag Block, Fwd 2311370-34 LH 8 RH -38 LH 8 RH

2

(Alt. 2411371-11) 241 1 371-2066-1 -2

8

(Alt. 2411371-9, -10) 2411371-1, -9, -10 (Alt. 2411371-11) 14

1 Fitting, Spar

1

0.4680

I

I 1

1

1+0.0060/

I

1 -0.0010

F

0.4680

1

1 ~0.0100

F

0.5938

1

IIH).0100

F

0.5938

1

lf0.0100

F

0.5938

1

IM.0100

F

0.5938

1

I f0.0100

0.4680

1

1+0.0060/

F

0.5938

I 1

1 -0.0010 lf0.0100

F

0.5938

1

IM.0100

F

0.5938

1

1~0.0100

F

0.5938

1

I f0.0100

F

0.5938

1

I f0.0100

F

0.5938

1

I f0.0100

G

0.5620

1

1+0.0080/

F

15

I 17

2411371-1

F

I

I

No. 7-

2822171-3, -4

18

-0.0010

Wing-to-Fuselage Fittings Figure EFFECTIVITY:

ALL

Allowable Wear and

Repair

Data

1 (Sheet 5 of 9)

51-71-01

Page 5 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

15

16

I DESCRIPTION

EFF.

Bushing- NAS75-1 0-016

Bushing-

I

MFD SHAFT

ID

OD

G

i

0.6250

MFD I

0.81 42

ID

+0.0015/

ALLOWANCE OD

-0.0010

+0.0000/

0.5000

0.6265

+0.0015/ -0.0000

-0.0008

1

G

0.5000

0.6265

+0.0015/

+0.0000/

-0.0000 17

i Bolt-NAS6208-22

18

H

18

1 Fitting, Aft-2311201-3, -4,

18

H

0.5000

19

1 Fitting, Fwd-2311201-1,-2,

18

H

0.5000

i

1 0.4995

1

1

1+0.0040/

1

1-0.0000

1

1+0.00401

WEAR ID

ALLOWANCE OD

+0.0000/

-0.0000

G

19

NAS75-8-026

MFD HOLE

HOLE

18

NAS75-8-021

I

-0.0008

1+0.0001/ -0.0010

-7, -8, -15, -16

1

-5, -6, -13, -14 20

Fitting, Soar No.

21

Bushing- NAS75-10-016

2322281-1,

1

1-0.0000

8

-2

22

Bushing-

23

Bolt- NAS6208-22

24

Fitting, Aft-

NAS75-8-021

18

J

0.5625

18

J

0.6250

18

J

i

I M.0100

0.8142

0.5000

+0.0015/

0.6265

-0.0010

+0.0015/

+0.0000/

-0.0000

18

1

J

i

1 0.4995

+0.0000/

-0.0000

1

-0.0008

1+0.0000/ -0.0010

2311211-1, -2, -3, -4, -5, -6, -7, -8, -9, -10 25

K

I

0.5040

i

1

1+0.0000/

1

1-0.0040

1

1+0.0000/

1

1-0.0040

Fitting, Aft2311212-1, -2, -3, -4, -5, -6, -7, -8, -9, -10

26

18

I

Bushing

NAS537-9- 50

K

18

1

I 3

0.5040

I L

0.5620

1

i +0.0015/

L

0.5620

1

i +0.001 5/

-0.0000

(Alt. NAS75-9-01 6)

-0.0000

Wing-to-Fuselage Fittings Figure EFFECTIVITY:

ALL

Allowable Wear and 1

Repair Data

(Sheet 6 of 9)

51-71-01

Page 6 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

Fitting, Spar No.

1

-3,

2322275-1, -2,

Bushing- NAS75-8-026 NAS75-7-026

Bolt

4

NAS6208-22

AN7-17A

2311161-23

Fitting

5

1

Replacewompart. ReamholeAto0.8125

I

(I~to.ooos). NAS75-10-016

NAS75-9-016 3

18

-4

Bushing

2

2

REPAIR

HOLE

EFF.

2311161-8

12

A

Replace worn part.

11

A

Replace

12

A

11

A

12

A

11

A

Replace worn part. Install new bushing with light coat of petrolatum (VV-P-236). Replace worn part. Install new bushing with light coat.of petrolatum (VV-P-236). Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install new bushing with wet primer on exterior surface. Ream bushing (7) to 0.6236 (+0.00051-0.0002) after assembly in fitting (5). Replace worn part. Install new bushing with wet primer on exterior surface. Ream bushing

12

B

12

C

11

B

11

C

6

Bushing

-2311161-20

2

C

5

C

7

2311161-6 Bushing- 2311161-21

2

C

5

C

2311161-9

I

worn

part.

(7) to 0.5625 (+0.0005/-0.0002) after assembly fitting (5). Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

in 11

C

9

C

12

D

6

D

7

D

13

D

14

D

3

D

EWSB26-9-30

4

D

EWSB22-7-A30

5

D

(Alt. EWSBM26-7-30)

5

D

AN7-22A

10

D

2

E

11

E

8

E

Bolt

8

NAS464P7L29

NAS464P8L29

Fitting, Spar

9

No. 5

2822172-1, -2

2322278-6, -9 2322278-7, -11 2322278-3, -5, -9, -4, -6, -10 2322278-11, -12 Bolt

10

11

I

EWSBM22-9-30

Fitting-2311181-7,

-8

2311181-1,-2, -5, -6 2311181-3, -4, -7, -8

Wing-to-Fuselage Fittings Allowable Wear and Repair Data Figure 1 (Sheet 7 of 9)

EFFECTIVITY:

ALL

51-71-01

Page 7 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM NO. 12

DESCRIPTION

1

EFF.

1

REPAIR

Drag Block,Aft2311370-33, -39

15

F

2411371-3

16

F

Replace worn part. Replace worn part.

8

F

Replace worn part.

2

F

Replace worn part.

2311370-34, -38

15

F

2411371-1

17

F

Replace worn part. Replace worn part.

8

F

Replace

1

F

Replace worn part.

18

G

I

18

G

I

19

G

I

1

G

I

18

H

18

H

18

H

(Alt. 2411371-17, -18) 2411371-5, -6 (Alt. 2411371-15, -16) 2411371-15, -16 13

HOLE

DragBlock,

Fwd-

(Alt. 2411371-11) 2411371-2066-1,-2 (Alt. 2411371-9, -10) 2411371-1,-9, -10

(Alt. 2411371-11) Fitting, Spar No. 7 2822171-3,

14

-4

Bushing -NAS75-10-016

15

1

16

1 Bushing-NAS75-8-021

worn

part.

Replacewompart. ReamholeGto0.8125 (~0.0005). Replace worn part. Install new bushing with light coat of petrolatum (VV-P-236). Ream bushing (15) to 0.6273 (f0.0005) after installation.

NAS75-8-026 17

Bolt

18

Fitting, Aft 2311201-3, -4, -7, -8,

19

1

20 21

1

NAS6208-22

-15,-16 Fitting, Fwd-2311201-1,-2, -5, -6, -13,-14 Fitting, Spat No. 8 2322281-1, -2

Bushing-

NAS75-10-016

1

18

1

J

18

J

I

Replace worn part. Install new bushing light coat of petrolatum (VV-P-236). Replace worn part. Install new bushing light coat of petrolatum (VV-P-236). Replace worn part. Replace worn part.

with with

Replacewompart. Replace worn part.

Ream hole J to 0.8125

(~0.0005). Replace worn part. Install new bushing with light coat of petrolatum (VV-P-236). Ream bushing (21) to 0.6273 (f0.0005) after installation.

22

Bushing- NAS75-8-021

18

J

23

Bolt

18

J

NAS6208-22

Replace worn part. Install new bushing light coat of petrolatum (VV-P-236). Replace worn part.

with

Wing-to-Fuselage Fittings Allowable Wear and Repair Data Figure 1 (Sheet 8 of 9)

EFFECTIVITY:

ALL

51-71-01

Page 8 SRM-I

Jun 6/98

Learjet ~Leariet/ STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

25

Fitting 2311211-1, -3, -5, -7, Fitting 2311212-1, -3, -5, -7,

26

Bushing

24

EFF.

DESCRIPTION

NO.

REPAIR

HOLE

-9

18

K

-9

1

K

3

L

Replace Replace

worn worn

part. part.

-2, -4, -6, -8, -10 NAS537-9-050

CODES

Replace worn part. Ream bushing (26) to (+0.0004/-0.0000) after installation.

0.5620

(Alt. NAS75-9-016)

EFFECTIVITIES

Subsequent; 35-001 and Subsequent; 36-001 and Subsequent Subsequent Subsequent; 29-001 and Subsequent; 31-001 thru 31-020 Subsequent and Prior Aircraft Equipped With EWSBM26-9-30 Bolt Subsequent; 36-001 and Subsequent

1

31-001 and

2

31-001 and

3

28-001 and

4

31-021 and

5

35-001 and

6

35-001 thru 35-009; 36-001 thru 36-005 35-010 and Subsequent; 36-006 and Subsequent; and Prior Aircraft

7

Equipped

With 232227&11

Spar

Fitting 8

28-001 and

9

28-001 and

10

23-001 and

11

23-001 and

36-001 and

Subsequent; 29-001 Subsequent; 29-001 Subsequent; 24-100 Subsequent; 24-100 Subsequent Subsequent; 29-001

and

Subsequent Subsequent; 31-001 and Subsequent and Subsequent; 25-001 and Subsequent and Subsequent; 25-001 and Subsequent; and

and

Subsequent;

31-001 and

12

28-001 and

13 14

23-001 thru 23-099; 24-100 thru 24-299; 25-001 thru 25-183 24-300 and Subsequent; 25-1 84 and Subsequent

15

23-001 thru 23-099; 24-100 thru 24-229,

16

Subsequent;

Subsequent

Except 24-218; 25-001 thru 25-066, Except 25-061 24-218, 24-230 and Subsequent; 25-061,25-067 and Subsequent; 35-001 and Subsequent; 36-001 and

Subsequent

17

24-218, 24-230 and Subsequent; 25-061, 25067 and Subsequent

18

23-001 and

24-100 and

29-001 and

31-001 and

23-001

24-100 and

19

35-001 and

29-001

Subsequent; Subsequent; and Subsequent; and Subsequent

Subsequent; Subsequent; Subsequent;

25-001 and 35-001 and 25-001 and

Subsequent; Subsequent; Subsequent;

2&001 and

Subsequent;

36-001 and

Subsequent Subsequent;

2&001 and

Wing-to-Fuselage Fittings Allowable Wear and Repair Data Figure 1 (Sheet 9 of 9)

EFFECTIVITY:

ALL

51-71-01

Page9 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL FLAP FIT~INGS

ALLOWABLE WEAR AND REPAIR DATA

B D

E A:

33

C‘

K

L

?9 3r0

,35

i 30

31

34

M

38 37

Detail A

DetailB

(TYPICAL)

Flap Fittings

8188

EFFECTIVITY:

Allowable Wear and

Figure 1(Sheet

84A

ALL

1 of

Repair

Data

14)

51-71-02

Pagel SRM-I

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL FLAP FI’I~TINGS

ALLOWABLE WEAR AND REPAIR DATA

41

d

)CsP~ P

42

Detail C 44 56

T 45,

D el

55

54

Ij a

46

57´•----

Detail D

58

S

R 47

52

I~ 61

~-I 53

Detail E (TYPICAL)

Flap Fittings Allowable Wear and Repair Data Fi~ure 1 (Sheet 2 of 14)

JEFFECTIVITY:

ALL

51-71-02

Page2 SRM-I

Tun 6/98

Leariet STRUCTURAL REPAIR MANUAL 13

11

~8-

10

2

12

:~CB

.D 8

4

C~k;n

1

Bu

5

A~

7

(INBOARD)

2

22

G

2,5 d

I

~27

20

F

15~cjlE

H

23

19

F

i (OUTBOARD)

(TYPICAL) Ag6C-2 8833C C8116A

Flap Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 14)

DBJX

urasa

EFFECTIVITY: SRM-4

ALL

51-71-02

Page3 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

I

I

MFD

MFD

HOLE

SHAFT OD

IUIFD

ALLOWANCE

EFF.

HOLE I

ID

1

A

0.4390

1

1 +0.0020/

B

0.430

1

1 +0.00201

A

0.4390

1

1 +0.0020/

I

1 -0.0000

1

1 +0.0020/

ID

OD

WEAR ID

ALLOWANCE OD

SupportInner (LH)-2322511-15,

1

-23, -31, -41,-55

-0.0000 -0.0000

Inner (RH)-2322511-16, -24, -30, -42, -56 1

1

I

I B

1

0.430

-0.0000

Outer

(LH)-2322511-17,

A

1

-25, -29, -39, 63

1

0.4390

I B

1

1 +0.0020/

I

1 -0.0000

1

1 +0.00201

0.4390

-0.0000

Outer (RH)-2322511-18

A

1

-26, -28, -40, -54

1

i

0.4390

I

1

1 +0.0020/

I

1 -0.0000

B

0.4390

1

1 +0.0020/ -0.0000

2

3

j

Cap-2322511-9,-45

1

A

0.4390

1

1 +0.0020/

Cap-2322511-8,-43

1

B

0.4390

1

-0.0000 1 +0.0020/

Cam Follower- CF-1-S-CP

1

-0.0000 4

A, A, A, A, A, A, A, A, A,

(Alt. CRS-1GCP) (Alt. CTA-31X-85) (Alt. CR-1X-65) CF-7/8-S-CP

(Alt. (Alt. (Alt. (Alt.

1

CRS-14CP) CTA-27X-41) CR-7/8-27X-41) CR-7/8-X-41)

5

Button- 232251 3-1, -2

6

Nose Track

1

I

B B B

B B B B B B

1

0.1900

1

1 +0.0020/ -0.0000

2322511-7, -27, -44, -46, 7

8

Bushing-

NAS76A4-21

Roller- 2325000-3

C

1

1

-57

I 1

1

0.7550

I C

C

1

1 +0.0050/

i 0.2500 0.3800

1 0.3761 0.7500

-0.0020 +0.0015/

+0.0000/

-0.0000

-0.0005

+0.0000/

~0.0010

-0.0020

Flap Fittings Allowable Wear and Repair Figure 1 (Sheet 4 of 14)

(EFFECTIVITY:

ALL

Data

51-71-02

Page 4 SRM-4

Jun 6/98

Learjet ~LearjetJ

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

Bolt- NAS334CP12-5

9

I

I

MFD

MFD

MFD

HOLE

SHAFT

ID

OD

ALLOWANCE

ID

OD

EFF.

HOLE

2

C

I

1

0.2492

i

1 +0.00001

3

C

I

1

0.2492

1

1 +0.00001

WEAR ID

ALLOWANCE OD

-0.0009

NAS334CP13

-0.0009

101 TrackAssy. 2325022-5;-9, -14, -16 11

I Bearing-

BSSR-6530

1

D

0.8140

1

D

0.3750

1 0.81 25

i f0.0010 +0.0000/

-0.0005

+0.0000/

(Alt. MS21231-6)

D

0.3750

0.81 25

+0.0000/ -0.0005

-0.0005

(Alt. ADW-6)

D

0.3750

0.81 25

+0.0000/

+0.0000/

-0.0005

121

1

14 1

Bushing-

3

1

1

I

0.3710

I

D

3

NAS72-6-005

I

D

2

Bolt-ANG-1Ci AN6-12

13

+0.0000/

-0.0005

1 -0.0000

I 0.5605

0.3750

-0.0005

1 +0.0030/

1 +0.0010/

+0.0000/

-0.0005

-0.0010

InboardTrack Attach

Fitting (LH)-2625023-7, -9,

D

4

1

-11,-15, -17, -21 2492007-1

0.5625

I

I

1

1 +0.0010/

I

1

-0.0000

5

D

0.5625

1

1 +0.0010/

4

D

0.5625

1

1 +0.0010/

I

1 -0.0000

1

1 +0.0010/

-0.0000

(RH)-2625023-8, -10, -12,

1

-16, -18, -22

I

I D

5

2490007-2

0.5625

-0.0000

151 SupportInner

E

1

(LH)- 2322512-6, -17, 1

-19, -51

1

I

0.4390

I

1

1 +0.0020/

I

1 -0.0000

F

0.4390

1

1 +0.0020/

E

0.4390

1

-0.0000

Inner

1

(RH)-2322512-5, -16,

1

-39, -52

I

1 +0.0020/ 1 -0.0000

F

0.4390

i

1 +0.0020/

E

0.4390

1

1 +0.0020/

I

I

-0.0000

Outer (LH)- 2322512-4, -15, -27, -49 1

1

I

1 -0.0000

F

0.4390

1

1 +0.0020/

E

0.4390

1

i +0.0020/

I

1

1

1 +0.0020/

I

I

-0.0000

(RH)-2322512-3, -14,1 1 -28, -50

Outer

1

I F

0.4390

-0.0000

-0.0000

Flap Fittings

Allowable Wear and

Figure

EFFECTIVI~:

ALL

Repair Data

1 (Sheet 5 of 14)

51-71-02

Page SRM-4

5

Jun 6/98

1

Learjet i

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO. 16

Cap-2322512-9, -31,

171

Cap-2322512-8

18 1

Cam Follower-

-32

I

I

MFD

MFD

HOLE

SHAFT

OD

MFD

ALLOWANCE

EFF.

HOLE

ID

1

E

0.3760

i

1 +0.00201

1

F

0.3760

1

1 +0.0020/

ID

OD

WEAR ID

ALLOWANCE OD

-0.0000

-0.0000

CF-7/8-S-CP

(Alt. CRS-14CP)

E

(Alt. CTA-27X-41)

E

(Alt. CR-7/8-27X-41)

E

(Alt. CR-7/8-X-41)

E

Button-2322513-2

19

E

1

1

(Alt. 2322513-1)

I

I

1

i

1 +0.0020/

1

I

I

i

1 -0.0000

1

i +0.0050/

0.1900

Nose Track

20

2322512-7, -13, -37

1

G

0.7550

Bushing-NAS76A4-021

1

G

0.2500

-0.0020

211 22

Roller- 2325000-3

1

G

23

Bolt- NAS334CP12-5

2

G

i

3

G

I

0.3761

0.3800

+0.0015/

0.7500

+0.00001

-0.0000

-0.0005

+0.00001

f0.0010

-0.0020 0.2492

1

1 +0.0000/

0.2492

1

1 +0.0000/

-0.0009

NAS334CP13

i

-0.0009

241

TrackAssy. 2325022-1, -10, -13, -15

25 26

1

Bearing-BSSR-5235 (Alt. MS21231-5) Bolt- AN5-11

1

H

0.6890

1

H

0.3125

I

1

1

I

i

1

f~0.0010

+0.0000/

0.6875

1

-0.0005

+0.0000/ -0.0005

2

H

I

i

0.3108

1

1 +0.0009/

3

H

I

1

0.3108

1

1 +0.0009/

3

H

-0.0000 NAS464P5-17

-0.0000 27

Bushing- NAS72-5-005

0.3125

0.4980

+0.001 0/

-0.0005

-0.0001

+0.000/

Flap Fittings Allowable Wear and Repair Data Figure 1 (Sheet 6 of 14)

(EFFECTIVITY:

ALL

51-71-02

Page 6 sRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 28

I

I EFF.

DESCRIPTION

I

MFD

MFD

MFD

HOLE

SHAFT

HOLE

ID

OD

H

0.5000

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Outboard Track Attach 1

Fitting (LH)- 2625024-3, 1

-5,-7

(RH)

r

I H

1

2625024-4, -6, -8

0.5000

1

i +0.0010/

I

1

1

1 +0.0010/

-0.0000 -0.0000

29

Sector6

2625031-1,-2, -6

J

0.3747

i

1 +0.0015/

K

1.2500

1

1 +0.0050/

L

0.7500

1

1 +0.0100/

J

0.3747

1

i +0.0015/

1.2500

1

1 +0.0050/

L

0.7500

1

1 +0.0100/

J

0.3747

1

i +0.0015/

1.2500

1

i +0.0050/

L

0.7500

1

1 +0.0100/

J

0.3747

1

1 +0.001 5/

1.2500

1

1 +0.0050/

0.7490

1

1 +0.0100/

-0.0000 -0.0000 -0.0000 7

2625031-9, -10

-0.0000 K

1

-0.0000 -0.0000

2625031V1-1, -2

8

-0.0000 K

1

-0.0000

-0.0000 9

2625031-13, -14

-0.0000 K

1

-0.0000 L

-0.0000 30

311 32

Bearing- AN200KP5 (Alt. MS27640-5) Spacer-NAS43DD5-79 Bolt- NAS1305-42H

K

1

I

i

0.3125

I

I K

1

10

1.2500

i

0.3200

1 0.4280

+0.0000/

+0.0000/

-0.0005

-0.0005

+0.0400/

+0.020/

-0.0000

-0.0000

K

I

i

0.3110

1

1 +0.0010/

K

I

i

0.3110

1

1 +0.0010/

-0.0000 NAS6605-44

11

I

-0.0000

Flap Fittings

Allowable Wear and

Figure

EFFECTIVITY:

ALL

1

Repair Data

(Sheet 7 of 14)

51-71-02

Page SRM-I

7

Jun 6/98

1

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.

I DESCRIPTION

Bearing- MS21233-5

33

I

I

MFD

MFD

HOLE

SHAFT

MFD

ALLOWANCE

EFF.

HOLE

ID

OD

ID

OD

1

L

0.3125

0.7500

+0.00001

+0.00001

-0.0005

WEAR I

ID

ALLOWANCE OD

-0.0005

34 1

Bolt- NAS464P5-10

1

L

i

1

0.3108

1

1 +0.00001

35

Bolt- NAS464P6-28

1

J

I

i

0.3742

1

1 +0.00001

36

Bolt- NAS464P4-11

1

M

i

1

0.2492

1

1 +0.00001

37

Bracket

-0.0009

-0.0009 -0.0009

Assy.

2325079-3, -4, -11,-12, -17,-18

1

I

38

Bracket

39

Pulley- MS20221-A1

Assy.

M

1

i

1

0.0250

I

1

N

1

N

i

i

I

1 +0.00051

1

I

1 -0.0000

1 f0.0100

0.3120

2425081-1,-11 0.3125

2.6250

+0.0000/

f0.005

-0.0005

Bolt- NAS1305-19H

40

I

1

1

N

1

P

0.3120

1

P

0.3125

0.3110

+0.001 0/ -0.0000

41

1

I

BracketAssy.-

1

1 +0.0100

2325080-1,-11 42

Pulley

MS20221-A1

2.6250

+0.0000/

~0.005

-0.0005 43

Bolt- NAS464P5-15

44

Bracket

45

Pulley- MS20221-A1

I

1

1

P

12

0

0.3120

1

13

Q Q

0.3120

1

0.3117

1

1 +0.0000/ -0.0009

Assy.

2625040-57

2625038-1,-2

14

0.3125

I ~t0.0100 I f0.0100

+0.0000/

2.6250

rt0.0050

-0.0005 46

Screw- NAS335CP20

14

Q

47

Bracket- 2325080-19

14

R

0.3120

48

Pulley- MS20221-A1

14

R

0.3125

I

i

0.3117

1

1 +0.00001 -0.0009

1 +0.0006/

1

-0.0001 2.6250

+0.0000/

f0.0005

-0.0005

49

Bolt- NAS464P5-12

14

50

Bracket- 2325080-20, -44, -52

14

51

Plate-2325080-21

14

1

R

I

i

0.3117

1

1 +0.0000/ -0.0009

S

1 1

0.3120

I S

0.3120

S

0.3125

1

1 +0.0006/

I

i

0.0001

1

1

+0.006/ -0.0001

52

Pulley-

MS20221-A1

14

2.6250

+0.0000/

~0.0005

-0.0005

Flap Fittings Allowable Wear and Repair Figure 1 (Sheet 8 of 14)

1EFFECTIVITY:

ALL

Data

51-71-02

Page8 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

I

I

MFD SHAFT

ID

HOLE

EFF.

MFD HOLE

I

I

OD

1

0.3117

MFD

ALLOWANCE

ID

53

Bolt- NAS464P5-17

14

1

S

1

54

Bracket- 2825082-4, -6

15

1

V

0.3160

1

1 +0.00001

Pulley-2815086-1

15

T

0.9370

1

1 +0.0000/

15

T, V

0.3125

OD

WEAR ID

ALLOWANCE OD

1+0.0000/ -0.0009 -0.0000

55

1

56

1 Bearing-

-0.0005

PD5K-FS464

+0.0000/

0.9370

-0.0005 57

1

Bolt-NAS464P5-24

15

58

1

Bracket-2825082-1, -3

15

T

I

1

0.3117

1

+0.0000/ -0.0005

1 +0.0000/ -0.0009

1

W

0.3160

U

0.31 25

1

1 +0.0000/ -0.0000

Pulley-

59

MS20221-A1

15

+0.0000/

2.6250

f0.0005

-0.0005 60

1

Bolt-NAS464P5-24

15

U

61

1

Bracket-2825083-7

15

X

Bolt- NAS464P5-13

15

U

I

1

0.3117

1

i +0.0000/ -0.0009

0.3160

1

1+0.0000/ -0.0000

62

I

1

0.3117

1

1 +0.0000/ -0.0009

Flap Fittings Allowable Wear and Repair Data Figure 1 (Sheet 9 of 14) EFFBCTnTrry:

ALL

51-n-o2

Page9 SRM-4

Jun 6/98

I

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

EFF.

1

SupportInner (LH) 2322511-15, -23, -31,

1

A, B

Replace

worn

part.

1

A, B

Replace

worn

part.

1

A,

B

Replace worn part.

HOLE

REPAIR

-41,-55 Inner

(RH) 2322511-16, -24, -30,

-42, -56 Outer (LH) 2322511-17, -25, -29,

-39,-53 Outer

(RH)

2322511-1 8, -26, -28,

1

A, B

Replace worn part.

1

A

3

-40, -54 Cap 2322511-9, -45 Cap 2322511;8, -43

1

B

4

Cam Follower

1

A, B

Replace worn part. Replace worn part. Replace worn part.

1

A, B

Replace worn part.

2

CF-1-S-CP

(Alt CRS-1GCP) (Alt CTA-31X-85) (Alt CR-1 X-65) CF-7/8-S-CP

(Alt (Alt (Alt (Alt

CRS-14CP) CTA-27X-l1) CR-7~27X-41) CR-7~X-41)

Button

5

2322513-2

1

I

I

(Alt. 2322513-1)

If

spanwise

cam

6

Nose Track

7

Bushing

2322511-7, -27, -44, -46, -57

1

C

NAS76A4-21

1

C

1

C

8

Roller

9

Bolt

2325000-3

NAS334CP12-5

NAS334CP13 Track

Assy. 2325022-5, -9, -14, Bearing BSSR-6530 (Alt. MS21231-6) (Alt. ADW-6)

10 11

12

1

-16

Bolt-ANG-16 AN6-12 NAS72-6-005

13

Bushing

14

Inboard Track Attach

tend play) of flap exmaximum, replace buttons followers (4). movement

ceeds 0.34 inch

Fitting -2625023-7, -9, -11,-15, -17,-21

2

C

3

C

1

D

1

D

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part.

part. part. part.

part. part. part. Secure with Loctite.

2

D

3

D

3

D

Replace Replace Replace

4

D

Replaceworn part. Replace worn part. Replace worn part. Replace worn part.

2492007-1

5

D

2625023-8, -10, -12, -16, -18, -22

4

D

2492007-2

5

D

worn worn

worn

on

Flap Fittings Allowable Wear and Repair Data Figure 1 (Sheet 10 of 14)

JEFFECTIVITY:

ALL

51-71-02

Page SRM-I

10

Tun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO. 15

Inner

1

Inner

1

17

18

Cam Follower-

CF-7/8-S-CP

E, E, E, E,

1 1

F

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

F F F

1

E

1

F

1

E, F

Replace worn part

1

2322513-2

Button

I

I

21

Nose Track

Bushing

22

Roller

23

Bolt

2322512-7, -13, -37

NAS76A4-21

2325000-3

NAS334CP12-5

NAS334CP13 24

Track

Assy.

If

spanwise

movement

tend play) of flap

ceeds 0.34 inch maximum, cam followers (18).

(Alt. 2322513-1) 20

part. part. part. part. part. part.

CRS-14CP) CTA-27X-41) CR-7/8-27X-41) CR-7/8-X-41)

(Alt. (Alt. (Alt. (Alt. 19

REPAIR

HOLE

1 Support(LH) 2322512-6, -17, -19, 61 (RH) 2322512-5, -16, -30, -52 Outer (LH) 2322512-4, -15, -27, -49 Outer (RH) 2322512-3, -14, -28, -50 Cap 2322512-9, -31, -32 Cap 2322512-8

16

EFF.

2325022-1, -10, -13,

1

G

1

G

1

G

2

G

3

G

1

H

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

replace

ex-

buttons

on

part. part. part. part. part. part.

-15

25

Bearing BSSR-5235 (Alt. MS21231-5)

1

H

26

Bolt

AN5-11

2

H

NAS464P5-17

3

H

3

H

1

H

1

H

NAS72-5-005

27

Bushing

28

Outboard Track Attach

Fitting 29

30 31

(LH) 2625024-3, -5, -7 (RH) 2625024-4, -6, -8

1 Sector 2625031-1, -2, -6

6

2625031-9, -10

7

2625031V1-1,-2 2625031-13, -14

8

Bearing AN200KP5 (Alt. MS27640-5) 1 Spacer MS43DD5-79

9

J, J, J, J,

K, K, K, K,

1

K

1

K

I Replace worn part. Replace Replace Replace

L L

L L

worn worn worn

Replace worn Replace worn Replace worn Replace worn Replaceworn Replace worn Replace worn

ALL

part. part. part. part. part. part. part. part. part. part. Secure with Loctite.

I Replace worn part.

Flap Fittings Allowable Wear and Repair Figure 1(Sheet 11 of 14) EFFECTNITY:

Secure with Loctite.

Data

51-71-02

Page SRM-4

11

Jun 6/98

1

Leariet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

32

EFF.

DESCRIPTION

NO.

I

Replacewompart.

11

NAS6605-44 33

K

10

Bolt- NAS1305-42H

REPAIR

HOLE

Bearing- MS21233-5

L

1

Replace

worn

part.

Secure with Loctite and

stake. 34

Bolt

NAS464P5-10

1

L

35

Bolt

1

J

36

Bolt

NAS464P6-28 NAS464P4-11

1

M

37

Bracket

1

M

1

N

1

N

1

N

1

P

1

P

39

Assy. 2325079-3, -4, -11, -12,-17,-18 Bracket Assy. 2425081-1, -11 Pulley MS20221-A1

40

Bolt

41

Bracket

Assy.

42

Pulley

MS20221-A1

43

Bolt

38

44

NAS1305-19H

2325080-1, -11

NAS464P5-15 Bracket Assy. 2625040-57

2625038-1,-2

1

P

12

Q

13

Q

14

MS20221-A1 NAS335CP20

14

Q Q

2325080-19

14

R

45

Pulley

46

Screw

47

Bracket

48

Pulley MS20221-A1

49

Bolt

50

Bracket- 2325080-44

NAS464P5-12

14

R

14

S

14

S

14

S

14

S

Replace worn Replace worn Replace worn Replace worn

part. part. part. part.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part. part. part. part. part. part. part.

Replace

worn

Replace worn Replace worn Replace worn Replace worn Replacewompart.

(Alt. 2325080-44) 51

Plate

2325080-21

MS20221-A1

52

Pulley

53

Bolt

54

Bracket

55 56

Pulley 2815086-1 Bearing PD5K-FS464

NAS464P5-17

2815082-4, -6

NAS464P5-24

57

Bolt

58

Bracket

59

PJ~ey- MS20221-A1

60

Bolt

61

Bracket

62

Bolt

2825082-1, -3

14

S

15

V

15

T

15

T, V

15

T

15

VV

15

U

NAS464P5-24

15

U

2825083-7

15

X

NAS464P5-13

15

U

Flap Fittings

EFFECTIVITY:

ALL

I

1

worn worn

part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn pact. Replace worn part. Replacewompart. Replace worn part. Replace worn part. Replace worn part.

Allowable Wear and

Figure

I

Replace Replace

Repair Data

(Sheet 12 of 14)

51-71-02

Page SRM-I

12

Jun 6/98

Learjet I~ri´•tl STRUCTURAL REPAIR MANUAL CODES 1

EFFECTIVITIES 23-001 thru 23-099; 24-100 and

Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-003 thru 23-099 Except When Modified by SSK 934 "Replacement of Wing Flap Assembly"; 24110 thru 24327 Except When Modified by SSK 934 "Replacement of Wing Flap Assembly"; 25-001 thru 25-204 Except 25-135 and 25-188 and Except When Modified by SSK 934 "Replacement of Wing Flap Assembly"; 35-001 thru 35-059 Except When Modified by SSK 934 "Replacement of Wing Flap Assembly"; 36-001 thru 36-017 Except When Modified by SSK 934 "Replacement of Wing Flap Assembly" 23-003 thru 23-099 When Modified by SSK 934 "Replacement of Wing Flap Assembly"; 24-328 and Subsequent and Prior Aircraft Modified by a SSK 934 "Replacement of Wing Flap Assembly"; 25-205 and Subsequent and Prior Aircraft Modified by SSK 934 "Replacement of Wing Flap Assembly"; 28001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-060 and Subsequent and Prior Aircraft Modified by SSK 934 "Replacement of Wing Flap Assembly"; 36-018 and Subsequent and Prior Aircraft Modified by SSK 934 "Replacement of Wing Flap Assembly" 31-001 thru 31-049; 35001 thru 35673; 36-001 and Subsequent; Except Aircraft With 2625023-9 or 2492007-1 Inboard Track Attach Fitting Installed 31-050 and Subsequent; 35-674 and Subsequent; Except Aircraft With 2625023-9 or 2492007-1 Inboard Track Attach Fitting Installed 23-001 thru 23-099; 24-100 and Subsequent; 25-001 thru 25-373; 28-001 thru 28-005; 29-001 thru 29-004; 35-001 thru 35-055; 36-001 thru 36-605, Except 36-060 and 36-061 25374 and Subsequent; 2&006 and Subsequent; 29-005 and Subsequent; 31-001 thru 31-032; 35056 and Subsequent; 36-606 thru 36-664 001 and

2

3

4

5

6 7

8

31-033 thru 31-047; 35-665 thru 35-672

9

31-033 and

10

23-011, 23-012, 23-015, 23-019, 23-031, 23-039, 23-050a and Aircraft Modified Per ECR 392; 23090 and Subsequent Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 24-100 and Subsequent Except When Modified by SE 23/ 24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 25-001 and Subsequent Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 28-001 and Subsequent Except When Modified by SE 23/24/25/2557-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 29-001 and Subsequent Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 31-001 thru 31-129 Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 35-001 thru 35-676 Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 36-001 thru 36-063 Except When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actua-

Subsequent Except When 2625031\11-1 or 2625031\/1-2 Sector Is Installed; 35-673 and Subsequent Except When 2625031V1-1 or 2625031V1-2 Sector Is Installed; 36-060, 36-061 and 36665 and Subsequent Except When 2625031V1-1 or 2625031V1-2 Sector Is Installed

tor and

Flap

Sector

Support Brackets"

Flap Fittings Allowable Wear and Repair Figure 1 (Sheet 13 of 14) EFFECTIVITY:

ALL

Data

I 51-71-02

Page SRM-I

13

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL CODES 11

EFFECTIVITIES 23-090 and

Subsequent When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator Flap Support Brackets"; 24-100 and Subsequent When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 25-001 and Subsequent When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 28-001 and Subsequent When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 29-001 and Subsequent When Modified by SE 23124/25/2557-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 31-130 and Subsequent and Prior Aircraft When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 35-677 and Subsequent and Prior Aircraft When Modified by SE 231 24/25/25-57-1, "Replacement of Spoiler Actuator and Flap Sector Support Brackets"; 36-064 and Subsequent and Prior Aircraft When Modified by SE 23/24/25/25-57-1, "Replacement of Spoiler Acand

Sector

tuator and 12

13 14

15

Flap Sector Support Brackets"

24-329 thru 24-348; 25-206 thru 25-224; 35-067 thru 35-115; 36-018 thru 36-032 24-349 and Subsequent, 25-225 and Subsequent; 28-001 and Subsequent; 29-001 and 31-001 and Subsequent; 35-116 and Subsequent; 36-033 and Subsequent

23-001 thru 23-099; 24-100 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent

Flap Fittings

Allowable Wear and

Figure

I

EFFECTTVITY:

Subsequent;

ALL

1

Repair Data

(Sheet 14 of 14)

51-71-02

Page SRM-4

14

Jun 6/98

Learjet STRUCT’URAL REPAIR MANUAL SPOILER FITTINGS

I Y~ )i

e

ALLOWABLE WEAR AND REPAIR DATA

H

18

,G 17

15

4 12 7

K

21

11

20

G

.i

D

8 18

Spoiler:Fittings Allowable Wear and Repair Figure 1 (Sheet 1 of 5)

EFFECTIVITY:

ALL

19

Data

51-71-03

Pagel SRM-4

Jun 6/98

Leariet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I EFF.

DESCRIPTION

NO.

Hinge Arm,

1

Inboard

1

Sleeve- 2322510-65

I HOLE A

1

2322510-2 thru -144 2

I

I

MFD SHAFT

ID

OD

0.5620

I A

1

MFD HOLE

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

i +0.00501 1 -0.0010

1 I

0.4410

MFD

0.5600

+0.00301

It0.0010

-0.0000

Bearing-

3

PB-814-14

A

1

0.2520

+0.0000/

0.4400

+0.0000/

-0.0010 4

Bolt-AN4-13A,-14A

1

A

5

Hinge Bracket

1

B

6

Fitting 2422513-1(Hole C

1

C

I

1

0.2490

1

-0.0010

1 +0.0000/ -0.0030

2322514-5,-11,-6,-12 Inbd side, Hole D Outbd

1

0.250

j

I

0.4375

I

side)

D

0.3755

C

0.2500

1

1 +0.0050/

I

1 -0.0010

1

1 +0.00001

I

1

1

1 +0.00001

-0.0010

-0.0005 7

1

1

Bushing-NAS77-4-06

8

Bushing- NAS724-002

1

9

Bolt- BACBSONJ4D10

1

D

+0.0015/

0.3761

0.2500

0.4355

+0.0000/

-0.0000

-0.0005

+0.00101

+0.0000/

-0.0005

I

BACB30NJ4D12 10

1

Arm

Assy -2422511-8,-13

I

i

I 2

1

I

0.2495

-0.0010

1 +0.0000/

1

E

0.2492

I 1

I 1 -0.0010 1 +0.0010/

F

0.4410

1

1 +0.0030/

G

0.2500

1

1 +0.0020/

E

0.2492

1

1 +0.001 0/

F

0.4410

1

1 +0.0030/

G

0.3120

1

1 +0.0020/

-0.0000 -0.0000 -0.0010 3

2422511-18, 31,-32

-0.0000

-0.0000 -0.0000 11

I

Bolt-NAS464P4-13

NAS464P4A11 12

1

Bearing- PB1014-14 (Alt. AA401-12)

13

1

Bolt- NAS464P5-20

I

1

I

I

I F

1

I

i

1

I

I

F

1

NAS464P5-17 14

E

1

I

0.3145

0.2492

1

I

I

1

I

I

1 -0.0009 +0.0000/

0.4400

I

1 +0.0000/

I

1 0.3117

-0.0010

1

1 +0.0000/ 1 -0.0009

I

Hinge Bracket-2422514-1, -2 thru

-43,

-44

2

H

0.3120

3

H

0.3756

+0.0060 -0.0000

2422514-57,-58, -60,-61

1

1 +0.0015 -0.0000

Spoiler Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 5) EFFECTIVITY:

ALL

51-71-03

Page2 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

DESCRIPTION

NO.

15

I

1 Bushing-2422514-63

I

I

MFD

MFD

HOLE

SHAFT

ALLOWANCE

MFD

EFF.

HOLE

ID

OD

ID

OD

3

H

0.31 20

0.3761

+0.0060/

+0.0000/

Bolt- NAS464P5A14

ID

ALLOWANCE OD

-0.0005

-0.0010

16

WEAR

3

G

I

1

0.3117

1

1 +0.0000/

2

G

I

1

0.2492

1

+0.0000/

3

G

0.3120

1

1 +0.0020/

2

G

0.2500

1

1 +0.00201

1

G

0.3120

1

1 +0.0020/

-0.0009

NAS464P4A13

-0.0009 17

1

HingeArm-2422541-2

-0.0000 2422541-1

-0.0010

Angle-

2322510-29, -30

-0.0000 18

1 HingeBracket1

J

Bolt-AN4-14A

1

J

Bearing- PB-814-14

1

J

0.2520

1

K

0.5620

1

K

0.4410

2322514-7, 8

0.2500

1

1 +0.0050/ -0.0010

19

1

I

1

0.2490

1 +0.0000/

1

-0.0030 20 21

1 Hinge

Arm-2322510-143

0.4400

+0.0000/

+0.0000/

-0.0010

-0.0010

1 +0.0050/

1

-0.0010 22

Sleeve- 232251 0-65

0.5600

+0.0030/

~0.0010

-0.0000

Spoiler Fittings Allowable Wear and Repair Figure 1 (Sheet 3 of 5) EFFECTNITY:

ALL

Data

51-71-03

Page3 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

1

Hinge Arm, Inboard

2

1 Sleeve-2322510-65

2322510-2 thru -144

EFF.

HOLE

1

A

1

A

REPAIR

Replace worn part. Replace worn part.

Install

new

sleeve with

Loctite. 3

Bearing

4

Bolt

5

Hinge

PB-814-14

AN4-14A

Fitting Bushing-

-12

2422513-1

7

A

1

A

Replace worn part. Replace worn part.

Bracket-

2322514-5,11,-6, 6

1

NAS77-4-06

1

B

1

C

1

C

Replace worn part. Replace worn part. Replace worn part.

Install new bushing with primer. No substitution of parts. I Replace worn part. Install new bushing with wet primer. No substitution of parts. Replace worn part. No substitution of parts. wet

8

Bushing- NAS72-4-002

1

D

9

Bolt

1

C,D

-13

2

2422511-18 thru -31, -32

3

E, F,G E, F,G

BACB30NJ4D10

BACB30NJ4D12 10

i

Arm

Assy. -2422511-8,

Replacewornpar. Replacewompart.

11

Bolt

1

E

12

Bearing PB1014-14 (Alt.AA401-12)

1

F

13

Bolt

1

F

Replace worn part.

14

Hinge, Bracket2422514-1 thru -44

2

H

2422514-57, -58, -60, -61

3

H

Replace worn part. Replace worn part. Replace worn part. wet primer. I Replace worn part.

NAS464P4-13, NAS464P4A11

15

1 Bushing-2422514-63

3

H

16

1 Bolt

1

G

17

1 Hinge

2

G

3

G

1

G

NAS464P5A14, NAS464P5A13 2422541-1

2422541-2

Angle 2322510-29,

new

bearing with

Loctite.

NAS464P5-20, NAS464P5-17

Arm

Replace worn part. Replace worn part. Install

-30

Install

Replace worn part. Replace worn part. Replace worn part. Ream hole G in angle (17)

new

bushing with

to 0.312

(+0.002/-0.000) after installation. 18

Hinge Bracket

19

Bolt

20 21

22

2322514-7, -8

1

J

1

J

Bearing PB-814-14 Hinge Arm 2322510-143

1

J

1

K

Sleeve

1

K

AN4-14A

2322510-65

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. Install

new

sleeve with Loc-

tite.

Spoiler Fittings Allowable Wear and Repair Figure 1 (Sheet 4 of 5) EFFECTIVITY:

ALL

Data

51-71-03

Page$ SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-001 thru 23-099; 24-100 thru 24-302, 24-309 thru 24317; 25-001 thru 25-194; 35-001 thru 35-

3

24-303 thru

032; 36-001 thru 36-013 24-308, 24-318 and Subsequent; 25-195 and Subsequent; 31-001 and Subsequent; 35033 and

Subsequent;

36-014 and

Subsequent

Spoiler Fittings Ailowable Wear and Repair Data Figure 1 (Sheet 5 of 5) EFFECTIVITY:

ALL

1 51-71-03

Page 5 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

B

G

F

L

J

A

~C

’E

A

W (TYPICAL) 813B2

Aileron

EFFECTIVITY:

System Fittings Figure

ALLORAS NOTED

Allowable Wear and 1

Repair Data

(Sheet 1 of 28) 51-71-04

Page SRM-4

1

Jun 6/98

Learpt

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

AILERON SYSTEM FITTINGS

.6

3

P ~f q

8

A

Bj D

Wing

Detail A (TYPICAL) Aileron

86B 4-4C-2

(EFFECTIVITY:

System Fittings Figure

Allowable Wear and 1

(Sheet

2 of

Repair

Data

28)

51-71-04

ALL _

Page2 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

Q~P

I

a.

J

16

178

15

14

13

F .z~s

Detail B Aileron

4-4C-2

EFFECTIVITY:

ALL

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 3 of 28) 51-71-04

Page3 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINCS

ALLOWABLE WEAR AND REPAIR DATA

Y

21

25

22

G´• 28

i 23

gC

~9

Detail C

8

~30

K

(TYPICAL) Aileron

B810C B46A C4-5B1

(EFFECTIVITY:

ALL

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 4 of 28)

51-71-04

Page4 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

AILERON SYSTEM FITTINGS

33´•

(AII Excetlt Model 31 Series Aircraft)

Detail E M 37

M 37 i

35

Detail F 3,8

3Q

N

;I

38

40

Detail G Aileron

EFFECTIVITY:

System Fittings Figure

ALL ORAS NOTED

Allowable Wear and

Repair

Data

1 (Sheet 5 of 28)

51-71-04

Page 5 SRM-I

Jun 6/98

1

Learjet

STRUCTURAL REPAIR NIANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

P 41

43

i ’d~

B

Detail H

44k

49

R

O

48~

(All Excetlt Model 31 Series Aircraft)

(All Excetlt Model 31 Series Aircraft)

Detail J

Detail K (TYPICAL)

Aileron

I

EFFECTIVITY:

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 6 of 28)

AU ORAS NOTED

51-71-04

Page 6 SRM-4

Jun 6/98

Learjet ~Learpt

STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

59

ALLOWABLE WEAR AND REPAIR DATA

AM

S a

51

53

~d

50’ r

j

o

52

50

AM

D eta i I L

58

T

55

60

57

.ig (AIl Excetlt Model 31 Series Aircraft)

(All Excetlt Model 31 Series Aircraft)

DetailM

Detail N (TYPICAL)

Aileron

EFFECTMTY:

System Fittings Figure

ALL ORASNOTED

Allowable Wear and 1

(Sheet

7 of

Repair Data

28)

51-71-04

Page 7 SRM-4

Jun 6/98

Learjet I C~ Learjet

STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

a (AIl Excetlt Model 31 Series Aircraft)

j

Detail P

65

64

W

e 66

63

~79 gc~

(A12

Model 31 Series Airmaft)

DetailQ

Detail R (TYPICAL)

Aileron

EFFECTIVITY: SRM-4

System Fittings Figure

ALL ORAS NOTED

Allowable Wear and 1

Repair Data

(Sheet 8 of 28) 51-71-04

Page 8 Tun 6/98

Learjet Ledrptl STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

~U"I

Eletail S ~lY3 72

e3~1; "ai

Y

76

Z

75

Y

1

DetailT

78

i/

Detail U (TYPICAL) Aileron

EFFECTIVITY:

NOTED

System Fittings Allowable Wear and Repair Figure 1 (Sheet 9 of 28)

Data

51-71-04

Page9 sRM-a

Jun 6/98

1

Learjet i

STRUCTURAL REPAIR MANUAL AILERON SYSTEM FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

AK 85

79/ ~3h, I AL

sp

82

AJ

,AG AB

AH

,88

AF _

AD

1 AE

DetailV

,81

AA

a;e

90

~1

,92 93

91r

AA

AB

Detail W

Aileron

(EFFECTNITY:

NOTED

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 10 of 28) 51-71-04

Page SRM-I

10

Jun 6/98

Learjet ~Learjetl STRUCTURAL REPAIR MANUAL AILERON SYSTEM PITTINGS

ALLOWABLE WEAR AND REPAIR DATA

A

uh 99~

C

f

BJ

38--´•´•

AQ 97

B

r i’

~i

99~AM

Detail B

r~ n

AC

Detail C

Aileron

EFFECTIVITY:

NOTED

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 11 of 28) 51-71-04

Page SRM-I

11

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.

I EFF.

DESCRIPTION Inboard

1

I

I HOLE I

MFD

MFD

HOLE

SHAFT

MFD

ID

I

ID

0.9005

i

1 +0.00051

I

1 -0.0000

OD

WEAR

ALLOWANCE OD

I

ID

ALLOWANCE OD

Hinge Bracket

2322530-3, -39, -40, -55, -56, -59, -60, -67, -68, -81, i

A

2

I

I

-82

Bearing-

2

BP-4

2

1

A

0.9014

1

1 +0.0000 -0.0005

KSP-4

4

A

0.9014

1

1 +0.0000

MS27645-4

3

A

0.9014

1

1 +0.0000

Bolt- AN4H1IA

5

A

I

1

0.2460

1

1 +0.0030/

6

A

I

1

0.2460

1

1 +0.0030/

-0.0005 -0.0005 3

-0.0000 AN4H12A

-0.0000

Middle

4

Hinge

Bracket B

2322530-19, -20, 27, -28, -51, -52, -89, -90 1

1

MS27645-4

1

B

1

B

5

Bearing-

6

Bolt- AN4H13A

7

Angle and Plate

8

Stud- 2322530-33, -53

9

Outboard

I

0.9005

1

1 +0.0005/

I

I

1 -0.0000

I

1

0.2460

1

1 +0.0030/ -0.0000

C

2322530-29, -30, -31, -32

Hinge

1

Bearing- N1827645-4 Bolt- AN4H11A

11

E

1

I

I

I

1

1 +0.0010/ 1 -0.0000 0.2492

1

1 +0.00001 -0.0009

Bracket

2322530-41, -42, -63, -64, -75,-76,-79,-80 1 10

I

1

0.2492

D

1

I

1

1 +0.0005/

I

0.9005

I

1 -0.0000

1

D

5

D

I

1

0.2460

1

1 +0.0030/

6

D

I

1

0.2460

1

1 +0.0030/

-0.0000 AN4H12A

-0.0000

121

Horn-

2324011-28

7

E

0.6560

1

1 +0.0020/

2324011-235

8

E

0.6560

1

1 +0.0020/

8

E

-0.0000 -0.0000

13

1

Bearing- ABT4-105

Aileron

I

EFFECTIVITY:

ALL

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 12 of 28)

51-71-04

Page SRM-4

12

Jun 6/98

Leariet ~Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

141

I HOLEI

EFF.

DESCRIPTION

NO.

I

MFD

MFD

HOLE

SHAFT OD

ID

MFD

WEAR

ALLOWANCE

ID

OD

Bolt-AN4-7

7

E

i

1

0.2490

1

1 +0.0010/

NAS464P4-8

8

E

I

1

0.2483

1

1 +0.0009/

I

ID

ALLOWANCE OD

-0.0000 -0.0000

Clevis Rod End

15

2433003-2

9

E

0.2492

1

1 +0.001 0/

2333001-7

10

E

0.2492

1

1 +0.00101

-0.0000

-0.0000 16

1 Bearing

Rod End-

F

1

HFV-L1

F

(Alt. TR-4) (Alt. REF-4) 17

F

BoR-AN4-I1

F

1

I

1

0.2460

1

1 +0.0030/ -0.0000

17A

I

F

0.2500

1

1 +0.0050/

12

F

0.2500

1

1 +0.0050/

13

F

0.2500

1

1 *0.0050/

0.9015

1

I f0.0010

0.9015

Actuator- 2380027-10

11

ActuatorArm-233300&3

-0.0010

181

-0.0010

23330086

-0.0010 19

Yoke- 232451 &1

14

15

20

2324511-5 BoR- NAS464P3-33

G, H G, H

14

G

I

1 1

0.2485

I rt0.0010 1 1 +0.0010/

G

I

1

0.2485

1

-0.0000 15

NAS1 304-34H NAS11 04-380

1

211 Bearing-MS27644-4

22

(Alt. DDP4) (Alt. BP4) (Alt. BR4) Bushing-

I

I G

1

I

NAS75-4-009

I 1

(Alt. MS27645-4) (Alt. KSP´•Q)

0.2500

I

0.3761

0.2500

1

Bolt- NAS464P4-12

1

I

H

H

0.2492

1 -0.0000 +0.0000/

+0.0000/

-0.0005

-0.0005

+0.0015/

+0.0000/

1 -0.0000 0.7500

I 1

1 +0.0010/

I 0.9014

I

G

1

231 Bearing-BP-´•l

I 0.2500

I

I

NAS75-4-008

24

1

1

-0.0005

+0.0000/

+0.0000/

-0.0005

-0.0005

1 +0.0000/ -0.0009

Aileron

EFFECTIVITY:

AU

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 13 of 28)

51-71-04

Page SRM-4

13

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I

I DESCRIPTION

I EFF.

I HOLE I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD I

ALLOWANCE

ID

OD

WEAR I

ID

ALLOWANCE OD

Aileron Drive Clevis

25

2324512-3, -5

16

H

0.2492

1

1 +0.0010/

J

0.4991

H

0.2492

1 1

1 +0.0005/ 1 +0.0010/

J

0.4991

i

1 +0.0005/

J

0.5000

-0.0000

2324517-1,-3

17

i

-0.0000 -0.0000

1 Bearing-AN201KP8A

26 27

1

1.1250

+0.0000/

+0.0000/

-0.0005

-0.0005

Pulley Shaft 2324513-3, -13

1

I

J

1

1

0.4986

1 +0.0005/ -0.0000

K

I

1

1

0.9986

1 +0.0005/ -0.0000

Pulley-

28

2324513-9, -10 232451 3-15, -16

1

1

K

1

I

1

1 +0.0000!

I

1 -0.0009

1

1 +0.0050/

0.9985

I

Arm Link-

29

2324011-111, -223

1

H

18

H

I

1

0.2490

1

1 +0.0000/

19

H

I

1

0.2492

1

1 +0.0000/

0.2500

-0.0010

Bolt- AN4-7

30

-0.0030

NAS464P4-8

-0.0009 31

1 Bearing Rod (Alt. TR-4)

End- HFV-4

1

(Alt. REF -4T) (Alt. HFR -4M) 32

1

Pulley-MS24566-3B

1

H, H, H, H,

C C C C

L

0.2500

2.0000

+0.0000/ -0.0005

33

Bolt- AN4H1OA

1

L

34

Bracket- 2424034-1

1

L

0.2500

35

Pulley-

1

M

0.3125

I

1

0.2460

1

+0.0000/ -0.0100

1 +0.0030/ -0.0000

MS20220A1

1

I IK).0100 1.7500

+0.0005/

f0.0050

-0.0000 36

Bolt- AN5H16A

1

M

I

1

0.3090

1

1 +0.0030/ -0.0000

Aileron

I

EFFECTNTT"Y: SRM-P

ALL

System Fittings Allowable Wear and Repair Figure 1 (Sheet 14 of 28)

Data

51-n-04

Page 14 Tun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

I

ITEM NO.

371

38

I

I

MFD

MFD

HOLE

SHAFT OD

MFD ID

EFF.

HOLE

ID

2324505-29, -30, -39, -40 2324505-67,-68

20

M

0.3120

1

1 ~0.0100

M

0.3120

1

I f0.0100

5425013-4, -5

21

M

0.3120

1

1

N

0.3125

DESCRIPTION

ALLOWANCE OD

WEAR ID

ALLOWANCE OD

Bracket-

Pulley- MS20220A1

I M.0100 +0.0005/

1.7500

IH).0050

-0.0000

i

1

1

N

Bracket- 2324505-6

20

N

0.3120

1

5425014-4, -5 MS20221A1

21

N

0.3120

1

1

P

0.3125

39

Bolt- AN5-17

40

0.3090

1

1 +0.00301 -0.0000

411 Pulley-

I f0.0100 I f0.0100 +0.0000/

2.6250

f0.0050

-0.0005 42

Bolt- AN5H16A

43

Bracket- 2324505-23

1

P

20

P

I

1

0.3090

1

1 +0.0030/ -0.0000

5425010-1 44

Pulley-

MS20221A1

21

P

20

Q

+0.0000/

2.6250

0.3125

~0.0050

-0.0005 45

Bolt- AN5-12

46

Bracket-

Q

20

I

1

0.3090

1 +0.0030/

1

-0.0000

Upper LH Q

20

2315159-1,-5, -6

0.3120

1 +0.0060/

1

-0.0010

Lower LH 20

2315159-2, -3

1

Q

0.3120

R

0.3125

1

1 +0.0060/ -0.0010

47

Pulley- MS20221-1 (Alt. MS20221A1)

20

j

I

48

Bolt- AN5-12

20

R

49

Bracket- 2315157-1, -2,

20

R

50

Bearing- AN201 KP-5-A Upper- MS27642-16

2.6250

I

I

I

1

+0.0000/

1 0.3090

lt0.0050

-0.0005

1

1 +0.0030/ -0.0000

1

-3, -4

Lower- MS27648-16

511 Spacer-23151256 5415136-19

I

I

20

S

21

AM

1

0.3120

1

1 +0.0060/

I

1

1.0000

1.7500

-0.0010

+0.0000/

+0.0000/

-0.0005

-0.0010 +0.0000

AM

1.0000

1.9375

+0.0000

-0.0010

-0.0010

20

S

0.3350

0.4380

M.01 50

M.01 00

21

AM

1.000

21

1

1 +0.0100/ -0.0000

Aileron

EFFECTIVITY:

ALL

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 15 of 28) 51-n-o4

Page SRM-4

15

Jun 6/98

I

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

I

I

I

MFD

MFD

HOLE

SHAFT

MFD

ALLOWANCE

ITEM I NO.

DESCRIPTION

EFF.

HOLE

52

Bolt- AN5H22A

20

S

53

Sector- 2315125-6

22

S

0.8118

3.8800

+0.0000/

23

S

0.8118

3.8800

+0.0000/

ID

I

I

OD

1

0.3090

ID

1

OD

WEAR ID

ALLOWANCE OD

1 +0.00301 -0.0000

~0.0030

-0.0005 2315124V1-2

f0.0030

-0.0005 2315125-7

S

24

0.8118

3.8800

+0.00001

M.0030

-0.0005 5415125-3

25

AM

1.0060

3115102-1

26

AM

1.9000

1

1 +0.0000/ -0.0010

54

Bracket- 2315158-1, -5, -9

20

S

0.3120

55

Pulley- M520221A1

20

T

0.3125

1

1 +0.00601 -0.0010

2.6250

+0.00001

f0.0050

-0.0005 56

Bolt- AN5-12

20

T

57

Bracket- 2315159-1, -2, -3,

20

T

58

Pulley- MS20221-1 (Alt. MS20221A1)

I

1

0.3090

1

1 +0.0030/ -0.0000

1

-5, -6

0.3120

I 20

I

I

I

U

0.3125

I

1 +0.00601

1

I

I

I

1

59

Bolt- AN5-12

20

U

60

Bracket- 2315157-3, -4

20

U

0.3120

Pulley-MS20219A1

20

V

0.2500

-0.0010 2.6250

+0.00001

1 0.3090

~0.0050

-0.0005

1

1 +0.0030/ -0.0000

1 +0.0060/

1

-0.0010 61

1

1.3120

+0.0000/

f0.0050

-0.0005 V

62

Bolt- AN4-10, -13

20

63

Bracket- 2315128-4, -5 Pulley- MS20219A1

20

V

0.2500

20

W

0.2500

1

I

1

0.2460

1

1 +0.0030/ -0.0000

64

1

I f0.0100 1.3120

+0.0000/

f0.0050

-0.0005

651

Bolt-ANC10

20

WI

1

66

Bracket- 23151288

20

W

0.2500

1

1 ~0.0100

67

Pulley-

28

X

0.3125

1

1 +0.0000/

29

X

0.3125

i

1 +0.0000/

1

X

0.2460

1

1 +0.0030/ -0.0000

MS20220-2

-0.0005

2615177-1

-0.0005 68

Bolt- AN5-24, -25

I

1

0.3090

1

1 +0.0030/ -0.0000

Aileron

I

ALL

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 16 of 28)

51-71-04

Page SRM-4

16

Jun 6/98

Learjet ~Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

I

NO.I 691

I DESCRIPTION

71

72

I

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

X

0.3125

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Bracket-

2315120-11, -12, -33, -34, -37, -39, -40, 111 70

I

Pulley Pulley Pulley- MS20219A1

1

I 1

x

1

x

1

Y

1

1 +0.001 01

I

1

-0.0000

+0.0000/

1.3120

0.2500

f0.0050

-0.0005 73

Spacer- NAS43DD4-20

Y

1

+0.0210/

0.3750

0.2760

M.0100

-0.0200 74

Bolt- AN4-13

75

Bracket- 261 5105-7, -8,

I

1

0.2460

1

1 +0.0030/

1

Y

27

Y

0.2500

1

I M.0100

47

Y

0.2500

1

Z

0.3125

1 1

I f0.0100 I M.0005

-0.0000

-14, -15, -16, -17, -18 261 51 05L96-1, -2 76

1 Pulley-MS20220-2

Z

(Alt. MS20220A2) 77

Bolt- AN5-12

1

Z

78

Bracket- 2315120-7, -8 Yoke Assembly

3

Z

0.3125

I

1 1

0.3090

I f0.0005 1 1 +0.0030/ -0.0000

79

AA

39

2415152-1

(Alt. 2415152-3, -5)

1

0.3120

1

I

0.4393

1

1 +0.0005/

I

1

j

M.010

-0.0007

AB

0.4393

1

1 +0.0005/

AC

0.4995

1

1 +0.0010

-0.0007

-0.0000 AD AE

AF

0.5000

1

I ~t0.0100

AG

0.3773

1

I rt0.0005

AK

0.8760

1

1 +0.0015/

AL

1.1880

1

1 +0.00201

AH AJ -0.0000 -0.0000

Aileron System

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Figure 1 (Sheet 17 of 28)

Data

51-71-04

Page SRM-P

17

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I

I

i

I

MFD

MFD

HOLE

SHAFT

IIIFD

ALLOWANCE

DESCRIPTION

EFF.

HOLE

ID

I

2615270-1

40

AA

0.4393

i

1 +0.0005!

AB

0.4393

1

1 +0.00051

AC

0.4995

1

1 +0.0010

OD

I

ID

OD

WEAR ID

ALLOWANCE OD

-0.0007

-0.0007 -0.0000 AD

AE AF

0.5000

1

I f0.0100

AG

0.3773

1

I M.0005

AK

0.8760

1

1 +0.0015/

AL

1.1880

1

1 +0.0020/

AC

0.5000

AH

AJ -0.0000

-0.0000 80

1

Bearing-MS27641KP8A (Alt. AN201KP8A)

81

Pin-2315152-33

82 83

1

I

1.1250

I

I

I

1

+0.0000/

1

+0.0000/

-0.0005

-0.0005

1

AC

Bearing- MS20200KP4

33

AG

0.2500

0.9014

+0.0000/ -0.0005

-0.0005

1 Bushing-NAS75-4-015

33

AG

0.2500

0.3761

+0.0015/

+0.0005/

33

AG

1

AK

(Alt.

231

1

5152-9)

I

1

0.4986

I

1 +0.0005/

I

1

-0.0000 84

Bolt- MS20004H15

85

Bearing- MS27641 KPGA

86

(Alt. AN201 KPGA) Bearing- B-539-ZZ (Alt. B-539-DD)

87

Shaft- 2315153-28

I

1

1

0.2477

-0.0000

+0.0000/

-0.0000

1 +0.0015/ -0.0000

I

0.3750

I

I

I

AL

1

0.7500

I 30

0.8750

+0.0000/

1 1.1850

1

+0.0000/

-0.0005

-0.0005

+0.0007/

+0.0000!

I

I

AK

I

1

0.3740

1

1 +0.0003/

AL

I

1

0.7490

1

1 +0.0000/

AK

I

1

0.3740

1

1 +0.0003/

-0.0007

-0.0010 -0.0002 -0.0010

2615153-5

31

(Alt. 2315153-49)

1

1

I

I

1

AL

I I

1

0.7490

1

1 +0.0000/

AK

I

1

0.3739

1

1 +0.0003/

-0.0002

-0.0010 231 5271-1

32

-0.0002

AL

I

1

0.7485

1

1 +0.0005/ -0.0005

Aileron

EFFECTIVITY:

ALL

System Fittings Figure

Allowable Wear and 1

Repair Data

(Sheet 18 of 28)

51-71-04

Page SRM-4

18

Jun 6/98

Learjet ~earptl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

NO. 88 89

90

I

I

I

DESCRIPTION

Pulley- 2315152-21 Bushing- NAS75-5-010

I

EFF.

HOLE

1

AA

44

AA

MFD

MFD

HOLE

SHAFT

ID

OD

I

1

1.7550

MFD ID

1

-0.0005 +0.00001

45

AA

0.3125

0.4386

+0.0015/ -0.0000

-0.0005

NAS75-5-114

46

AA

0.3125

0.4386

+0.00151

+0.0000/

-0.0000

-0.0005

45

AA

0.3125

0.4386

+0.0015/

+0.0000/

-0.0000

-0.0005

46

AA

0.3125

0.4386

+0.0015/

+0.00001

43

AA

I

1

0.3120

1

1 +0.0000/

NAS464P5-15

44

AA

I

1

0.3117

1

1 +0.0000/

NAS464P5-38

45

AA

I

1

0.3117

1

1 +0.0000/

NAS464P5-41

46

AA

I

1

0.3117

1

1 +0.00001

1

AB

I

1

1.7550

1

I f0.0100

45

AB

1 Bushing-NAS75-5-016

-0.0000 Bolt- NAS1305-15D

ID

ALLOWANCE OD

+0.0000/

-0.0000 NAS75-5-1 09

NAS77-5-34 91

OD

WEAR

I M.0100 +0.00151

0.4386

0.31 25

ALLOWANCE

-0.0005 -0.0010 -0.0009 -0.0009 -0.0009

92 93

Pulley- 231 5152-21 Bushing- NAS75-5-014

-0.0005

+0.0000/

AB

0.3125

0.4386

+0.0015/ -0.0000

-0.0005

45

AB

0.3125

0.4386

+0.0015/

+0.00001

-0.0000

-0.0005

46

AB

0.3125

0.4386

+0.0015/

+0.0000/

44

AB

I

1

0.3120

1

1 +0.0000/

NAS464P5-22

45

AB

I

1

0.3117

1

1 +0.0000/

NAS464P5-23

46

AB

I

1

0.3117

1

1 +0.00001

34

J

I

1

1.9050

1

1 +0.00001

Bushing-

NAS77-5-007

NAS77-5-013

-0.0000 95

+0.0000/

-0.0000 46

NAS77-5-24 94

+0.0015/

0.4386

0.3125

Bolt- NAS1305-15D

-0.0005

-0.001 0/ -0.0009 -0.0009

96

Torque Tube

97

Block

2315151-2

-0.0020

Assy., Bearing

2315151-6

34

K

2.6250

34

K,L

2.0610

1 +0.0010/

1

-0.0000 98

Bearing- 8-545-ZZ (Alt. 85-545-DD)

I

Aileron

EFFECTIV~Y:

ALL

I

I

2.6250

I

1

+0.0005/

-0.0010

-0.0005

-0.0000

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 19 of 28) 51-71-04

Page SRM-4

19

Jun 6/98

1

Learjet i Leariet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

NO. 99

MFD

MFD

MFD HOLE

ALLOWANCE

ID

EFF.

HOLE

ID

I

35

M

1.9050

1

1 +0.00001

23151 54-1

36

M

1.9050

1

1 +0.00001

231 521 6-1

37

M

1.9050

1

1 +0.00001

38

N

2.2500

DESCRIPTION Bellcrank- 2315151-4, -7

WEAR

ALLOWANCE

I SHAFT OD

I

OD

ID

OD

-0.0020 -0.0020 -0.0020 100

Bearing-

LS4

Aileron

I

EFFECTIVITY:

ALL

0.7500

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 20 of 28) 51-71-04

Page 20 SRM-C

Tun 6/98

Learjet ~jLeariet/

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO. Inboard

1

Bearing-

BP-4

2

A

I

Replace worn part. primer or secure with Replace worn part. primer or secure with Replace worn part. primer or secure with Replace worn part. Replace worn part. Replace worn part. Replacewompart.

A A

I I

bearing

in wet

Stake

new

bearing

in wet

Loctite. Refer to 51-70-00.

Stake

new

bearing

in wet

Loctite. Refer to 51-70-00.

1

B

j

Bearing-MS27645-4

1

B

I

AN4H13A

1

B

1

C

1

E

I

Replace worn part. Stake new bearing in wet primer or secure with Loctite. Refer to 51-70-00. Replace worn part. Replace worn part. Drill holes in line in angle and plate prior to final attachment to allow installation of stud (8). Replacewompart.

1

D

I

Replacewompart.

Bearing-MS27645-4

1

D

I

Bolt- AN4HIIA

5

D

6

D

7

E

8

E

8

E

Replace worn part. Stake new bearing in wet primer or secure with Loctite. Refer to 51-70-00. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Secure with Loctite. Refer to 51-70-00. Bearing outer race must project equally

7

E

8

E

HingeBracket-

6

Bolt

7

Angle and Plate 2322530-29, -30, -31, -32 Stud- 2322530-33, -53 Hinge Bracket

Outboard

9

2322530-41, -42, -63, -64, -75, -76, -79,-80 10 11

new

Loctite. Refer to 51-70-00.

A

2322530-19, -20, -27, -28, -51, -52, -89,-90

8

Stake

A

Middle

1

Replacewornpat.

6

AN4H11A

AN4H12A

5

I

5

Bolt

1

A

3

MS27645-4

4

2

4

KSP-4

3

REPAIR

Hinge Bracket

2322530-3, -39, -40, -55, -56, -60, -67,-68,-81,-82 2

HOLE I

I

AN4H12A

Horn

12

2324011-28

2324011-235

Bearing

13

-ABT4-105

from both sides of horn. 14

1

Bolt-AN4-7 NAS464P4-8

15

1

Clevis Rod End

2433003-2

2333001-7 16

1 Bearing

Rod End

HFV-4

E

1

F F

Aileron

ALL

E

F

(Alt. TR-4) (Alt. REF-4)

EFFECTIVITY:

9 10

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part.

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 21 of 28) 51-71-04

Page 21 SRM-I

Tun 6/98

Learjet ~Learjet/

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

EFF.

DESCRIPTION

NO. Bolt

17

11

2380027-10

Actuator Arm

18

1

AN4-11

Actuator

17A

12

2333008-3

13

2333008-6 19

2324511-5

15

NAS464P3-33 NAS1 304-34H NAS1104-380

14

Bolt

20

21

14

Yoke -232451&1

1

i

Bearing-

15 15

1

MS27644-4

REPAIR

HOLE

Replace worn part. Replace worn part. F Replace worn part. F Replace worn part. G, H Replace worn part. G, H Replace worn part. G Replace worn part. G(Replacewompart. G Replace worn part. G Replace worn part. F F

1

NAS75-4-009

22

Bushing

23

NAS75-4-008 Bearing BP-4

I

G

1

H

51-70-00.

Bolt- NAS464P4-12 Aileron Drive Clevis

25

2324512-3, -5 2324517-1,3

H

16 17

H, J H, J

1

J

1

J, K

1

K

1

H H

Bearing- AN201KP8A

27 28

Pulley Shaft 2324513-3, Pulley 2324513-9, -10

29

2324513-15, -16 Arm Link 2324011-111, -223

30

Bolt

AN4-7

18

19

31

NAS464P4-8 Bearing Rod End

K

1

HFV-4

32

(Alt. TR-4) (Alt. REF-4T) (Alt. HFR-4M) Pulley MS24566-3B

33

Bolt

34

Bracket

H

H, H, H, H,

C C C C

20

L

AN4H1OA

20

L

35

Pulley

36

Bolt

2424034-1

MS20220A1

ANSH1GA

Aileron

EFFECTIVITY:

-13

I

1

26

1

ALL

Replaceworn parts. Pressfitnewbushings in primer. Replaceworn part. Securewith Loctite. Referto

wet

(Alt. MS27645-4) (Alt. KSP4) 24

Secure with Loctite. Refer to

51-70-00.

(Alt. DDP4) (Alt. BP-4) (Alt. BR4)

I

20

L

1

M

1

M

Replacewompart. Replace worn part. Replace worn part. Replace worn part. Stake new bearing in wet primer or secure with Loctite. Refer to 51-70-00. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 22 of 28) 51-71-04

Page 22 SRM-I

Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

37

EFF.

DESCRIPTION

NO.

Bracket- 2324505-29, -30, -39, -40,

REPAIR

HOLE

20

M/Replacewompart.

21

M

1

N

-67, -68 5425013-4, 6 38

Pulley MS20220A1

39

Bolt

40

Bracket

AN5-17 2324505-6

5425014-4, -5 41

1 Pulley

42

Bolt

43

-MS20221A1

ANSH1GA 2324505-23

Bracket

5425010-1

1

N

20

N

21

N

1

P

1

P

20

P

21

P

44

Pulley MS20221A1

20

45

Bolt

AN5-12

20

Q Q

46

Bracket20

Q

20

Q

Upper LH 2315159-1, -5, Lower LH

-6

2315159-2, -3

47

Pulley MS20221-1 (Alt. MS20221A1)

20

R

48

Bolt

20

R

49

Bracket

20

R

50

Bearing- AN201KP-5-A

20

S

AN512

2315157-1, -2, -3, -4

20

S

20

S

22

S

2315124V1-2

23

S

2315125-7

24

S

20

S

51

Spacer 2315125-5

52

Bolt

53

Sector

AN5H22A 2315125-6

2315158-1, -5, -9

54

Bracket

55

Pulley MS20221A1

20

T

56

Belt

20

T

57

Bracket

20

T

58

Pulley MS20221-1 (Alt. MS20221A1)

20

U

59

Bolt

AN5-12

20

60

Bracket

61

Pulley MS20219A1

62

Bolt

63

Bracket

AN5-12

2315159-1, -2, -3, -5, -6

2315157-3,

U -4

AN4-10, -13 2315128-4, -5

64

Pulley

65

Bolt

66

Bracket

MS20219A1

AN4-10

2315128-9

Aileron

EFFECTIVITY:

ALL

U

20

U

20

V

20

V

20

V

20

W

20

W

20

W

System Fittings Figure

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. primer or secure with Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Allowable Wear and 1

Repair

Stake

new

bearing in

wet

Loctite. Refer to 51-70-00.

Data

(Sheet 23 of 28)

51-71-04

Page 23 SRM-4

Jun 6/98

1

Leariet ~gLearjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO. 67

DESCRIPTION

1 Pulley

MS20220-2

2615177-1

EFF.

HOLE

28

X

29

X

68

Bolt

1

X

69

Bracket

1

X

70

1

x

1

x

1

Y

73

Pulley Pulley Pulley MS20219A1 Spacer- NAS43DD4-20

1

Y

74

Bolt

75

Bracket

71 72

AN5-24, -25 231512~11,-12, -33, -34, -37, -39, -40, -41

AN4-13

2615105-7, -8, -14, -15, -16,-17,-18 2615105L96-1,-2

76

1 Pulley

77

Bolt

78

Bracket 2315120-7, -8 Yoke Assembly 2415152-1

MS20220-2

REPAIR

Replace worn Replace worn Replace worn Replace worn

part. part. part. part.

worn

worn

part. part. part. part.

1

Y

Replace Replace Replace

27

Y

Replace

47

Y

1

Z

Replace worn part. Replace worn part.

worn

worn

(Alt. MS20220A2) AN512

1

Z

3

Z

39

AA,AB AC, AD AE, AF AG,AH AJ, AK

40

AA,AB AC,AD AE, AF AG,AH AJ, AK

1

AC

231515233

1

AC

82

(AR.23151528) 1 Bearing-MS202000KP4

33

83

1 Bushing

79

(Alt. 2415152-3, -5)

Replace worn part. Replace worn part. Replaceworn part.

AL

2615270-1

Replaceworn part.

AL 80

1 Bearing

MS27641 KPBA

AN201 KP8A 81

Pin

NAS75-4-015

1

AG

33

AG

33

AG

1

AK

1

AL

Replace worn part. Stake new bearing in wet primer or secure with Loctite. Refer to 51-70-00. Replace worn part.

Replace worn part. Stake new bearing in wet primer or secure with Loctite. Refer to 51-70-00. Replace worn part. Install bushing with wet primer on

84

Bolt

MS20004H15

85

Bearing

MS27641 KPGA

AN201 KPGA 86

1 Bearing

51-70-00.

B-539-ZZ

(Alt. B-539-DD)

EFFECTIVITY: SRM-4

ALL

Replace worn part. Secure with

Loctite. Refer to

51-70-00.

Aileron

I

exterior surface.

Replace worn part. Replace worn part. Secure with Loctite. Refer to

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 24 of 28) 51-71-04

Page 24 Jun 6/98

Learjet Lsarjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

87

Shaft- 2315153-28 2615153-5

REPAIR

EFF.

HOLE

30 31

AK,AL AK,AL

Replaceworn part. Replaceworn part.

32

AK, AL

1

AA

44

AA

Replaceworn part. Replace worn part. Replace worn part.

(Alt. 2315153-49) 2315271-1 88 89

Pulley 2315152-21 Bushing- NAS75-5-010

er on

45

NAS75-5-109

AA

Replace er on

46

NAS755-114

AA

bushing with

wet

prim-

part. Install bushing with

wet

prim-

wet

prim-

bushing with

wet

prim-

part. Install bushing with

wet

prim-

with wet

prim-

Install

exterior surface. worn

exterior surface.

Replace

worn

part. Install bushing with

exterior surface. Replace worn part. Install

er on

90

45

NAS75-5-016

Bushing

AA

er on

46

NAS77-5-34

AA

Replace er on

91

92

93

1 Bolt NAS1305-15D NAS464P5-15 NAS464P5-38

43

AA

44

AA

45

AA

NAS464P5-41

46

AA

1

AB

45

AB

Pulley 2315152-21 Bushing- NAS75-5-014

46

AB

1 Bushing-

45

NAS77-5-007

AB

45

AB

95

44

AB

NAS464P5-22

45

AB

NAS464P5-23

46

AB

34

J

Bolt

NAS1305-15D

98

Torque Tube 2315151-2 Block Assy., Bearing 2315151-6 Bearing 8-545-22

99

Bellcrank

96 97

100

34

K

34

K, L

35

M

2315154-1

36

M

2315216-1

37

M

Bearing LS4

38

N

2315151-4, -7

Aileron

EFFECTIVITY:

ALL

part. Install bushing with

wet

prim-

worn

part. Install bushing with

wet

prim-

wet

prim-

exterior surface.

Replace er on

worn

exterior surface.

Replace er on

NAS77-5-013

exterior surface.

Replace er on

94

worn

exterior surface.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install bushing er on

NAS77-5-24

exterior surface.

worn

part. Install bushing with

exterior surface.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part. part. part. part.

System Fittings Allowable Wear and Repair Data Figure 1 (Sheet 25 of 28) 51-71-04

Page 25 SRM-4

Jun 6/98

1

Learjet I

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-002 thru 23-099; 24-100 thru 24-302, 24-309 thru 24-314; 25-001 thru 25-186; 35-001 thru 35019; 36-001 thru 36-044

3

24-303 thru 24-308, 24-315 thru 24-357; 24-100 thru 24-302, 24-309 thru 24-314; 25-187 thru 25364; 28-001 and Subsequent; 29-001 and Subsequent; 31-014 and Subsequent; 35-020 thru 35-

4

504; 35-654 and Subsequent; 36-013 thru 36-053, 36-059 and Subsequent 25-365 and Subsequent; 31-001 thru 31-013; 35505 thru 35-653; 36-054 thru 36-058

5

28-001 and

6

23-001 thru 23-099; 24-100 and 001 and Subsequent

7

23-001 thru 23-034

Subsequent;

Subsequent; 31-001 and Subsequent Subsequent; 25-001 and Subsequent; 35-001

29-001 and

Except 23-011, 23-012, 23-015, 23-019,

and

Except

23-031 and

Subsequent;

36-

Aircraft Modified

by

ECR 392 8

23-011,23-012, 23-015, 23-019, 23-031,23-035 and Subsequent and Prior Aircraft Modified by ECR 392

9

23-011,23-012, 23-015, 23-019, 23-031,23-035 and Subsequent and Prior Aircraft Modified by ECR 392; 24-100 thru 24-351; 25-001 thru 25-229; 35-001 thru 35-133; 36-001 thru 36-034

10

24-352 and

Subsequent;

25-230 and

31-001 and

Subsequent;

35-134 and

11

23-001 thru 23-034

12

23-035 thru 23-049

13

23-050 and

14

23-001

Subsequent; Subsequent;

28-001 and

36-035 and

Subsequent; Subsequent

29-001 and

Except 23-039, 23-043 and Except Aircraft Modified by ECR Subsequent and Prior Aircraft Modified by ECR 392 thru 23-099; 24-100 and Subsequent; 25001 and Subsequent; 35-001

Subsequent;

392

thru 35465; 36-001

thru 36-050 15

28001 and 36-051 and

Subsequent; Subsequent

29-001 and

16

23-001 thru 23-099; 24-100 and thru 36-022

17

2&001 and

Subsequent;

Subsequent;

31-001 and

25001 and

Subsequent;

Subsequent;

35466 and

Subsequent;

35-001 thru 35092; 36-001

Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35093 and Subsequent; Subsequent 23-001 thru 23-049 Except 23-011, 23-012, 23-015, 23-019, 23-031 23-039, 23-043 and Except Aircraft Modified by ECR 392 23-011,23-012, 23-015, 23-019, 23-031,23-039, 23-043, 23-050 and Subsequent; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 31-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 thru 25-364; 2&001 and Subsequent; 29-001 36-023 and

18 19

20 21 22

24

thru 29-003; 35-001 thru 35501 25-365 thru 25373; 29-004; 35-502 thru 35-505, 35-509 thru 35-531, 35-589 thru 35692 25-374 and Subsequent; 29-005; 35-506 thru 35-508, 35-532 thru 35-588, 35-593 and Subsequent;

25

31-001 and31-034

26

31-035 and

23

36-001 and

Subsequent Subsequent

Aileron

I

EFFECTNITY:

ALL

System Fittings Allowable Wear and Repair Figure 1 (Sheet 26 of 28)

Data

51-71-04

Page 26 SRM-4

Jun 6/98

Learjet ~´•rj´•

i

STRUCTURAL REPAIR MANUAL CODES

27

EFFECTIVITIES

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 thru 35-370, 35-399 and Subsequent; 36-001

28

thru 36-040, 36-042 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and

29

28001 and

30

31

Subsequent Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly" 23-001 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 35-018 thru 35-487; 35-500, 35-502, 35-503, 35-505, 35509 thru 35567; 36-009 thru 36-060 and Prior Aircraft With 2315153-49 Shaft

Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 2&001 and Subse-

32

23-001 and

33

quent; 29-001 and Subsequent; 31-001 and Subsequent; 35488 thru 35-499, 35-501, 35-504, 35506 thru 35-508, 35568 and Subsequent; 36-061 and Subsequent 24-247 and Subsequent and Previous Aircraft Modified by AAK 76-04A, "Reduced Approach Speed

34

35 36 37

System"; 25-082 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23099; 24-100 thru 24-246 Except When Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-001 thru 25-081 Except When Modified by AAK 76-04A, "Reduced Approach Speed System" 23-001 and Subsequent 24-100 thru 24-152; 25-001 thru 25-016 23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051, 23-060, 23-06;5, 23-087, 23-096; 24-153 and

Subsequent; 25017 and Subsequent Subsequent Except 23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051,

38

23-001 and

39

23-060, 23-065, 23-087, 23-096 23-00 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-

40

24-247 and

Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent Subsequent and Previous Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 25082 thru 25360 and Previous Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 2&001 thru 28005; 29-001 thru 29-003; 35-001 thru 35-487; 36-001 thru 36-050 001 and

41

23-001 thru 23-029

42

23-030 thru 23-099

43

23-001 and

44

23-001 thru 23-099; 24-100 thru 24-246; 25-001 thru 25-081 25-082 thru 25-360; 28-001 and Subsequent; 29-001 and Subsequent; 35-001 thru 35-487; 36-001 thru 36-050

45

Subsequent

Aileron

EFFECTIVITY:

AU

System Fittings Allowable Wear and Repair Figure 1 (Sheet 27 of 28)

Data

51-71-04

Page 27 SRM-4

Jun 6/98

Leariet Learjetl

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

25-361 and

46

Subsequent; 29-004;

31-001 and

Subsequent;

35488 and

Subsequent;

36-051 and

Subsequent 35-371 thru 35-398; 36-041

47

Only

NOTES:

Refer to Rudder

System for

Refer to Elevator

System

Part Number, Allowable Wear and

for Part

Aileron

I (EFFECTIVITY:

ALL

Repair

Data.

Number, Allowable Wear and Repair Data.

System Fittings Figure

Allowable Wear and 1

(Sheet

28 of

Repair Data

28)

51-71-04

Page 28 sRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR WIANUAL TIP TANK FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

,C

D At

1

WS205.14

WS 157.48

2

,,12,.,

/i

´•S~;1 4

a

,ic

3

ii A

9’

r

C5

I

~21O

Detail A

si ‘B

Detail B 4~26C-1 4-34A

EFFECTIVITY:

Tip Tank Fittings Allowable Wear and Repair Data Figure 1 (Sheet 1 of 4) 23-001 THRU 23-099; 24-100 AND

SEQUENT; SRM-I

35-001 AND

SUBSEQUENT; 25001 AND SUBSUBSEQUENT; 36-001 AND SUBSEQUENT

51-71-05

Page

1

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL TIP TANK FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

´•´•c,

Detail C

Detail D Tip Tank Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 4) EFFECTIVITY: SRM-I

23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

51-71-05

Page 2 jun 6/98

Learjet ~Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

NO. 1 2

3 4

DESCRIPTION

Fitting- 2322372-1, -2, -7, -8

1 Bushing-NAS75-7-009 Bolt, Fwd-NAS464P7A21

1 Fitting-2322373-1,-2

MFD SHAFT OD

EFF.

HOLE

ID

1

A

0.5625

1

A

0.4375

1

A

1

B

0.5625 0.4375

5

Bushing- NAS75-7-009

1

B

6

Bolt, Aft-NAS464P7Ai4

1

B

1

C

7

MFD HOLE

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

+0.0000 -0.0010 0.5638

+0.0015/ -0.0000

+0.0000/ -0.0007

+0.0009/ -0.0000

0.4358

+0.0000/ -0.0010 0.5638

+0.0015/ -0.0000

0.4358

+0.0000/ -0.0007

+0.0009/ -0.0000

1 MountingAssembly2423160-3 thru 36

0.5631

+0.0000/

0.5631

+0.0000/ -0.0010

-0.0010 D

1

8

Bushing- NAS75-7-017

1

C

0.4375

0.5638

+0.0015/ -0.0000

+0.0000/ -0.0007

9

Bushing-

NAS75-7-017

1

D

0.4375

0.5638

+0.0015/ -0.0000

+0.0000/ -0.0007

Tip Tank Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 4) EFFECTIVITY:

23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25-001 AND SUBAND SUBSEQUENT; 36-001 AND SUBSEQUENT

SEQUENT; 35001 SRM-I

51-71-05

Page 3 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

2

Fitting 2322372-1, -2, -7, Bushing -NAS75-7-009

3

Bolt

4

Fitting 2322373-1, -2 Bushing -NAS75-7-009

1

5

EFF. -8

NAS464P7A21

NAS464P7A14

6

Bolt

7

Mounting Assembly 2423160-35, -36

HOLE

1

A

Replace

1

A

1

A

1

B

1

B

Replace worn part. primer. Replace worn part. Replace worn part. Replace worn part.

1

B

primer. Replace

1

C

1

D

8

Bushing -NAS75-7-017

1

C

9

Bushing-

NAS75-7-017

1

D

CODES 1

REPAIR

I

worn

worn

EFFECTIVITY:

Install

new

bushing

in wet

Install

new

bushing

in wet

Install

new

bushing

in wet

Install

new

bushing

in wet

part.

Replace worn part. Replace worn part. Replace worn part. primer. Replace worn part. primer.

EFFECTIVITIES 23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25-001 AND 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

Tip Tank Fittings Allowable Wear and Repair Figure 1 (Sheet 4 of 4)

I,

part.

SUBSEQUENT;

Data

23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

51-71-05

Page 4 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL LANDING GEAR FI’I~TINCS

ALLOWABLE WEAR AND REPAIR DATA

C

A,

.i-

I

"_I*rclWS 92.52 WS 0.001

(TYPICAL)

C

4

31

5

01

Main Gear Actuator

Detail A

426C-1

Detail B

Landing Gear Fittings Allowable Wear and Repair Data Figure 1(Sheet 1 of 11)

A63C-1 B43ac

EFFECTIVI~Y:

C

ALL

n-71-os

PageZ SRM-4

Jun 6/98

I

Learjet I

STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

(31-001 and Subseauent) Shim

E D

17

Shim

15

Detail C 20

qll :f

Shim

H

;-I ’I

G

E

i

QDetail D*s~

I’Q Main

Nose

Landing Gear

Landing Gear

Detail E C63B

I

EFFECTIVITY:

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 11) ALL

51-71-06

Page2 SRM-I

Jun 6/98

~j Learjet STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

23

22

J

j

Deta i I F M

N

30

’-i25

P 32

31

i

26

Detail G

31

Detail H

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 11)

EFFECTIVITY:

ALL

51-71-06

Page 3 SRM-I

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.

I DESCRIPTION

I

I

MFD

MFD

HOLE

SHAFT OD

MFD

EFF.

HOLE

ID

1

B

2.0079

2

A

1.0000

1.1000

f0.01 00

3

A

1.0000

1.1000

f0.0100

1

B

1.7550

2.0360

~0.0010

1

A

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Doubler-

1

2322203-9, -10, -13,

-14

1

1 +0.00121 -0.0000

2

Spacer-

2441001-1

2441 007-1

Bushing- 23221 87-1,

3

-2

+0.02001 -0.0000 +0.02001 -0.0000 +0.00081 -0.0000

4

1

PillarAssy. -2341123-1, -14, 1

-17, -18, -23

I

1

0.9990

1

1 +0.0000/

1 -0.0005

I

I

I

I

B

I

1

1.7450

1

1 +0.0000/

C

I

1

0.8000

1

I f0.0100

1 1

1 ~0.0100 I fO.Oi 00

I f0.0300 1 ~0.0300

-0.0100 5

1 SparNo.8 2322212-1, -2, -39, -40, -43, -44,-49,-50,-58,-59, -65, -66, -69, -70, -76, -77 122250016-273, -274

6

Bearing Plate

7

2322222-1 2441 007-2, -5, -6 Bearing Plate

8

2322221-1, -2, -3, -4, -5, -6, -7 Support- 2322204-1, -2 5420000L-1 437-1, -2

4

C

0.8750

5

C

0.8750

2

C C

1.0200 1.0200

1

6

0.6265

1

C

1

1

I

I

1

I

D

1.3130

1

8

D

1.3130

1

7

1

2822163-17

(LH Only)

9

D

1.3130

1

2822163-18

(RH Only)

10

D

1.3130

1

11

D

1.3130

1

1 +0.0015/ 1 -0.0000 1 +0.0000/ -0.0010 1 +0.0000/ -0.0010 1 +0.0000/ -0.0010 1 +0.0000/ -0.0010

122250011V1-2

(RH Only)

1 +0.0000/ -0.0010

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 4 of 11)

IEFFECTIVITY:

ALL

51-71-06

Page 4 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I

EFF. I HOLE I D

1

Bushing- 23221 97-1

9 10

I DESCRIPTION

NO.

1 Bushing-232219&1

D

1

OD

ID

OD

ID

1.1240

1.3160

+0.00201 -0.0000 +0.0020/

+0.0000/

1.128

-0.0000

-0.0020

1.3160

1.1200

I

1

2322146-3, -4, -5, -6

12

E

1.9685

1

2322146-7, -8

13

E

1.9685

1

5420000\/5-1

14

E

1.9685

1

28221 59-21, -22

15

E

1.9685

1

1

E E E

12

1 Fitting,MainGearFwd-

Pin-2341110-1,-2,-003

WEAR

ID

D

I

ALLOWANCE

MFD SHAFT

1

11

#FD

MFD HOLE

1.1245

OD

-0.0020

+0.0000/

1 +0.0000 1 -0.0020

1

ALLOWANCE

1.128

1

1.121

1 +0.0002/ -0.0008 1 +0.0002/ -0.0008 1 +0.0002/ -0.0008 1 +0.0002/ -0.0008

13

1 Bearing.-BLS-32 I

(Alt. VTB08160) (Alt. 16-577) 14

1

FwdTrunnionPin2341111-1

I

16

E

0.7500

1.2593

M.0002

+0.0002/

2341111-2

17

E

0.7500

1.2588

f0.0300

-0.0015 +0.0002/

6041113-001

5

E

0.6000

1.2588

1

1

F

0.8125

1

F

0.6090

0.81 45

1 ~0.0005 +0.0080/

-0.0015

15

1 BearingPlate

16

1 Bearing-2311580-5,

2311580-4, -9, -13, -15 -6

1

1 +0.0002/ -0.0015

-0.0010 17

1

Pin-23421081

F

I

1

0.6240

1

+0.0000/ -0.0010

1 +0.0000/ -0.0015

18

1 Bearing Plate-2311580-3,

19

1 Bearing-2311580-5, -6,

20 21

1

G G

1

G

1

H

1

-12,-14

Pin-2342108-1

1 Fitting-2411243-1,3

-11

0.8125

1

0.6090

I

0.81 45

1 0.4375

1

0.6240

I f0.0005 +0.0080/ +0.0000/ -0.0010 -0.0010 1 1 +0.0000 -0.0015 I f0.0005

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 5 of 11) ALL

51-71-06

Page 5 SRM-4

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I DESCRIPTION

22

I EFF.

I HOLE I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

Bolt- NAS464P7L53

1

H

I

1

0.4367

1

1 +0.00001

NAS464P5LA7

16

H

I

i

0.4367

1

1 +0.00001

1

H

WEAR ID

ALLOWANCE OD

-0.0009

-0.0009 23

j Spacer-NAS43DD7-25

24

Nose Gear Actuator

1

J

25

Bracket- 234211 1 -1, -3

1

K

0.4900

0.5780

+0.0000/

+0.0000/

-0.0500

-0.0300

0.4367

1

1 +0.0000/

0.5620

1

1 +0.0010/

L

0.5000

1

1 +0.0010/

K

0.4375

-0.0009

1

-0.0000 -0.0000

Bushing-

26

NAS77A7-28

1

0.5638

+0.0015/

+0.0000/

-0.0000 27

Bolt- NAS464P7L20

28

Clevis- 2317103-1

i

i

1

K

18

M

0.4380

i

1 +0.0000/

19

M

0.4390

1

1 +0.0000/ -0.0010

1

L

0.4367

-0.0007

i +0.0000/

1

-0.0009 -0.0010 Clevis- 2417012-1 29

Bolt- NAS464P833

30

Actuator Attach Pin

I

1

0.4991

1

1 +0.0000/ -0.0009

2341109-2, -4, -5

N

20

0.6872

1

1 +0.0010/ -0.0000

I

(Shank Diameter) 5441101-2

I 21

1

I N

1 0.6872

1.1220

1

1

1

+0.0000/ -0.0010

1 1

+0.0000/ -0.0010

i +0.0010/ -0.0000

31

1

(Shank Diameter) (Finish 63 RMS) ActuatorPinBushing2341112-1, -2

I I 22

1 I P

1.1250

1.1240

1.2520

1 I +0.0015/

+0.0000/

-0.0000

-0.0000 +0.0000/

-4

23

P

1.1250

1.2520

+0.0015/

2341130-3, -4

24

P

1.1250

1.2520

-0.0000 +0.0015/ -0.0000

+0.0000/ -0.0010

20

N

0.5625

0.6892

+0.0015/

+0.0000/

5441101-3,

32

I I

Bushing- 23411 09-3 5441101-3

21

N

0.5625

0.6892

-0.0010

-0.0000

-0.0010

+0.0015/ -0.0000

+0.0000/ -0.0010

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 6 of 11)

JEFFECTIVITY:

ALL

51-71-06

Page 6 SRM-I

Jun 6/98

Leariet Learjet I STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

DESCRIPTION

NO. 33

I

1

Bolt-NAS464P9-20

I

I

EFF.

HOLE

1

N

MFD

MFD

HOLE

SHAFT

ID

OD

I

i

0.5616

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00001

1

-0.0009 34

Cylinder Assy. 2341101-1,-2

25

P

1.2500

1

1 +0.0010/

2441 011-1,-2

26

P

1.2500

1

1 +0.00101

-0.0000 -0.0000

2341100-2045-1L, -1 R, -2R, -3L, -4L, -5L, -6L, -7L, -8L, -9R, -10R

27

P

1.2500

1

1 +0.00101 -0.0000

2441011-13, -14, -37, -38, -39, -40

28

P

1.2500

1

1 +0.001 01 -0.0000

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 7 of 11) EFFECTNITY:

ALL

51-71-06

Page 7 SRM-I

Jun 6/98

Learpt IL~j´•tl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

EFF.

1

Doubler

2

Spacer

3 4

Bushing 2322187-1, -2 Pillar Assy. 2341123-1, -14, -17,

5

Spar No. 8 2322212-1, -2, -39, -40,

2322203-9, -10, -13, -14 2441001-1

2441007-1

HOLE

REPAIR

i

B

2

A

3 1

A

1

A, B,C

4

C

I Replace worn part. Replace worn part. Replace worn part. Replace worn part.

B

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replacewompart.

-18, -23 -43, -44, -49, -50, -58, -59, -65, -66, -69, -70, -76, -77 12225-0016-273, -274

5

C

2

C

6

C

1

8

2441007-2,-5 Plate- 2322221-1, -2, -3, -4, -5, -6, -7 Support 2322204-1, -2

7

C D

8

D

9 10

O

9

5420000L1437-1, -2 2822163-17 (LH Onlyj 2822163-18 (RH Only) 122250011V1-2 (RH Only) Bushing 2322197-1

6

Bearing

7

1 Bearing

Plate

2322222-1

i

D D D

232219&1

1

D

2341110-1,-2, -003

1

D

12

15

E E E E

1

E

1

E

10

Bushing

11

Pin

12

Fitting, Main Gear

11

13

5420000\/5-1 13

1 Bearing

14 -22

BLS-32

(Alt. VTB08160) (Alt. 16-577) 14

1 Pin

2341111-1

2341111-2 6041113-001

1

E

16

E

17

E E

5

ream on ream on

installation. installation.

Repair or replace worn part. Repair or replace worn part. Repair or replace worn part. Repair or replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Plate-

15

Bearing

16

2311580-4, -9, -13, -15 Bearing 2311580-5, -6

17

Pin

18

Bearing Plate 2311580-3, -12, Bearing 2311580-5, -6, -11

19

part. part. part. part. part. part. part. Line part. Line part.

Fwd

2322146-3, -4, -5, -6 2322146-7, -8

2822159-21,

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

2342108-1

1

F

1

F F

1

20

Pin

21

Fitting 2411243-1,

22

Bolt NAS464P7L53 NAS464P5LA7

2324108-1

-14

1

G

1 1

G G H

1

H

16

H

1

-3

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 8 of 11)

(EFFECTIVITY:

ALL

51-71-06

Page 8 SRM-I

Jun 6/98

Leariet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM HOLE

EFF.

NO.

DESCRIPTION

23 24

Spacer NAS43DD7-25

1

H

Nose Gear Actuator Bracket 2342111-1 Bushing NAS77A-7-28 Bolt NAS464P7L20 Clevis 2317103-1 2417012-1 Bolt NAS464P&33 Actuator Attach Pin 2341109-2, -4, -5

1

J

25

26 27 28

29 30

1

5441101-2 31

1

Actuator Pin

K, L

1

I

K

1

K

18

M

19

M

1

L

20

N

21

N

22

P

23

P

REPAIR

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Replace worn part. Replace worn part.

Bushing

2341112-1, -2 5441101-3, -4 2341130-3, -4

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

24

P

20

N

21

N

1

N

25

P

2441011-1, -2

26

P

2341100-2045-1 L, -1 R, -2R, -3L, -4L, -5L, -6L, -7L, -8L, -9R, -fOR

27

P

Replace worn part. Replace worn part. Replace worn part.

2441011-13, -14, -37, -38, -39, -401

28

P

Replace worn part.

32

Bushing 23411093

33

Bolt

34

Cylinder Assy. 2341101-1,

5441101-3

NAS464P9-20 -2

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 9 of 11) EFFECT(V~DI:

ALL

51-71-06

Page9 SRM-4

Jun 6/98

1

Learpt

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-003 and

3

4

5 6

7

8 9 10 11 12

13

14

15 16

17

18 19 20

Subsequent Except Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 24-100 thru 24-229 Except Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 25-001 thru 25-069 Except Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit" 23-003 thru 23-099 When Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 24-230 and Subsequent and Prior Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 25-070 and Subsequent and Prior Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 31-001 and Subsequent 23-001 thru 23-099 When Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 24-230 and Subsequent and Previous Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 25-070 and Subsequent and Previous Aircraft Modified by AMK 71-03A, "Main Landing Gear Actuator Bearing Retainer Kit"; 2&001 and Subsequent; 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25001 and

Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 2&001 and Subsequent; 24001 and Subsequent; 31-001 thru 31-014 31-015 and Subsequent 31-015 thru 31-042; 31-058 and Subsequent 31-043thru31-057 23-001 thru 23-099 When Used With 2322146-1, -2 Fwd Main Gear Fittings; 24-100 and Subsequent When Used With 2322146-1, -2 Fwd Main Gear Fittings; 25-001 and Subsequent When Used With 2322146-1,-2 Fwd Main Gear Fittings; 35-001 thru 35-549; 36-001 thru 36-053 23-001 thru 23-099 When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 24-100 and Subsequent When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 25-001 and Subsequent When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 2&001 and Subsequent; 29-001 and Subsequent; 35650 and Subsequent; 36-054 and Subsequent 31-012 Only 31-001 and Subsequent Except 31-012 23-001 thru 23-099 When Used With 2322146-1, -2 Fwd Main Gear Fittings; 24-100 and Subsequent When Used With 2322146-1, -2 Fwd Main Gear Fittings; 25-001 and Subsequent When Used With 2322146-1,-2 Fwd Main Gear Fmings 23-001 thru 23-099 When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 24-100 and Subsequent When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 25-001 and Subsequent When Used With 2322146-4, -5 or -6 Fwd Main Gear Fittings; 2&001 and Subsequent; 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-00 thru 23-099; 24-100 thru 26357; 25011 thru 25-277; 2&001 thru 2&005; 29-001 thru 29-002; 35001 thru 35-249; 36-001 thru 36-044 24-358 and Subsequent; 25278 and Subsequent, 28006 and Subsequent; 29-003 and Subsequent; 31-001 and Subsequent; 35-250 and Subsequent; 36-045 and Subsequent 23-001 thru 23-099 Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 24-100 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 25-001 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 28-001 and Subsequent Except When Modified by SSK 973 "Re~ placement of Main Landing Gear Bushing and Pin"; 29-001 and Subsequent; 35~X)1 thru 35-611; 36001 thru 36055

Except 36-054

Landing Gear Fittings Allowable Wear and Repair Data Figure 1 (Sheet 10 of 11)

(EFFECTIVITY:

ALL

51-71-06

Page 10 SRM-4

Jun 6/98

Learjet Leariet I

STRUCTURAL REPAIR MANUAL EFFECTIVITIES

CODES

by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 25-001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 2&001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 31-001 and Subsequent; 35-612 and Subsequent; 36-054, 36-056 and Subsequent 23-001 thru 23-099 Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 24-100 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 25-001 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 2&001 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 31-001 thru 31-055; 35-001 thru 35-672; 36-001 23-001 thru 23-099 When Modified

21

24-100 and

22

thru 36-063

31-056 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 35-672 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 36-063 and Subsequent Except When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin" 23-001 thru 23-099 When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 24-100 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 25-001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 2&001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 31-001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 35001 and Subsequent When Modified by SSK 973 "Replacement of Main Landing Gear Bushing and Pin"; 36-001 and Subsequent When Modified by SSK 973 "Replacement of

23

24

Main Landing Gear Bushing and Pin" 23-001 thru 23-099; 24-100 thru 24329; 25-001 thru 25205; 35-001 thru 35-066; 36-001 thru 36-017 24-330 and Subsequent; 25206 and Subsequent; 35067 thru 35-135; 36-018 thru 36-034

25 26

35136 thru 35250; 36-035 thru 36-044 28001 and Subsequent; 29-001 and Subsequent; 31-001 and

27

28

38045 and

Subsequent;

35-251 and

Subsequent;

Subsequent

NOTES:

Install

new

bushing

with wet

primer.

Seal

edges carefully.

primer.

Seal

edge carefully.

Line

ream

bushing

to 1.1265

(+0.00051-0.0000) inch af-

ter installation.

Install

new

bushing with

wet

bearing with light coating of corrosion preventative per MIL-C-16173, Grade race is facing aft and is horizontal within ~15". assembly Install

new

1. Install

bearing

so

that

slot in outer

Align

oil hole in

Install

new

bearing outer

bushing

race

with

fitting

on

forward

edge of bearing plate. bushings to

0.437

Landing Gear Fittings Allowable Wear and Repair Figure 1(Sheet 11 of 11)

Data

with wet

primer.

Seal

edges carefully. Line

ream

(+0.001/-0.000) inch after

installation.

EFFECTIVITY:

ALL

51-71-061 Page 11

SRM-4

Jun 6/98

Learjet ~Learjet( STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

1.

General A.

B.

C.

responsibility of the aircraft owner/maintenance facility to determine qualifications of maintenance personnel performing repair procedures. As always, a clean environment and good general shop practices shall be exercised any time repairs are performed on the aircraft. Prior to, and after performing, any repairs on the Landing Gear Fittings, ensure serviceability and reliability of part. If serviceability and reliability of any part or repair remains in question or if guidance is needed in making this determination, contact Learjet Field Service for additional information. Repairs must be equal to, or greater in strength, than the original structure. Technique and material variation is permissible only so far as to facilitate fabrication and ensure the original strength and useIt is the

fulness of the affected D.

F.

G.

H.

yet been developed.

repair procedures pertaining to items not covered in this section, refer to that items respective chapter. Following any repair or maintenance procedures on the aircraft structure/components, update all aircraft log books as required. Following any repair or maintenance procedures on the aircraft structure/components, ensure inspection records pertaining to any specific repair-related procedure are identified, properly documented and closely adhered too. All parts fabricated by the repair facility shall be identified for future reference. Marking of parts shall be accomplished in a manner which does not affect the serviceability and reliability of the part. For

Limitationsand A.

component.

for structure not included in this section does not necessarily indicate that the structure involved is non-repairable, but that the application of a typical repair procedure to theoretical damage

Repairs has not

E.

2.

REPAIR

I

Inspections

Limitations

(1) Learjet engineering approved repairs to landing gear fittings are limited to those items/areas as outlined in step 4., REPAIR PROCEDURES. (2) Limitations applied to repairs in this section must be followed unless Leajet engineering authori-

ty

to the

(3) Fittings

contrary is given. or

forgings

must be

replaced if cracked or if fitting hole (non-bushed) tolerance exceeds fitting or forging are not allowed. Fittings or forgings with

the allowable limits. Cracks in any bushing shall be repaired. B.

Inspections (1) Following

Forward Trunnion Mount

Fitting Repair (PINs

2322146-1 thru -8, 2822259-21 b -22, and

5420000V5-1~ -2): (a) Forward trunnion mount fitting retainer for

security

of retainer

(b) Forward trunnion

landing 3.

must be

mount

gear is removed

inspected

every 600 hours

and for cracks in the

fitting. fitting retainer (PIN 12224-005-3) must be removed each and fitting must be inspected for any structural damage.

screws

time main

I

Materials andProcesses A.

Materials

(1) Repair materials and required

treatments

processes will be listed in the repair procedure. Maonly so far as to facilitate fabrication and ensure the

or

or permissible original strength and usefulness of the affected component.

treatment variation is

terial B.

Frocesses

(1) Refer

to the

appropriate sections,

in this

chapter,

for chemical process and treatment

speci~ica-

tions.

EFFECTIVITY:

NOTED

51-71-06

Page 201 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

REPAIR

Repair Procedures

4.

All dimensions

NOTE: A.

are

in inches unless otherwise

Forward Trunnion Mount

and -2) (See NOTE:

Fitting Repair (PINs

specified.

2322146-1 thru -8, 2822159-21 and -22, and 5420000V5-1

Figure 201.)

Repair procedures

for both LH and RH forward trunnion mount

thru -8, 2822159-21 and -22, and 5420000V5-1 and -2,

are

fittings,

PIN 2322146-1

identical unless otherwise

specified.

(1) Tools and Equipment NOTE:

Equivalent substitutes may be used in lieu of the following: PART NUMBER

NAME

Countersink (1000)

MANUFACTURER

USE

Commercially available

Countersink retainer.

Drill

#19

Commercially available

Drill retainer.

Drill

#29

Commercially available

Drill tnmnion mount

fitting. 8-32 UNC-3A

Tap

Commercially available

Tap retainer screw holes in trunnion mount

fitting.

(2) Parts and Materials NOTE:

Equivalent substitutes may be used in lieu of the following: PART NUMBER

MANUFACTURER

Retainer (1 ea.)

12224-005-3

Fabricate

Screw (6 ea.)

MS24694-S5

Commercially available

NAME

USE

Repair fitting.

locally

Secure retainer to

fitting. 222

Loctite

(Refer

Trunnion Mount

Loctite Corp. Newington, CT to the

Screw lock. 06111

applicable Leajet IPC.)

Bearing

12224005

EFFECTNITY:

NOTED

51-71-06

Page 202 SRM-4

Jun 6/98

LBarjet Learjet

STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

REPAIR

(3) Repair Procedure: (See Figure 201.) (a) Remove main landing gear strut assembly from aircraft. (Refer to the applicable Learjet Maintenance Manual.) (b) Remove internal retainer ring and forward trunnion mount bearing. (c) Clean and rework surrounding area where material has been broken (or cracked) at snap ring flange to remove all damaged flange material. (See Details A and B.) Ensure maximum allowhas not been exceeded. able dimension of 2.125 inch, as shown in Detail A, flag (d) Inspect area with dye penetrant and/or Eddy current method for possible crack extension. (Contact Learjet Field Service if more cracks are found.)

(e) Fabricate 12224-005-3 retainer per Detail C. Do

not drill

screw

hole locations in retainer at this

time. MATERIAL NOTE:

(Preferred)

Fabricate 12224-005-3 retainer out of #300 Series A151 Stain-

less Steel, 1/2 hard

or

harder.

(Alternate) 4130 Steel, heat

paint (f)

(g) (h) (i)

(j) (k) (I)

after

treat 140-160

KSI, cadmium plate and epoxy

machining.

Providing maximum edge distance obtainable, locate and mark six (6) hole locations on forward fitting. Check hole locations for a minimum edge distance of 0.20 inch on fitting. Transfer hole locations to -3 retainer and drill retainer to match fitting. (See Detail C.) Using a drill stop on drill, drill six (6) holes in fitting not less than 0.450 inch and not more than 0.050 inch deep. Tap screw holes in fitting using 8-32 UNC-3A tap. Chemically treat reworked area for corrosion and touch-up prime exterior surface of fitting. Identify -3 retainer for future reference. Using a new trunnion mount bearing, install bearing with a light coating of corrosion preservative per MIL-C-16173 Grade 1. Install bearing so assembly slot in outer race is facing aft and is horizontal within +15".

(m) Install -3 retainer. Add Loctite 222, or equivalent, to retainer screw threads. (n) Install main landing gear strut assembly. (Refer to the applicable Learjet Maintenance

).la-unaM

(O) Update all aircraft log books. (4) Limitations and Inspections Requirements: (a) Forward trunnion mount fitting retainer (PIN 12224-005-3)

must be

inspected

every 600 hours

fitting. fitting retainer (PIN 12224-005-3) must be removed each time main landing gear is removed and fitting must be inspected for any structural damage. for

security

of retainer

(b) Forward trunnion

EFFECTNITY:

NOTED

screws

and for cracks in the

mount

51-71-06

Page 203 SRM-4

Jun 6/98

~j Learjet STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

REPAIR

&32 UNC-3A

Trunnion

(Ref)

Fitting Web #5

(ReD -----;f-

&32 UNC3A Thread

UP

iI

i

c

FWD

Web #5

(6 Places)

(ReO

INBD ~Trunnion

INBD

C

(Section

I

C)

Fitting

(-3 RETAINER NOT SHOWN FOR CLARITY)

Detail A damaged portion ring location.

Remove this

edge

of lock

around

(-3 RETAINER NOT SHOWN FOR CLARITY)

I~

Check hole location for minimum distance of 0.20 inch

on

edge trunnion fitting.

Detail B

2.125 maximum allowable dimension af-

information is

ter

Maximum hole

Add Loctite 222,

applied.

depth

not to exceed 0.500

inch, minimum depth

not less than 0.450

equivalent, to

on screw

51-70-00.)

This dimension may change after preliminary location of six (6) holes in trunnion

inch. Locate to match -3 retainer.

0.23

or

only (6 places). (Refer

fitting. No. #19 (0.166) Dia. Hole (thru 3) CSK 1000

x

0.310/0.320

Dia.0.212

(6 Places) (this side)

~n r

12224-0053 Retainer

30"(Typ)

2110 (f 0.005)

1QI ~e 0.112

1.60 Dia. 3.00 Dia.

Detail C Forward Trunnion Mount

Figure

EFFECTIVITY:

NOTED

Fitting Repair

201 (Sheet 1 of 2)

51-71-06

Page 204 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL LANDING GEAR FITTINGS

REPAIR Tnu~nion

i_L""Web I

FWD

-t,

MS 24694-55

Rtting

#5 (Ret)

ScrewI~

(ReO INBD 12224-005-3 Retainer

(Section A A) -r

Trunnion

ij

III I /r I i rli I I Detail B

I

´•r

j

-C-

II

R

--;-1222P005-3 Retainer

I’

1

II I

-’1

Rtting

I

I I

’---111I

-i,-I-

-i--i~l

´•i~2-

Web #5 (ReD

1

VP

t,l,

MS 24694-55 Screw

(6 Places)

(VIEW LOOKING FORWARD AT SPAR #5) (BEARING NOT SHOWN FOR CLARITY)

Detail D Fitting Repair Figure 201 (Sheet 2 of 2)

Forward Trunnion Mount

EFFECTIVITY:

NOTED

51-71-06

Page 205 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

r-’---I

:i i....i A

I

‘B 8.

F

O -9

1 k

3

j

G lo

2\

DH11 I

5 A

Detail A

J/

\13

K/ 15~

Detail B A75C-1 87-6A

EFFECTIVITY: SRM-I

Engine Mount Fittings Allowable Wear and Repair Data Figure 1 (Sheet 1 of 4) 23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25-001 AND SUBSEQUENT; 28-001 AND SUBSEQUENT; 29-001 AND SUBSEQUENT

51-71-07

Page 1 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

NO.

DESCRIPTION

1

Engine Mount,

I

I

EFF. I HOLE I

MFD

MFD

HOLE

SHAFT

ID

I

0.0000

1

OD

MFD I

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Fwd

LM30&19

A

1

1 +0.0000/ -0.0000

2

1

Bolt-Fwd NAS464-6A37

2

A

I

1

0.3734

1

1 +0.0000/

3

A

I

1

0.3742

1

1 +0.0000/ -0.0009

-0.0005

NAS464P6A39

Fitting Engine Support

3

2351 005-1, -2

4

2351005-3, -4

5

1

B

0.3750

1

1 +0.00201

B

0.3750

1

-0.0000 1 +0.0020/ -0.0000

EngineMount-LowerAft

4

LM30&33

C

1

0.0000

1

1 +0.0000/ -0.0000

Lower Aft NAS464P8A64

Bolt

5

C,D I

1

1

0.4991

1 +0.0000/

1

-0.0009

Mount

6

Assy Engine Shock O

1

2451 004-1

0.5000

1

1 +0.0015/

0.7490

1

1 +0.0000/

-0.0000 E

1

-0.0005 7

1 YokeAssembly-Engine F

1

2351 03&40

1

0.3747

1

1 +0.0015/ -0.0000

Bolt

8

Upper Aft F,G I

1

NAS464P6L20

1

0.3742

1

1 +0.00001 -0.0009

Spacer Upper Aft NAS43HT6-16

9

F, G

1

0.4020

0.5000

+0.0250/ -0.0250

Rod End Engine Mounting REM-GTH

10

G, H

1

0.0000

0.0000

+0.0000/ -0.0000

11

I Mount-Top

+0.0015/ -0.0015 +0.0000/ -0.0000

Half H

1

LM30821

0.0000

1 +0.0000/

1

-0.0000

121

13

Sleeve-Mount LM30&23

H, 1

1

Pad Engine Mount, 2351 031-3

0.0000

0.0000

+0.0000/ -0.0000

+0.0000/ -0.0000

Upper 1

I

I

1

1.4000

1

1 +0.0000/ -0.0000

Engine Mount Fittings Allowable Wear and Repair Figure 1 (Sheet 2 of 4) EFFECTIVITY: SRM-4

Data

23-001 THRU 23-099; 24-100 AND SUBSEQUENT; 25-001 AND SUBSEQUENT; 28-001 AND SUBSEQUENT; 29-001 AND SUBSEQUENT

51-71-07

Page 2 jun 6/98

Learjet Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I 14

15

1

I

I

Mount- Bottom Half LM30&22

1

Bolt-2351032-6

1

MFD

MFD

HOLE

SHAFT

ID

OD

HOLE I

EFF.

DESCRIPTION

I

K

I

I

0.0000

I

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00001 -0.0000

1

1

MFD

0.4991

1

1 +0.0000/ -0.0009

Engine Mount Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 o~ 4) EFFECTIVITY:

SEQUENT; SRM-4

AND SUB-

51-71-07

28-001 AND SUBSEQUENT; 29-001 AND SUBSEQUENT

Page 3

23-001 THRU 23-099; 24-100 AND

SUBSEQUENT; 25-001

Tun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

EFF.

HOLE

REPAIR

Aft

1

Engine Mount,

2

LM30&19 Bolt FWD NAS464-6A37 NAS464P6A39

3

Fitting

1

A

2

A

3

A

4

B

5

B

Replace worn part. Replace worn part.

1

C

I Replaceworn part.

1

C, D

1

D

I Replaceworn part.

1

E

Replace worn part.

1

E, F

Replace worn part.

1 1

E, F F, G

Replace worn part. Replace worn part.

1

G

Replace worn part. Replace worn part. Replace worn part.

Engine Support

25510005-1, -2 23510005-3, -4 Mount Lower Aft LM308-33 Bolt Lower Aft NAS464P8A64 Mounting Assy Engine Shock 2451004-1 Yoke Assy Engine 235103&40 Bolt Upper Aft NAS464P6L201 Spacer Upper Aft NAS43HT6-16 Rod End Engine Mounting Mount- Top Half LM30&21 1 Sleeve- Mount LM30&23 1 Pad Engine Mount, Upper 23510313 1 Mount- Bottom Half LM30&22 1 Bolt 2351032-6

Engine

4

5 6 7

8 9 10 11 12

13 14 15

CODES

1

1 1

worn

part.

I Replaceworn part. H

Replace worn part.

H

I Replaceworn part.

J I

Replace worn part. I Replaceworn part.

EFFECTIVITIES 23-001 thru 23-099; 24-100 and 29-001 and Subsequent

2

23-001 thru 23-069

3

23-070 thru 23-099; 24-100 and 001 and Subsequent 23-001 thru 23049

5

I

1

1

4

G,

1

Replace

Subsequent;

23-050 thru 23-099; 24-100 and

29-001 and

Subsequent; 25-001 and Subsequent; 2&001 and Subsequent;

Subsequent;

25-001 and

Subsequent;

25-001 and

2&001 and

Subsequent;

Subsequent; 29-

2&001 and

Subsequent;

Subsequent

Engine Mount Fittings Allowable Wear and Repair Data Figure 1 (Sheet 4 of 4) EFFECTIVITY:

23-001 THRU 23-099; 24-100 AND

SEQUENT; SRM-I

28-001 AND

SUBSEQUENT; 25-001 AND SUB SUBSEQUENT; 29-001 AND SUBSEQUENT

51-71-07

Page 4 Jun 6/98

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

A~

ALLOWABLE WEAR AND REPAIR DATA

’B

~dls

?Ir

i,

M

~i;p H

i!

K

U

~o

N

lo d

20

20

d,

I

A

9

4

s’ti 20

’3

i:

L 19

Detail A

3

-i-:

B

I;

a

d

D E

Detail B

A7-29C-1 A7-29C-2 B7-29C-1 14-115C

EFFECTIVITY:

Engine Mount Fittings Allowable Wear and Repair Figure 2 (Sheet 1 of 8) 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

SRM-I

Data

51-71-07

Page 5 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

NO. 1

I

I DESCRIPTION

I

IEFF.

I HOLE

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Engine Mount, Aft 26510216

4

A

1

0.4997

1

1 +0.00101

0.3117

1

1 +0.00101

0.4997

i

1 +0.00101

B

0.3117

i

1 +0.00101

A

0.4997

B

0.3117

1

1 +0.00101

A

0.4997

i

1 +0.00101

B

0.3117

i

1 +0.0010/

0.4997

1

1 +0.001 01

0.3117

1

0.4997

1

1 +0.001 01 -0.0000 1 +0.0010/

B

0.3117

1

A

0.4997

1

1 +0.00101 -0.0000 1 +0.0010/

0.3117

1

1 +0.0010/

A

0.4997

1

1 +0.00101

B

0.3117

1

A

0.4997

1

1 +0.001 0/ -0.0000 1 +0.001 0/

0.3117

1

1 +0.0010/

0.4997

i

0.3117

1

1 +0.00101 -0.0000 1 +0.001 0/

-0.0000 B

-0.0000

2651031-3, -4

5

A

1

-0.0000 -0.0000

(Alt. 2651031-5, -6)

1 +0.00101 -0.0000 -0.0000

2651031-5, -6

6

-0.0000 -0.0000

(Alt. 2651031-7, -8)

A

1

-0.0000 B

2651 031-7, -8

7

A

1

-0.0000

(Alt. 2651031-11, -12)

-0.0000 B

1

-0.0000

2651 031-11, -12

8

-0.0000

(Alt.

2651 031-13,

-14)

-0.0000 B

1

-0.0000

2651031-13, -14

9

A

B

1

-0.0000

Engine Mount Fittings Allowable Wear and Repair Data Figure 2 (Sheet 2 of 8) EFFECTIVITY:

31-001 AND

SUBSEQUENT; 35-001 AND SUBSEQUENT;

36-001 AND SUBSEQUENT SRM-I

51-71-07

Page 6 Jun6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I

I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

DESCRIPTION

IEFF.

HOLE

2

Bolt-2651027-1

1

A

I

1

0.4995

1

i +0.0000/

3

Bolt- NAS335CP23

1

B

I

1

0.3117

1

1 +0.00001

Isolator,Aft- LM833-SA4

1

C

NO.I

WEAR ID

ALLOWANCE OD

-0.0010 -0.0009 4

1

0.3130

1

1 +0.00001

0.3125

1

1 +0.00001

-0.0005 D

1

-0.0005 Mount

E

Flange

5

Engine

6

Bolt- 2652002-2

10

1

E

I

1

0.3115

1

Bolt- 2652002-3

11

I

E

I

1

0.3115

1

12

1

F

0.5000

1

F

0.5000

1

F

0.5000

1

F

0.5000

1

F

0.5000

1

F

0.5000

1

F

0.5000

1

F

1 0.5000 1

G

0.1895

1 +0.0000/ -0.0005 1 +0.0000/ -0.0005

Fitting, Aft Eng. Support

7

2612056-5, -6

(Alt. 2612056-7, -8) 2612056-7, -8

13

(Alt. 2612056-9, -10) 14

2612056-9, -10

1 +0.0010/ -0.0000 1 +0.00101 -0.0000 i +0.00101 -0.0000 1 +0.00101 -0.0000 1 +0.0010/ -0.0000

(Alt. 2612056-13, -14) 261 2056-13, -14

15

1

2612056-1 7,-18

Support Beam Assy.

8

Aft

9

Bolt, Aft Side

1

11 12

1

1

1

1

HLI&6-5 10

16

1

G

I I

i i

0.1895

I

Bolt,TopAft-HL1S-Gd

1

G

I

1

0.1895

Bolt,TopFwd-HL1&6-4

1

G

I

1

0.1895

Bolt, FwdSide-HL1&66

1

G

I

1

0.1895

1 +0.0010/ -0.0000 1 +0.00101 -0.0000 +0.0010/ -0.0000 i +0.0010/ -0.0000 1 1 +0.0000/ I 1 -0.0010 1 1 +0.0000/ -0.0010 i 1 +0.0000/ -0.0010 1

Engine Mount Fittings Allowable Wear and Repair Figure 2 (Sheet 3 of 8) EFFECTIVITY:

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

SRM-4

1 +0.0000/ -0.0010

Data

51-71-07

Page

7

Jun 6/98

E~ Learjet Ledlietl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

Bolt,Bottom-HL1&6-4

13

I

I

EFF.

HOLE

1

G

MFD

MFD

HOLE

SHAFT

ID

OD

i

i

0.1895

MFD

ALLOWANCE

ID

1

OD

WEAR ID

ALLOWANCE OD

1 +0.0000/ -0.0010

14

Fitting, FwdEng.Support

1

261 2042-5,-6

17

1

H

0.6255

1

1 +0.0000/

J

0.3120

1

H

0.6255

1

J

0.3120

1

1 +0.0010/ -0.0000 1 +0.0000/ -0.0010 1 +0.0010/

H

0.6255

i

1 +0.0000/

J

0.3120

1

H

0.6255

1

1 +0.00101 -0.0000 1 +0.0000/

J

0.3120

1

1 +0.001 0/

H

0.6255

i

1 +0.0000/

J

0.3120

1

i +0.0010/

H

0.6255

1

1 +0.0000/

J

0.3120

1

-0.0010

261 2042-7,-8

18

-0.0000

(Alt. 2612042-9,-10)

-0.0010

261 2042-9,-10

19

-0.0010 -0.0000

(Alt. 2612042-13,-14)

-0.0010 -0.0000 20

261 2042-1 3,-14

-0.0010

15

1

Bolt-HL30-10-6

16

1

EngineMount,Fwd-

L

0.4367

1

K

0.6245

1

L

0.4367

1

1 +0.0015/

K

0.6245

1

L

0.4367

1

1 +0.0010/ -0.0000 1 +0.001 5/ -0.0000

I

22

2651 011-8

1 I

I

K

21

1

0.6245

J

1

2651011-6

1 +0.001 0/ -0.0000 1 1 +0.0005/ -0.0000 1 +0.0010/ 1 -0.0000 1 +0.0015/ -0.0000 1 +0.001 01

1

I

0.3120

-0.0000 -0.0000 23

2651011-10

Engine

EFFECTIVITY:

Mount

Fittings Allowable Wear and Repair Figure 2 (Sheet 4 of 8)

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

SRM-I

Data

51-71-07

Page 8 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I DESCRIPTION

2651 011-12

I

I

MFD

MFD

HOLE

SHAFT

MFD ID

EFF.

HOLE

ID

I

24

K

0.6245

1

1 +0.00101

L

0.4367

1

1 +0.00151

K

0.6245

1

1 +0.001 01

L

0.4375

1

1 +0.00151

K

0.6245

1

1 +0.001 01

L

0.4375

1

1 +0.0015/

K

0.625

1

1 +0.00101

L

0.4375

1

1 +0.00151

K

0.6245

1

L

0.4375

1

K

0.6245

1

1 +0.00101 -0.0000 1 +0.0015/ -0.0000 1 +0.001 01

L

0.4375

1

1 +0.00151

OD

I

ALLOWANCE OD

WEAR ID

ALLOWANCE OD

-0.0000 -0.0000 25

2651 011-13

-0.0000 -0.0000 26

2651011-15

-0.0000 -0.0000 27

2651011-18

-0.0000 -0.0000 28

2651 034-1

29

2651 0343

-0.0000 -0.0000 17

30

K

I

1

0.6240

1

i +0.00001

2651 026-3

31

K

I

1

0.6240

1

1 +0.00001

2651 026-4

32

K

i

1

0.6240

1

1 +0.0000/

1

L,M

1

0.4370

1

1 +0.0000/

1

M

0.4375

N

0.3935

Bolt-2651026-1

-0.0010 -0.0010 -0.0010

NAS1307-3H

18

Bolt

19

MountAssy.

20

Bolt

LM-833-SA5

1

80917-6-10

N

I

1 1 1

0.3882

-0.0010 I f0.0010 1 +0.0000/ -0.0005 1 1 +0.0000/ -0.0002

Engine Mount Fittings Allowable Wear and Repair Figure 2 (Sheet 5 of 8) EFFECTIVITY:

31-001 AND

SUBSEQUENT; 35-001

36-001 AND SUBSEQUENT SRM-I

AND

SUBSEQUENT;

Data

51-71-07

Page 9 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO. 1

Engine Mount,

EFF.

HOLE

4

A

Aft

2651021-5

B

2651031-3, -4

5

A

B A B

(Alt. 2651031-5, -6) 2651031-5, -6

6

A B A

(Alt. 2651031-7, -8)

B

2651031-7, -8

7

A B

A

(Alt. 2651031-11, -12)

B

2651031-11,

-12

8

A

9

A B A

B

(Alt. 2651031-13, -14) 2651031-13, -14

B 2651027-1

1

NAS335CP23

t

Isolator, Aft-LM833-SA4

1

A B C, D

3

Bolt Bolt

4

2

5

Engine Mount Flange

6

Bolt

7

2652002-2 2652002-3

Fitting,

Aft

REPAIR

1

E

10

E

11

E

12

F

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part.

Replace Replace Replace Replace Replace

part. part. part. part. part. part.

worn worn

worn worn

worn

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. (Refer to applicable basic Learjet Maintenance Manual for complete inspection requirements.)

Replace worn part. Replace worn part.

Eng. Support-

2612056-5, -6 (Alt. 2612056-7, -8) 2612056-7, -8 (Alt. 2612056-9, -10) 2612056-9, -10 (Alt. 2612056-13, -14) 2612056-13, -14 2612056-17, -18

13

F F

14

F F

15

F

16

F

G G

8

Aft

Assy.

1

9

Bolt, Aft Side HL1&6-5

1

Support

Beam

F

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Refer to Chapter 53. Replace worn part. Install oversized fastener if hole "G" is worn past tolerance. (Refer to 5170-00.)

Engine Mount Fittings Allowable Wear and Repair Data Figure 2 (Sheet 6 of 8) EFFECTIVITY:

31-001 AND SUBSEQUENT; 35001 AND SUBSEQUENT; 36-001 AND

SRM-B

SUBSEQUENT

51-71-07

Page

10

Jun 6/98

Learjet ~Lenrjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO. 10

1 Bolt, Top Aft

HL19-6-5

EFF. 1

REPAIR

HOLE

I

G

Replace

worn

hole "G" is

part. Install oversized fastener if past tolerance. (Refer to 51-

worn

70-00.) 11

I

Bolt, Top Fwd

HL186-4

1

G

I

Replace

worn

hole "G" is

part. Install oversized fastener if past tolerance. (Refer to 51-

worn

70-00.) 12

1

Bolt, FwdSide-HL1SG-6

1

G

Replace

worn

hole "G" is

part. Install oversized fastener if past tolerance. (Refer to 51-

worn

70-00.) 13

1

HL18-6-4

Bolt, Bottom

1

I

G

Replace

worn

hole "G" is

part. Install oversized fastener if past tolerance. (Refer to 51-

worn

70-00.) 14

1 Fitting,

Fwd

Eng. Support-

2612042-5, -6 2612042-7, -8 (Alt. 2612042-9, -10) 2612042-9, -10 (Alt. 2612042-13, -14) 2612042-13, -14 15

1

Bolt- HL30-10-6

17

18 19 20 1

H, H, H, H, H, H,

J J J

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install

J

J J

J

hole "J" is

worn

oversized fastener if

past tolerance. (Refer to 51-70-

00.)

Engine Mount, Fwd

16

17

1

2651011-18

25 26 27

2651034-1

28

2651034-3

29

K, L K, L K, L K,L K, L K, L K, L K, L K, L

2651011-6

21

2651011-8

22

2651011-10

23

2651011-12 2651011-13 2651011-15

24

30

K

2651026-3

31

K

2651026-4

32

K

Bolt

2651026-1

1

L

19

Bolt NAS1307-3H Mount Assy. LM-833-SA5

1

M, N

20

Bolt- 6600187-4

1

N

18

I

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replacae worn part. Replace worn part. (Refer to Chapter 71 of basic Learjet Maintenance Manual for complete inspection requirements.) Replacewornpar.

Engine Mount Fittings Allowable Wear and Repair Figure 2 (Sheet 7 of 8) EFFECTIVITY:

31-001 AND 36-001 AND

SRM-4

SUBSEQUENT; 35001 AND SUBSEQUENT; SUBSEQUENT

Data

51-71-07

Page

11

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL CODES 1 2

EFFECTIVITIES 31-001 and Deleted

Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

3

Deleted

4

35-001 thru 35-027, 35-029 thru 35-032, 35-035; 36-001 thru 36-013, 36-015, 36-016 35-028, 35-033, 35-034, 35-036 thru 35-052; 36-014 and 36-017

5

6

35-053 thru 35-499, 35-501 thru 35-503, 35-506 thru 35-508; 36-018 thru 36-053 and Prior Aircraft Equipped With 2651031-5, -6 Aft Engine Mount

7

35-500, 35-504, 35-505, 35-509 thru 35-654; 36-054 thru 36-059, 36-062, 36-063; 31-001 thru 31013; and Prior Aircraft Equipped With 2651031-7, -8 Aft Engine Mount 31-014 thru 31-048; 35-655 thru 35-674; 36-060, 36-061 and Prior Aircraft Equipped With 265103111,-12 Aft Engine Mount

8 9

31-049 and

10

35-001 thru 35-020; 36-001 thru 36-013 35-021 and Subsequent; 35-014 and Subsequent; 31-001 and

11

Subsequent; 35-675 and Subsequent; Equipped With 2651031-13, -14 Aft Engine Mount

36-064 and

13

35-001 thru 35-141; 36-001 thru 36-034 35-142 thru 35-295; 36-035 thru 36-044 and Prior Aircraft

14

35-296 thru

12

15

16

18 19

20

22

23 24 25 26 27

28 29

30 31 32

Subsequent

Equipped

Fitting

35-001,35-002;36-001 35-003 thru 35-018; 36-002 thru 36-008 35-019 thru 35-022; 36-009 thru 36-013 35-023 thru 35-026; 36-014 thru 36-016 35-027 thru 35-340; 36-017 thru 36-045 and Prior Aircraft Equipped With 2651011-13 Engine Mount 35-355 thru 35-522, 35-529, 35-530, 35-531, 35-589; 36-046 thru 36-053 35-340 thru 35-354 and Prior Aircraft Equipped With 2651011-18 Engine Mount 35-523 thru 35-654; 36-054 thru 36-059, 36-062, 36-063; 31-001 thru 31-013 31-014 and Subsequent; 35-655 and Subsequent; 36-060, 36-061, 36-064 and

Subsequent

and

Prior Aircraft Equipped With 2651034-3 Engine Mount 31-001 thru 31-007; 35-001 thru 35-642; 36-001 thru 36-057 31-008; 35-643 thru 35-647; 36-058 and Prior Aircraft Equipped With 2651026-3 Bolt 31-009 and Subsequent and Prior Aircraft Modified Per SE 31-71-1 "Powerplant Replacement of Forward Engine Mount Bolts"; 35-648 and Subsequent and Prior Aircraft Modified Per SE 35/36-71-5 "Powerplant Replacement of Forward Engine Mount Bolts" Except Aircraft 35-110; 36-059 and Sut~ sequent and Prior Aircraft Modified Per SE 35/36-71-5 "Powerplant Replacement of FoMlard Engine Mount Bolts"

31-001 AND SUBSEQUENT; 35-001 AND 36-001 AND

SRM-I

Fitting

Fitting

Engine Mount Fittings Allowable Wear and Repair Figure 2 (Sheet 8 of 8) EFFECTIVITY:

With 2612056-7, -8

35-001 thru 35-035; 36-001 thru 36-013, 36-015, 36-016 35-036 thru 35-178; 36-017 35-179 thru 35-307; 36-039 thru 36-044 and Prior Aircraft Equipped With 2612042-9, -10 Fitting 35-308 and Subsequent; 36-045 and Subsequent and Prior Aircraft Equipped With 2612042-13, -14

21

and Prior Aircraft

35-420; 36-045 thru 36-047 and Prior Aircraft Equipped With 2612056-9, -10 Fitting 35-421 thru 35-450 and Prior Aircraft Equipped With 2612056-13,-14 Fitting; 36-048 thru 36-051and Prior Aircraft Equipped With 2612056-13,-14 Fitting 35-451 and Subsequent; 36-052 and Subsequent and Prior Aircraft Equipped With 2612056-17, -18

17

Subsequent

SUBSEQUENT

SUBSEQUENT;

Data

51-71-07

Fage

12

Tun 6/98

Learjet STRUCTURAL REPAIR MANUAL ENGINE MOUNT FIT~INGS

i.

I

General A.

B.

C.

responsibility of the aircraft owner/maintenance facility to determine qualifications of maintenance personnel performing repair procedures. As always, a clean environment and good general shop practices shall be exercised any time repairs are performed on the aircraft. Prior to, and after performing, any repairs on the Engine Mount Fittings, ensure serviceability and reliability of part. If serviceability and/or reliability of any part or repair remains in question or if guidance is needed in making this determination, contact Learjet Field Service for additional information. Repairs must be equal to, or greater in strength, than the original structure. Technique and material variation is permissible only so far as to facilitate fabrication and ensure the original strength and useIt is the

fulness of the affected D.

F.

G.

H.

yet been developed.

repair procedures pertaining to items not covered in this section, refer to that items respective chapter. Following any repair or maintenance procedures on the aircraft structure/components, update all aircraft log books as required. Following any repair or maintenance procedures on the aircraft structure/components, ensure inspection records pertaining to any specific repair-related procedure are identified, properly documented and closely adhered too. All parts fabricated by the repair facility shall be identified for future reference. Marking of parts shall be accomplished in a manner which does not affect the serviceability and reliability of the part. For

Limitationsand A.

component.

for structure not included in this section does not necessarily indicate that the structure involved is non-repairable, but that the application of a typical repair procedure to theoretical damage

Repairs has not

E.

2.

REPAIR

I

Inspections

Limitations

(1) Learjet engineering approved repairs to engine mount fittings are limited to those items/areas as outlined in step 4., Repair Procedures. (2) Limitations applied to repairs in this section must be followed unless Leajet engineering authori-

ty to

the

(3) Fittings

contrary is given. or

forgings

must be

replaced if cracked or if fitting hole (non-bushed) tolerance exceeds fitting or forging are not allowed. Fittings or forgings with

the allowable limits. Cracks in any bushing shall be repaired. 3.

I

Materialsand Processes A.

Materials

(1) Repair materials and required terial

or

treatment variation is

original strength and B.

processes will be listed in the repair procedure. Maonly so far as to facilitate fabrication and ensure the

treatments or

permissible

usefulness of the affected

component.

Processes

(1) Refer

to the

appropriate sections,

in this

chapter,

for chemical process and treatment

specifica-

tions.

EFFECTIVITY:

ALL

51-71-07

Page 201 SRM-B

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

4.

REPAIR

Repair Procedures NOTE: A.

All dimensions

are

in inches unless otherwise

Forward

Engine Mount (See Figure 201.) WARNING:

specified.

and

Support Fitting (PINs

2612042-5 thru -14)

Repair

THE FOLLOWING REPAIR PROCEDURE EMPLOYS THE USE OF A DRY ICE-

ALCOHOL MIXTURE. WHEN WORKING WITH DRY ICE-ALCOHOL MIXTURE ENSURE ADEQUATE SAFETY PRECAUTIONS AND PROCEDURES ARE CLOSELY ADHERED TO. NOTE:

Repair procedures for both LH unless otherwise specified.

and RH

engine mount and support fittings are identical

Bushings may be installed only in holes ensure

that are out of tolerance. Care must be taken to that bushed hole(s) is line reamed to match other existing bolt holes.

Due to time constraints contained in the

the

procedure

be

thoroughly

following procedure, it is recommended that prior to performing the following

read and understood

task.

(1) Tools and Equipment NOTE:

Equivalent substitutes may be used

NAME

ICountersink Dry Ice

in lieu of the

following:

PART NUMBER

MANUFACTURER

9100392

Leajet Inc.

Repair engine mount

Commercially Available

Cold soak

Alcohol

USE

bushings

(2) Parts and Materials PART NUMBER

MANUFACTURER

Bushing (4 ea.)

12135-060-1

Leajet Inc.

Repair engine mount

Bushing (4 ea.)

12135-060-2

Leajet Inc.

Repair fitting

NAME

USE

12135-060

EFFECTIVITY:

NOTED

51-71-07

Page 202 SRM-I

Jun 6/98

Learjet ~jLearpt/ STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

REPAIR

(3) Tolerances TOLERANCE

NAME

Engine Mount Bolt Hole

0.6255 to 0.6245

Fitting Bolt Hole

0.6255 to 0.6245

Bolt (Ref)

0.6240 to 0.6230

(4)

Repair Procedure: (See Figure 201.) (a) Remove engine ~om aircraft. (Refer to applicable Learjet Maintenance Manual.) (b) Remove attaching parts securing engine mount to fitting. (c) Modify engine mount (PINs 2651034-1 thru -3) as follows: 1) Measure outside diameter of new bushing (PIN 12135-060-1). 2) Machine existing hole in engine mount to within 0.0002 to 0.0004 inch interference fit with outside diameter of bushing. 3) Countersink hole in engine mount using a 45" countersink to a depth of 0.060 inch by 0.870 inch diameter. (See Detail D.)

4) 5) 6)

Clean

engine mount. Inspect machined area of engine mount using Eddy current method Cold soak bushings by placing in a mixture of alcohol and dry ice

for

possible cracks.

for

a

minimum of 20

minutes.

Applyepoxy primer to four (4) holes in engine mount just prior to installing new bushings. 8) Remove bushing from alcohol and dry ice mixture and install in engine mount within 14 7)

I

seconds.

Allowenginemountto reachroom temperature. Measurediameter of upperengine mountbolt. Using dimension determined in step 9), line ream opposing bushings. Line ream inside diameter of upper bushings to provide a 0.001 inch maximum clearance for engine mount bolt. (d) Modify support fitting (PINs 2612042-5 thru -14) as follows: 1) Measure outside diameter of new bushing (PIN 12135-060-2). 2) Machine existing hole in fitting to within 0.0002 to 0.0004 inch interference fit with outside diameter of bushing. 3) Cleanfitting. 4) Inspect machined area of fitting using Eddy current method for possible cracks. 5) Cold soak bushings by placing in a mixture of alcohol and dry ice for a minimum of 20 9) 10) 11) 12)

minutes.

Applyepoxy primer to four (4) holes in engine mount just prior to installing new bushings. 7) Remove bushing h´•om alcohol and dry ice mixture and install in fitting within 14 sec-

6)

ends.

EFFECTIVITY:

NOTED

51-71-07

Page 203 SRM-I

Jun 6/98

I

Leariet

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

8) 9) 10) 11)

Allow

fitting to

reach

temperature.

Measure diameter of upper engine mount bolt. Using dimension determined in step 9), line ream Line

for

ream

engine

inside diameter of upper mount bolt.

(e) Install engine mount in (f) Align lowerboltholes.

(g)

room

REPAIR

bushings

to

opposing bushings. provide a 0.001 inch maximum clearance

fitting using only upper bolt.

Measure diameter of lower

engine mount bolt. bushings of engine mount and fitting to provide a 0.001 inch maximum clearance for engine mount bolt. (i) Install lower engine mount bolt. (j) Install engine mount in aircraft. (Refer to applicable Leajet Maintenance Manual.). (k) Update all aircraft log books to indicate that Engine SUtll70Tt Modification Installation #12135059-1 (LH)l-2 (Rli) has been incorporated. (h) Line

I

(1)

EFFECTIVITY:

ream

inside diameter of lower

Restoreaircraftto normal.

NOTED

51-71-07

Page 204 SRM-I

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

REPAIR

Fitting

Engine Mount

r

Beam

Assembly (ReD

Ball?

ii’

O

12135-060-2

s~

Bushing

12135-060-1

I

Bushing

NOTES:

Bushing

to be flush

on

this side when installed.

Permissible to radius

bushing 45" flange edge

Permissible to radius

bushing edge

to

to

prevent damage

prevent damage

on

on

assembly

Dimension of hole to be 0.0002 to 0.0004 inch interference fit (4

assembly to

to

fitting.

engine mount.

places).

(LH SHOWN, RH OPPOSITE)

Engine Mount and Fitting Repair Figure 201 (Sheet 1 of 3)

Repro

EFFECTIVITY:

NOTED

51-71-07

Page SRM-4

205

Jun 6/98

Learjet

REPA\RYANUAC STFIUCfURAC FITTINGS-REpAIR

ENGINE MO~JNT

Fitting

12135-060-2 Bushing

-i--

’Typ’ca’’

II

I,: II

1~

1\

C

i

i; t

Beam

Fitting

Assembly (ReO

(Sedion A A)

Detai\A Mount and

Fittine,- Repab 2 of 3)

En~ne 201 (Sheet Figure Repro

51-71-07 page 206

Jun 6/98

EF ECTrVITY:sRM-a

NOTED

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ENGINE MOUNT FITTINGS

REPAIR

D

EngineMount

Engine Mount

~II

12135-060-1

Bushing

(4 Required) _Irr

j

\I

t I/-

(Typical)

II

~cau E,

Ic-~a

!II

r-

II

(Section

B-

B)

(VIEW LOOKING FORWARD)

Engine Support

Detail B

Installation

I~

Engine Mount

(4Places)-\

0.870 inch Diameter

Fitting

(Countersink diameter)

(4Places) 12135-060-2

Bushing

Countersink 45"

x

0.060

W

12135-060-1

Bushing

(Section C C)

(Section

D

D)

(TYPICAL OF 4 LOCATIONS)

(TYPICAL OF 4 LOCATIONS)

DetailC

DetailD

Repro

EFFECTIVITY:

Engine Mount and Fitting Repair Figure 201 (Sheet 3 of 3) NOTED

51-71-07

Page 207 SRM-4

Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL RUDDER FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

Z

~H

’K

D

Detail A Rudder

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1(Sheet 1 of 16) 51-71-08

Pagel sRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL RUDDER FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

lafli

p;---

3

6

1 2

5

7´•\~!"

4

A’$ Detail C

Detail B

1

o

I\

9 I

.j,

11

17

12

20

19

F

\’I"

‘e

15

13/

Detail D

Detail E Rudder

)EFFECTIVITY:

ALL

E

Detail F

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 16) 51-71-08

Page 2 SRM-I

Jun 6/98

Learjet I Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

RUDDER FITTINGS

28

G

a

22

K

,,P,

24

H

23

8/

J

Detail H

Detail G

30

~JZ>

31

ii 32

VV~

30

32

D eta i I J

M 35

35

Detail K 822C-1

Rudder

A515A

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 16) 51-71-08

Page SRM-4

3

Jun 6/98

1

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL RUDDER FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

36

36

41

39

N

e~o o

0

38 37

Detail I

Detail iW

7’ a 42

4s

,49

2

44

50

as 47 48

Detail N C5-2B2

Rudder

DEFIC

F821C

I

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 4 of 16) 51-71-08

Fage4 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL RUDDER FITTINGS

ALLOWABLE WEAR AND REPAIR DATA

51

T

57 V

~Y Y~

71

57

U

7372

58

59 ss~ 6

69

AA

63

76 _~Y\\

64 78

AC’;T~ tl,

67

77

80

65

81

Detail P C52BZ

Rudder

DE5-IC

FB21C

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 5 of 16)

51-71-08) Page5

SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO. 1

Horn

2

Bearing-

I

I

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

A

0.6562

1

A

0.2500

Assy. 2333009-6

1

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00401 -0.0000

M521233-4

0.6562

+0.00001 -0.0005

3

Bolt- NAS4´•64P4-8

4

Clevis, Rod End 2433003-2

1

A

1

A

1

B

I

1

0.2492

0.2492

1

+0.00001

-0.0005 1 +0.00001 -0.0009

1 +0.00101

1

-0.0000

End

HFV-4

5

Bearing, Rod

6

Bolt- NAS464P4-13 NAS464P4-14 Actuator Arm

7

B

2

I

2333008-3, -4, -6, -7

I

I I

B

1

1 I 0.2500

0.2492

1

1 I

1 +0.00001 1 -0.0009

1 +0.00501 -0.0010

Hinge Assy.

8

1

2331030-10, -12

i

1

C

1

0.7488

i +0.00051 -0.0000

9 10

Bearing- AN201 KP4A

1

C

Bolt- AN4H11A

1

C

0.2500

I

0.7500

1

0.2490

+0.0000/

+0.00001 -0.0005

1

-0.0005

1

+0.000/ -0.0030

11

HingeAssy.

I

2331031-8, -10, -11,-14 12

Bearing-AN201KP4A

13 i

Bolt-AN4H11A

14

15

1

Bearing BlockAssy.-

1

2312040-7 Bearing- BR-4

16

I

1

D

1

D

1

1

D

I

0.7488

E 1

I

1

0.2500

0.7500

1 0.8998

I

1 +0.0005/ -0.0000 +0.00001 -0.0005

+0.00001 -0.0005 0.0000/ -0.0030

0.2490 1 +0.0008/ 1 -0.0000

1 I

E

1

(Alt DAS4-14A)

1

E

Bo~- NAS1 44A23

1

E

0.2490

I

1 +0.00001 -0.0030

17

1 TorqueTube Assy. 1

F

1

F

(AltAJ04C-125)

1

F

Fork EndTerminal-

1

2433002-1

0.3755

1

1 +0.0000/ -0.0005

18

1 Bushing- DBS-4-030

19

1

MS20667-6

I

Rudder

EFFECTIVITY:

ALL

F

I

0.3130

I

1

1 +0.0020/

I

1 -0.0000

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 6 of 16) 51-71-08

Page6 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 20

I DESCRIPTION

I HOLE

EFF.

Bolt- NAS464-4-8

I

MFD SHAFT

ID

I

I

F

I

MFD HOLE

OD

1 0.2492

MFD I

ALLOWANCE

ID

1-

OD

WEAR ID

ALLOWANCE OD

1+0.0000/ -0.0009

21

1 Pulley-

MS20220A2

G,

1

H

0.3125

3.0000

+0.0005/

+0.0050/ -0.0000

22

Bracket, Upper LH 2331 510-21,-22, -23, -24,

G

0.3120

1

I f0.0100

131G

0.3120

1

lf0.0100

0.3120

1

IM.0100

1 0.3110

1-

2

-53, -54

24

2615116-1, -5 Bracket, Lower LH 2615117-1, -5 BoR- AN25-12, -17, -22

25

Pulley- MS20220A2

26

MS20220-2 Bracket- 2512500-23

23

3

H

1

G,H

1

J,

I

1+0.00001 -0.0020

I

2615113-1

K

0.3125

I

3.0000

I

+0.0005/

I

1

25

J

0.31 20

1

1+0.00601 -0.0010

26

J

0.3120

1

1+0.0100/

25

J

0.31 20

1

1+0.0060/

26

J, K

0.3120

1

25

J

0.3120

1

26

J

0.31 20

1

+0.0050/

1-0.0000

-0.0000 27

1 Bracket-2512500-22 2615112-2

28

Bracket- 2512500-24 2615119-1

29

1 Bolt- AN2527

1

J,K

30

1 Pulley-MS20220A2

1

L

0.3125

31

1 Bracket- 2512500-5, -6, -7,

1

L

0.3120

I

-0.0010 1+0.0100/ -0.0000 1+0.0060/ -0.0010 1+0.01 00/ -0.0000

1 0.3110

1-

1+0.0000/ -0.0020

3.0000

+0.0005/

)-0.0000

MS20220-2

1

-8, -11,-12, -42, -44, -55, -56, -57, 68 32 33

34

+0.0050/

BoA- NAS464P5-44 NAS464P5-23 Pulley- MS20220A2

I L

1

I

i Bracket-2512500-27, -28

I

I I

1

I

1+0.00601 1 +0.0010

1 0.3117 I

11

1

M

0.315

4

M

0.3120

1

1+0.0080/

M

0.3120

1

1+0.0060/

3.0000

+0.0005/

1+0.0000/ 1-0.0009 +0.0050/ -0.0000

-0.0001

1

2488510-4, -5

5

2488716-4, -5

6

M

0.3120

1

1+0.0060/

2512500-6, -t 7, -18, -33, -34, -39, -40, -47

7

M

0.3120

1

1+0.0080/

1

(-0.0001

-0.0001 -0.0001

1

Rudder

EFFECT~VITY:

ALL

I

I

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 7 of 16) 51-71-08

Page7 SRM-I

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

DESCRIPTION

NO. 35 36

I

1

37

EFF.

Bolt- NAS464P5-44 NAS464P5-23 Pulley- MS20220A1

M

1

I

I

ID

OD

I

0.3117

1 I

I I

1 I

Bracket- 2312500-34, -35, 36

1

N

0.3120

1

N

Bolt-NAS464P5-22

1

N

1 Pulley-

M520220-2 MS20220A2

0.3120

I

P

1

I

I

1.7500

1 1 1

0.31 25

I

MFD

0.3117 3.0000

ALLOWANCE

ID

OD

WEAR I

ID

ALLOWANCE OD

1 +0.0000/ 1 -0.0009 +0.0005/

+0.0050

-0.0000 1 +0.0006 1 -0.0010 1 1 +0.0000/ -0.0009 +0.0050 +0.0005/

I

I

1 -0.0000

1

1 +0.0010/ -0.0000

Bracket- 2315120-11, -12,

-33, -34, -37, -39, -40, -41 Bolt- AN5-24, -25 Bellcrank- 2315129-4

1

P

1

P

8

3115042-1

1

9

0.3125

I

Bearing- 8-546-22 (Alt. &540-0[))

1.3130

R

0.3754

Q

1.3130 0.3754

1

0.7488

1

T

8

1

MS27646-40

1

Q

R 43

MFD SHAFT

0.3125

39

42

HOLE I

MFD HOLE

N

1

41

I

1

38

40

I

I

I

0.3120

T

0.7488

1

Q

0.3750

1 +0.0000/

-0.0030 I f0.0010 1 +0.0005/ -0.0000 I ~H).0010 1 +0.0005/ -0.0000 1 +0.0005/ 1 -0.0000 1 +0.0005/

1 1

1

I

9

1

1

-0.0000 44

Shaft- 2315121-29, 35

0.8470

+0.0010

+0.00001

-0.0000 45

Bolt- NAS1306-601-I

1

Q

46

Link- 2300003-1 31

1

R

47

Bolt- AN24-12

1

S R

48

Bolt- AN25-12

1

S

49

Tumbuckle EyeNAS64846LL

I

1

-0.0010

0.3745

1

1 +0.0000/

I

1 1 1

0.2480

I f0.0100 I M.0100 1 1 +0.00001

I

1

0.3110

1

-0.0010 0.2500 0.3120

-0.0020

1 +0.0000/ -0.0020

50 51

Bushing- DBS-Q-030 (Alt. -AJg4C-1 25) 1 Bearing-KS4A (Alt. -MS27645-4A)

ALL

S

1

R

1

R

1

S

1

Rudder

(EFFECTIVITY:

1

S

0.3120

0.2500 0.2500

1

1 +0.0020/ -0.0000

0.7500 0.7500

+0.0000/

+0.0000/

-0.0005

-0.0005

+0.0000/ -0.0005

+0.0000/

Fittings Allowable Wear and Repair Figure 1 (Sheet 8 of 16)

-0.0005

Data

51-71-08

Page 8 SRM-´•I

Jun 6/98

Learjet Leariet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

DESCRIPTION

NO. 52

I

1

2315121-14

Aft Rod End

I

I

MFD

MFD

HOLE

SHAFT

MFD

ALLOWANCE OD

ID

EFF.

HOLE

ID

I

OD

23

S

0.2500

1

1 +0.0010/

24

S

0.2500

1

1 +0.0010/

1

S

WEAR ID

ALLOWANCE OD

-0.0000 70031 00-901

-0.0000 Bolt- AN24-15

53

I

1

0.2480

1 +0.00001

1

-0.0020 54

1 Connecting

Rod-

2315121-21

10

1

T

0.2500

1

1 +0.001 0/

2415149-4

12

1

T

0.2500

1

3115140V1-1

13

T

0.2500

1

3115040-2

14

T

0.2500

1

1

T

15

T, U

0.6570

1

V

0.7490

1

T, U

0.6570

1

0.7490

1

-0.0000 1 +0.001 0/ -0.0000 1 +0.0010/ -0.0000 1 +0.0010/ -0.0000

55 1

Bolt- NAS464P4-9

56

Bellcrank- 2315121-1

I

1

0.2492

1

1 +0.0000/ -0.0009

16

2315138-1, -4, -6, -8

V

1

i +0.0020/ -0.0000 1 +0.0005/ -0.0000 1 +0.0020/ -0.0000 1 +0.0005/ -0.0000

57

1 Bearing-

17

LS4

1

0.2500

T,U

18

T, U

Bolt- NAS464P4-9

1

U

Rod End-2315121-14

1

U

0.2500

Bearing- AN201KP4A

1

V

0.2500

MS21 233-4

0.6562

+0.0000/

-0.0005

-0.0005 +0.0000/ -0.0005

+0.0000/

0.6562

0.2500

+0.0000/

-0.0005 58

I

1

0.2492

1 +0.0000/

1

-0.0009 59

1

1

1 +0.0010/ -0.0000

60

0.7500

+0.0000/

+0.0000/

-0.0005

-0.0005

61

Bolt- NAS1304-32H

1

V

62

Bracket- 231 5122-1, -7, -8,

1

V

I

1

0.2495

1

1 +0.0000/ -0.0010

0.1890

1

1 ~0.0100

-17, -18, -117, -118, -122, -133,-149

Rudder

EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 9 of 16) 51-71-08

Page SRM-I

9

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 63

I DESCRIPTION

I

I

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

W

0.3125

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 Bearing

Rod EndMS21 242-S05

1

1 +0.0000/ -0.0005

64

1

Pedal

Support-

2315141-17, -18, -29, -30

W

1

X

Bolt- NAS464P5-9

65

1

0.3130

1

Y

1

0.7500

0.8690

1 +0.0010/ -0.0000 +0.0000/ -0.0020

0.5000

+0.000/ -0.001

+0.0020/ -0.0000

WI

1

0.3117

1

1 +0.0000/

1

X

i

0.2470

1

1 +0.0010/

-0.0009

I

66

1 SupportStud

67

1

Bearing- AN201KP4A

1

X

68

1

Sleeve Pin-2315141-12

1

Y

69

1

Bushing- NAS77-8-25

1

Y

0.5000

0.6265

+0.0015/ -0.0000

+0.0000/ -0.0008

Bushing- NAS75-4-202

1

Y

0.2500

0.3761

+0.0015/ -0.0000

+0.0000/ -0.0005

19

Y

0.6250

1

i +0.0000/

Z

0.3750

Y

0.6250

1 1

1 +0.0030/ 1 +0.0000/

Z

0.3750

Y

0.6250

1 1

Z

0.3750

1

Y

0.6250

1

1 +0.0030/ 1 +0.0000/ -0.0020 1 +0.0030/ -0.0010 1 +0.0000/ -0.0020

Z

0.3750

1

-2315141-20

-0.0000 0.2500

0.7500

+0.0000/

+0.0000/

-0.0005

I

i

0.4980

1

-0.0005

1 +0.0000/ -0.0020

70 71

1

RudderPedal-

2315141-1,-24, -33

-0.0020 238401 0-2, -6

20

-0.0020

2415171-1, -9

2415175-1

21

22

i +0.0030/ -0.0010

Rudder

IEFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 10 o~ 16) 51-71-08

Page SRM-Q

10

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

TTEIIl NO. 72

I IEFF.

DESCRIPTION

1

Link

Assy. 2315167-22,

-29

1

I

MFD

MFD

HOLE

SHAFT OD

MFD

HOLE

ID

Z

0.6557

1

1+0.0020/

AA

0.6557

1

1+0.0020/

ALLOWANCE OD

ID

WEAR ID

ALLOWANCE OD

-0.0000 -0.0000 73

II

Bearing- AG4S (Alt. -ABG-4) (Alt. -LHA-4)

74

Bolt- NAS464P4-9

75

Arm

Assy. 2315166-10, -11, -15, -16, -18, -19

I

AA

1

AA

1 1

AA AA

1

AA

I

1 0.2492

1

1+0.0000/ -0.0009

0.2500

1

1+0.0050/

X

0.9390

1

1+0.0005/

AB

0.1890

1

1+0.0060/

10.1894

1

-0.0010 -0.0000 -0.0010 1

AB

\1

78

Lin~-23151 67-14, -27 Bushing- NAS753-011

1

AB AB

0.3120 0.1 900

79

1 NutAssy.-2315167-16

1

AC

0.3140

80

I Bushing-

1

AC

0.1900

81

1 Lever-2315167-28

1

AC

0.1910

76

Bolt- NAS464P3-9

77

1

1+0.0000/ -0.0009

NAS753-004

0.31 36

1 0.3136

1

f0.0010 +0.0015/ +0.0000/ -0.0000 1-0.0005 1 +0.0010/ -0.0000 +0.0015/ +0.0000/ -0.0000 -0.0005

1+0.00501 -0.0010

Rudder

EFFECTIV~:

ALL

Fittings Allowable Wear and Repair Data Figure 1(Sheet 11 of 16) 51-71-08

Page 11 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

HOLE

Horn Assy. 2333009-6 Bearing- MS21233-4

1

A

1

A

DESCRIPTION

NO. 1 2

3

Bolt

NAS464P4-8 2433003-2 HFV-4 Rod End Bearing,

1

A

4

Clevis, Rod End

1

A

1

B

Bolt NAS464P4-13 NAS464P4-14 Actuator Arm 2333008-3, -4 ,-6, -7

2

B

1

B

Hinge Assy. 2331030-10, Bearing AN201KPIA

1

C

1

C

5 6 7

8 9

-12

REPAIR

Replace worn part. Replace worn part. Install Loctite. (Refer to 51-70-00.) Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. or secure

Bolt

10

II

AN4H11A

2331031-8, -10,

41-,11-

Hinge Assy. 12

1 Bearing-AN201KP4A

1

C

1

D

1

D

Bolt- AN4H11A Bearing Block Assy.

1

D

14

2312040-7 Bearing- BR-4

1

E

15

13

Stake

with Lodite.

new

(Refer

I Replace

worn

stake in

place

part. Install or secure

E

1

F F

Replace worn part.

1

F

1

F

Replace worn part.

1

F

1

G, H

Replace worn part. Replace worn part.

2

G

3

G H

24

2331510-21,-22, -23, -24, -53, -54 2615116-1,6 Bracket, Lower LH 2615117-1, -5 Bolt AN25-12, -17, -22

25

Pulley MS20220A2

1

G, H J, K

26

Bracket 2512500-23 2615113-1 Bracket 2512500-22

25

J

26

J

25

J, K J, K

1

NAS144A23

16

Bolt

17

Torque Tube Assy. 2433002-1 Bushing DBS-4-030 (AltAJ04C-125)

18 19 20 21 22

23

1 Fork End Terminal MS20667-6 Bolt NAS464-4-8 Pulley MS20220A2 Bracket, Upper LH

3 1

E

in

place

51-70-00.)

new

bearing and

(Refer

to

51-70-00.) I Replaceworn part.

1

1

(Alt DAS4-14A)

bearing

to

with Loctite.

1

1

bearing with

Replace worn part. Replace worn part.

Replace worn part. Replace worn part. Install primer. Replace worn part. Install primer. Replace worn part.

E

new

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part.

Replace worn Replace worn Replace worn Replace worn

part. part. part.

new

bearing

in wet

new

bearing

in wet

MS20220-2

27

26

2615112-2

Rudder

(EFFECTIVITY:

ALL

Fittings Allowable Wear and Repair Figure 1 (Sheet 12 of 16)

part.

Data

51-71-08

Page SRM-I

12

Jun 6/98

Learjet I Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO. 28

Bracket

2512500-24

2615119-1 29

30 31

Bolt

AN25-27

Pulley MS20220A2 MS20220-2 1 Bracket 2512500-6, -7, -8, -11,-12,

REPAIR

EFF.

HOLE

25 26

K K

1

J, K

1

L

Replace worn Replace worn Replace worn Replace worn

1

L

Replace worn part.

1

L

Replace worn part.

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part.

-42, -44, -55, -56, -57, -58 32 33 34

NAS464P5-44 NAS464P5-23 Pulley MS20220A2 Bracket 2512500-27, -28 2488510-4, -5 Bolt

2488710-4, -5 2512500-6, -17, -18, -33, -34, -39, -40, -47

39 40

NAS464P5-44 NAS464P5-23 Pulley MS20220A1 Bracket 2312500-34, -35 ,-36 Bolt NAS464P5-22 Pulley MS20220-2 Bracket 2315120-11, -12, -33, -34,

41

-37, -39, -40, -41 Bolt AN5-24, -25

35 36 37 38

42

43

44

45 46 47

48 49 50 51

Bolt

Bellcrank 2315129-4 3115042-1 Bearing- 8-540-ZZ

1

M

4

M

5

M

6 7

M M

1

M

1

N

1

N

1

N P P

1 1

1

P

8

Q, R Q, R

9 8

Q

(Alt. -B540DD)

8

Q

MS27646-40

9

Q

1 1

Q Q

1

R, S

Shaft 2315121-29, -35 Bolt NAS1306-60H Link 2300003-131 Bolt AN24-12 Bolt AN2512 Turnbuckle Eye NAS64&46LL Bushing DBS-4-030 Bearing KS4A

(Alt.

MS27645-4A)

Rudder

EFFECTIVITY:

ALL

1

R

1

S

1 1

S R S

1

S

1

part. part. part. part. part.

I Replace worn part. Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install new bearing in wet primer. I Replace worn part. Install new bearing in wet primer. I Replace worn part. install new bearing in wet primer. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Press fit into wet primer. Replace worn part. Stake new bearing in place or secure with Loctite. (Refer to 51-70-00.) I Replace worn part. Stake new bearing in place or secure with Loctite. (Refer to 51-70-00.)

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 13 of 16) 51-71-08

Page 13 SRM-4

Jun 6/98

I Learjet Learjeil STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

52

DESCRIPTION

Aft Rod End

2315121-14

7003100-901

HOLE

9

S

10

S

S T T

53

Bolt

9

54

Connecting

10 12

55 56

AN24-15 Rod 2315121-21 2415149-4 3115140V1-1 3115040-2 Bolt NAS464P4-9 Bellcrank- 2315121-1

EFF.

13 14

2315138-1,-4, -6, -8 57

58 59 60 61 62

T

15

1

T, U, V T, U, V T, U T, U T, U T, U T, U T, U

i

U

1

U V

17

18 1

(Alt. LHSSVV-4) (Alt. -BLFN-4) (Alt. -BLFN-4-100) (Alt. -RSST-4)

1 1

Bolt

NAS464P4-9 Clevis, Rod End 2315121-14 Bearing- AN201KP4A

1

Bolt NAS1304-32H Bracket 2315122-1, -7, -8, -17, -18,

T

1 16

LS4 MS21233-4

1 Bearing

T

1

V

1

V

REPAIR

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. Replace worn part. Replace worn part. Replace worn part. Replaceworn part. Replaceworn part. Replace worn part. Replace worn part. Secure new bearing with Loctite. (Refer to 51-70-00.)

Replace worn part. Replace worn part. Replace worn part. primer. Replace worn part. Replace worn part.

Install

new

bearing in

wet

-117,-118,-122,-133,-149

69 70

Rod End MS21242-205 Pedal Support 2315141-17, -18, -29, -30 Bolt NAS464P5-9 Support Stud 2315141-20 Bearing AN201 KP4A Sleeve Pin 2315141-12 Bushing NAS77-8-25 Bushing- NAS75-4-202

71

Rudder Pedal

63

64 65 66 67 68

72

Bearing,

1

1

1 1 1

X Y

1

Y Y

1

2415171-1

22

73

Assy. 2315167-22, Bearing- AG´•QS

74

Bolt

EFFECTIVITY:

ALL

19 21

-29

NAS464P4-9

W X

1

20

Link

W Replace worn part. W, X, YI Replace worn part.

1

2315141-24, -33 2384010-2, -6 2415171-1,-9

Rudder

I

1

Y, Z Y, Z Y, Z Y, Z Z, AA

1

AA

1

AA

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Secure Loctite. (Refer to 51-70-00.)

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Secure Loctite. (Refer to 51-70-00.) Replace worn part.

with

new

bushing

new

bearing with

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 14 of 16) 51-71-08

Page SRM-4

14

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

75 76

EFF.

DESCRIPTION

NO.

1

Arm

Assy. 2315166-10, -11,-15, -16,-18,-19

Bolt Link

1

HOLE

AA, X,I

NAS464P3-9

1

AB

2315167-14, -27

1

AB

1

AB

80

1

AC

81

Lever

1

AC

78

CODES

2315167-28

Replace

worn

I

part.

AB

Bushing- NAS75-3-011 Nut Assy. 2315167-16 Bushing- NAS75-3-004

77

REPAIR

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Secure Loctite. (Refer to 51-70-00.) Repair worn part.

I new

bushing

with

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-001 thru 23-099; 24-100 thru 24-305, 24-309 thru 24322; 25-001 thru 25-201 001 thru 35-045; 36-001 thru 36-016

3

24-306 thru 24-308, 24-323 and Subsequent; 25-196, 25-202 and Subsequent; 35-046 and Subsequent; 36-017 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subse-

Except 25-196;

35-

quent 4

5 6 7 8

9

23-001 thru 23-099; 24-100 thru 24-270 Except Aircraft Equipped With 24-100 thru 24-270 Equipped With Drag Chute 24-271 and Subsequent and Prior Aircraft Equipped With Drag Chute

Drag

Chute

25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent; 31-001 thru 31-054 Except Aircraft Modified by SE 31-32-2, "lnstallation of Digital Nose Wheel Steering" 31-055 and Subsequent and 31-035 thru 31-054 When Modified by "lnstallation of Digital Nose Wheel

Steering" 10

11

12

23-001 thru 23-099; 24-100 thru 24-246 Except Aircraft Modified by AAK 76-04A, "Reduced Speed System"; 25-001 thru 25-081 Except Aircraft Modified by AAK 76-04A, "Reduced

Speed System" Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-082 and Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 24-247 and Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-082 and Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 thru 31-034; 35-001 and Subsequent; 36-001 and Subsequent 24-247 and

14

31-035 thru 31-051 31-052 and Subsequent

15

23-001 thru 23-037

16

23-038 and

13

29-001 and

Subsequent; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent Rudder

EFFECTIVITY:

Approach Approach

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 15 of 16)

1 51-71-08

Page SRM-4

15

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

CODES

EFFECTIVITIES

17

23-001 thru

18

Subsequent; 25-012 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-003 thru 23-099 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 24-100 thru 24-357 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 25002 thru 25-302 Except When Modified by AMK 8102, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 28001 thru 28-005 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacemenr’; 29-001 thru 29-002 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 35-001 thru 35-298 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 36-001 thru 36-044 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement" 23-001 thru 23-099 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacemenr’; 24-100 thru 24-139 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement" 23-001 thru 23-099 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacemenr’; 24-358 and Subsequent and 24-100 thru 24-139 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacemenr’ and 24-140 thru 24-357 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 25001 thru 25302 When Modified by A 2381421-1 Kit, 25303 thru 25-338 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement" and 25-340 thru 25-357 When Modified by AMK 81-03, "Rudder Pedal Heel Support Replacement"; 2&001 thru 2&005 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 29-001 thru 29-003 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 35-001 thru 35400 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement’"; 36-001 thru 36-047 When Modified by AMK 8102, "Rudder Pedal Rework and Heelplate Replacement" 23-001 thru 23-099 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 24-140 thru 24-357 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 25339 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 28-006 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 29-004 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 31-001 and Subsequent; 35-401 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 36-048 and Subse-

19

20

21

22

23-099; 24-100 thru 24-171; 25-001 thru 25-011

24-172 and

quent When Modified by 23

24

SRM-4

2384010-5 Kit

Equipped With Yaw Sensor; 29-001 and Subsequent Not Equipped With Yaw Sensor; 31-001 and Subsequent Not Equipped With Yaw Sensor; 35-001 and Subsequent Not Equipped With Yaw Sensor; 36-001 and Subsequent Not Equipped With Yaw Sensor 23-001 thru 23-099 Equipped With Yaw Sensor; 24-100 and Subsequent Equipped With Yaw Sensor; 25-001 and Subsequent Equipped With Yaw Sensor; 28001 and Subsequent Equipped With Yaw Sensor; 29-001 and Subsequent Equipped With Yaw Sensor; 31-001 and Subsequent Equipped With Yaw Sensor; 35001 and Subsequent Equipped With Yaw Sensor; 36-001 and Subsequent Equipped With Yaw Sensor Rudder

JEFFECTIVITY:

a

23-001 thru 23-099 Not Equipped With Yaw Sensor; 24-100 and Subsequent Not Equipped With Yaw Sensor; 25-001 and Subsequent Not Equipped With Yaw Sensor; 28-001 and Subsequent Not

ALL

Fittings Allowable Wear and Repair Data Fi~ure 1 (Sheet 16 of 16) 51-71-08

Page 16 Jun 6/98

Learjet I

STRUCTURAL REPAIR MANUAL HORIZONTAL STABILIZER FI’ITINGS

i:

2

ALLOWABLE WEAR AND REPAIR DATA

AB CA

__

i 3

/‘7

8 5

i´•l

j B

F

E D

Detail A Horizontal Stabilizer AB7C eec

EFFECTIVrTY:

ALL

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 1 of 5) 51-71-09

Page 1 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO. 1

I DESCRIPTION

EFF.

I HOLE

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Hinge Assy. 2332015-1, -2, -7, -8, -16, -17, -20, -21

2

I

BushingNMB (A)

1

A

1

AJF16C-1O1

2.3000

i

I

1

1 +0.11001

i

1 -0.0000

1

B

1.2510

+0.00001

1

B

1.2510

+0.0000/ -0.0005

1

C

1.3760

+0.0000/

1

C

1.3760

+0.0000/

2

C

-0.0005

(Alt. -KJB172016B) 3

BushingNMB

(A) AJF18C-102

-0.0005

(Alt. -KJB1721188)

-0.0005 4

Pin-2331028-1, -2, -3, -4, 1

-5,-6

1 I 1

1.1280

D

I I I

1.0937

1 I 1

1 +0.0000/ 1 -0.0005 1 +0.0005/

E

I

1

1.0320

1

i ~0.0100

F

I

1

1.0312

1

1 +0.0005/

B

I

1

1.0030

1

1 +0.0000/

C

I

1

1.1305

1

+0.0000/

D

I

1

1.0937

1

1 +0.0005/

E

I

1

1.0320

1

1 ~0.0100

F

I

1

1.0312

1

1 +0.0005/

B

I

1

1.0049

1

1 +0.00001

I

-0.0000

-0.0000 -0.0005 2430000-1 929-1, -2

3

1

-0.0010

-0.0000

-0.0000 -0.0005 5

Hinge Assy. 2331025-1,-2, -7, -8, (Alt.2331 025-15, -16)

G

4

1

1.1875

i

1 +0.0005/

1.2500

1

G

1.1875

1

1 +0.0005/ -0.0000 1 +0.0005/

H

1.2500

1

j

I H

2530000\/2-1,

-2

5

1

1

-0.0000

-0.0000

Horizontal Stabilizer

IEFFECTNITY:

ALL

1 +0.0005/ -0.0000

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 2 of 5)

51-71-09

Page:! SRM-I

Jun 6/98

Learjet 1

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

NO.

I

I

I EFF.

DESCRIPTION

6031025-1, -2, -5, -6, -11,-12

I HOLE G

6

1

I

MFD

MFD

HOLE

SHAFT

ALLOWANCE

ID

ID

I

1.1875

1

1 +0.00051

I

1

1

1 +0.0005/

I H

MFD

1.2500

OD

OD

WEAR ID

ALLOWANCE OD

-0.0000 -0.0000

6

Bushing,

LH4

2331 025-7

7

8

F

1.0937

1.2510

+0.0005/

+0.0005/

-0.0000

-0.0000 +0.0005/

2331025-13

5

F

1.0937

1.2510

+0.0005/ -0.0000

-0.0000

6031 025-5

6

F

1.0937

1.2510

+0.0005/

+0.0005/

-0.0000

-0.0000

Bushing,

RH-

2331 025-8

4

D

1.0312

1.1885

+0.0005/ -0.0000

+0.0005/ -0.0000

2331025-14

5

D

1.0312

1.1885

+0.0005/ -0.0000

+0.0005/

6031 025-6

6

D

1.0312

1.1885

+0.0005/ -0.0000

+0.0005/ -0.0000

7

E E

1.0600

1.2500

0.9300

1.0000

~t0.0100

rt0.0100

Sleeve- 2431111-1,-2 2431111-3

8

Horizontal Stabilizer

EFFECTIVITY:

ALL

-0.0000

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 3 of 5)

51-71-09

Page3 SRM-I

Jun 6/98

1

Leariet ~jLearjetl STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO. 1

D ESC RI PTION

EFF.

HOLE

Hinge Assy. 2332015-1, -2, -7, -8,

1

A

I Replace worn part.

1

B

I Replace worn part.

1

C

I Replace worn part.

-16, -17, -20, 2 3 4

-21

Bushing NMB (A) AJF16C-I01 (Alt. -KJB172016B) Bushing NMB (A) AJF18C-102 (Alt. -KJB1721188) 1 Pin 2331028-1, -2, -3, -4, -5, 2331028-1929-1,

5

-6

2

-2

Hinge Assy. 2331025-1, -2, -7, (Alt. 2331 025-15, -16)

3

-8

5430000\12-1,-2 6031025-1,-2, -5, -6, -11,-12 6

7

8

LH 2331025-7 2331025-13 6031025-5 Bushing, RH 2331025-8 2331025-14 6031025-6 Sleeve 2431111-1,-2 2431111-3

Bushing,

Horizontal Stabilizer

I

EFFECTIVITY:

ALL

REPAIR

4

5

6 4

B, C, D,I Replace E, F B, C, D,I Replace E, F G, H Replace

G, H G, H F

5 6

F

4

D

5

D

6

D

7

E

8

E

F

worn

part.

worn

part.

worn

part.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part. part. part. part.

Fittings Allowable Wear and Repair Figure 1 (Sheet 4 of 5)

Data

51-71-09

Page4 SRM-I

Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL CODES 1

2

3 4

EFFECTIVITIES 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent Except 24-307 and 24-323; 25-001 and Subsequent Except For 25-204; 28001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent 24-307 and 24-323; 25-204 23-001 thru 23-099 Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 24-100 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 25-001 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 28-001 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 29-001 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 31001 thru 31-042 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 35-001 thru 35-670 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 36-001 thru 36-063 and Subsequent Except When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"

5

31-043 thru 31-049

6

23-001 thru 23-099 When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 24-100 and Subsequent When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 25-001 and Subsequent When Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 28-001 and Subsequent When NModified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 29-001 and Subsequent When Modified by

7

SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 31-050 and Subsequent and Prior Aircraft Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 35-671 and Subsequent and Prior Aircraft Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly"; 36-064 and Subsequent and Prior Aircraft Modified by SSK 9101, "Replacement of Horizontal Stabilizer Hinge Assembly" 23-001 thru 23-099; 24-100 and Subsequent; 25-001 thru 25´•375; 28-001 thru 28-005; 29-001 thru

29-004; 35-001 thru 35-525; 36-001 thru 36-053 8

25-376 and

Subsequent;

31-001 and

Horizontal Stabilizer

EFFECTIVITY:

Subsequent;

35-525 and

Subsequent;

36-054 and

Subsequent

Fittings Allowable Wear and Repair Data Figure 1 (Sheet 5 of 5)

I

ALL

Page SRM-I

5

Jun 6/98

Learjet i

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

AsC

L

J

2, 2,

J

~C‘LB M

Z,N

J

E J

(Model 23 Series Aircraft Only)

K\4

J

~o E

L‘u

i~HYi

1

Q\,

C

"G

M

2, Elevator

EFFECTIVITY:

NOTED

System Allowable Wear and Repair Data Figure 1 (Sheet 1 of 29) 51-71-10

Pagel SRM-4

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR GND REPAIR DATA

A

B

/e

i-´•i~-

(Model 25. 28. 29. 31. 35 and 36 Series Aircraft)

K\J\H \M

~P

N D

P: A ,3 4

´•78

B C

Detail A 8814C-1 CB-14C

Elevator

~15C

EFFECTIVITY:

ALL OR NOTED

System Allowable Wear and Repair Figure 1 (Sheet 2 of 29)

Data

51-71-10

Page2 sRM-4

Jun 6/98

Learjet ~Learjet STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

Detail B

12

Detail C

a~

16

Detail D BB14C-1

Elevator

CB14C Dg15C

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 3 of 29) 51-71-10

Page SRM-4

3

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

ELEVATOR SYSTEM

-7

103

AM

AL

~tCU/

102

AM

O

O ii

,1K

98

--~-t

Detail E BS14C-l ael4e

os-lse

EFFECTNITY: SRM-4

Elevator

System Allowable Wear and Repair Data Figure 1 (Sheet 4 of 29)

24SERIES AIRCRAET

51-71-10

Page4 Tun 6/98

Learlet ~Learjet(

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

86

88

AG

21.

20

101

C\J

AH’ 91~

93 94 95

15

Detail E B&14C-1 CB14C DB15C

EFFECTIVITY:

Elevator

System Allowable Wear and Repair Data Figure 1 (Sheet 5 of 29)

24 SERIES AIRCRAFT AND 25 SERIES AIRCRAFT

51-71-10

Page 5 SRM-4

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

104~\ R

ALLOWABLE WEAR AND REPAIR DATA

le

20

21

107

AL 23

j AM

S 105

\106

AK

Detail E AV

p

27P 115

DetailT EFB52C-1

EFFECTIVITY:

Elevator

Detail U

System Allowable Wear and Repair Data Figure 1 (Sheet 6 of 29)

25SERIES AIRCRAFT~

51-71-10

Page6 SRM-I

Tun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

107

z 93 94

95

AR 109

114

113

AQ

111

AO 108

r~

1

33

i;o

AU

AL

BATi AS

AM

105

33

112 112´•

AH

GBI4e H882A

EFFECTIVITY:

Detail S Elevator

System Allowable Wear and Repair Data Figure 1 (Sheet 7 of 29)

25 SERIESAIRCRAET

51-71-10

Page 7 SRM-I

Jun 6/98

1

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

35

ALLOWABLE WEAR AND REPAIR DATA

N 21

j

20

K 17

36

Q~

zs 3s

~3 1 24

J

I

0~

i

28

21

M

Detail E

a

31

P

Detail F

Is81A KL&44B Mg32C Ne9e

I

EFFECTIVITY:

Elevator

System Allowable Wear and Repair Data Figure 1 (Sheet 8 of 29)

28, 29, 31, 35 AND 36 SERIES AIRCRAFT

51-71-10

Page8 SRM-I

Jun 6/98

Learjet ~Learjet STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

CZ’~;

39

kL 43

47-~

44

Detail G

50

I

49´•

V

d‘ I

JgelA

Elevator

KLg44B

Mg32C NB9C

EFFECTIVITY:

ALL

Detail H

System Allowable Wear and Repair Data Figure 1 (Sheet 9 of 29) 51-71-10

Page SRM-4

9

Jun 6/98

1

Learjet Leariet I

STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

52

,54

W

Detail J

57

´•_’r">YS

~4.

se

~ohP: ~It

I

58

Detail K

56

5P

60

Y

61

Detail I P&15C

JEFFECTIVITY:

Elevator

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 10 of 29) 51-71-10

Page SRM-I

10

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

ELEVATOR SYSTEM

.*1

62

z AA

B Pa 64

Po I/´•~\

Detail M

Detail N

AB AC

AD

AP

i $8

AE 70

7~1

15~BP Detail P

QRLF~WD

EFFECTIVITY:

Elevator

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 11 of 29) 51-71-10

Page 11 SRM-I

Jun 6/98

I Learjet Learjetl STRUCTURAL REPAIR MANUAL ELEVATOR SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

AF

AG

i1/~76

77

75 it

s’

’ ´•i

R

3 77

Detail Q

Detail R QR&43D

EFFECTIVITY:

Elevator

System Allowable Wear and Repair Data Figure 1 (Sheet 12 o~ 29)

AIRCRAFT EQUIPPED WITH ELEVATOR BOB WEIGHT

51-71-10

Page SRM-I

12

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I

Bellcrank Assy. 2331 511-15, -16, -33, -34,

1

A

1

-45, -46, -61, -62, -83, -84, 1 -1 01, -102, -801, -802

Bearing- MS27645-4A

2

I

EFF. I HOLE

DESCRIPTION

NO.

I

I

1

I

MFD

HOLE

SHAFT

ID

OD

0.7493

I

MFD ID

1

1+0.00001

1

1-0.0005

B, C

0.3140

1

1+0.0030/

D

0.7395

1

-0.0000 1+0.0005/ -0.0000

A

0.2500

0.7500

1+0.0000/ -0.0005

Pin- HL 18-8-9

2

BoB- 2331511-87

3 4

6 7

Bolt NAS464P4A-32 NAS464P4A30 SB41 OA4K28S Torque Tube 2434003-7 Bearing- BLFR-4-045 Bolt- NAS464P4-14

8

Rod End Clevis

3

1

ALLOWANCE OD

WEAR ID

ALLOWANCE I

OD

+0.0000/ -0.0005

A

I

1 0.2495

1

1+0.0000/

A

I

1 0.2495

1

1+0.0000/

-0.0010 -0.0010 4

5

1

B, B, B, B,

5 6

C C C

1

C D

1

D

1

0.3140

I

1

1 0.0030

1 0.2492

1

1+0.0000/ -0.0009

1

D

0.2492

1

1+0.001 01

8

D

0.2492

1

1+0.001 01

1

E

0.7488

1

1+0.00051

2331510-75

7

2331510-31

-0.0000 -0.0000 9

Hinge Assy. 2332918-16, 1

-20, -22

I

I

10

1 Bearing-ANPO1KP4A

1

E

11

I Bolt- AN4H11A

1

E

12

1 HingeAssy. -2332013-19,

48

F

1 0.2500

I

1-0.0000 0.7500

1 0.2490

+0.00001 -0.0005

1

+0.0000/ -0.0005

1+0.0000/ -0.0030

-22, -24 3532003-1, -2

1

I

+0.0005/

0.7488

I

1

1-0.0000

49

F

0.7488

48

F

0.2500

0.7500

49

F

0.2500

0.7500

1

F

+0.00051 -0.0000

13

1 Bearing-AN201KP4A MS27641-4

14

1 Bolt-AN4H11A

I

1 0.2490

+0.0000/ -0.0005 +0.0000/ -0.0005

1-

+0.0000/ -0.0005 +0.0000/ -0.0005

1+0.0000/ -0.0030

15

Bearing Rod

End

2331 51 0-28

1

G

0.9020

1

1+0.0020/ -0.0000

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 13 of 29) 51-71-10

Page 13 SRM-4

Jun 6/98

Leariet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO. 16

I 1 I IEFF. HOLE I

DESCRIPTION

1 Bearing- AN200KS-4 (Alt. MS276454)

17

1

G

1

G

1

Yoke-2331512-2

9

MFD

MFD

HOLE

SHAFT

ID

OD

ID

OD

0.2500

0.9014

+0.0000/ -0.0005

+0.00001 -0.0005

+0.00001

+0.0000/

-0.0005

-0.0005

0.2500

MFD

0.9014

ALLOWANCE

G

0.2492

1

1 +0.0010/

H

0.2495

1

-0.0000 1 +0.0010/

J

0.7494

1

G

0.2492

1

0.2495

1

J

0.7494

1

G

0.2492

1

1 +0.001 0/ -0.0000

H

0.2495

1

1 +0.0010/

J

0.7494

1

-0.0000 1 +0.0000/

G

0.2492

1

1 +0.0010/

H

0.2495

1

J

0.7494

1

G

0.2492

1

H

0.2495

1

J

0.7494

1

1 +0.0010/ -0.0000 1 +0.0000/ -0.0006 1 +0.0010/ -0.0000 1 +0.0010/ -0.0000 1 +0.00001 -0.0006

WEAR I

ID

ALLOWANCE OD

-0.0000

2331517-2

10

1

H

1

1 +0.0000/ -0.0006 1 +0.00101 -0.0000 1 +0.0010/ -0.0000 1 +0.00001 -0.0006

2531 533-1

11

-0.0006

2531 533-5

12

-0.0000

2631 508-2

18

13

Bolt- NAS464P4-35

1

G

Cable

1

H

I

1

0.2492

1

1 +0.0000/ -0.0009

19

1

Fitting-26315041 1

(Alt. 2631509-2)

20

1 Hinge

Bracket-2331510-17

I

1

Elevator

(EFFECTIVITY:

ALL

0.2500

I

1

I

K

0.1880

1

J

0.2500

1

1 +0.0050/ 1 -0.0000 1 +0.0050 -0.0000 -0.0000 1 +0.0020/ -0.0000

System Allowable Wear and Repair Data Figure 1 (Sheet 14 of 29) 51-n-10

Page SRM-4

14

Jun6/98

Learjet ~Leariet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

NO.I

I

DESCRIPTION

21

1

22

1 Down-spring

Bolt-NAS464P48

I

EFF.

HOLE

1

J

1

L

MFD

MFD

HOLE

SHAFT

ID

I

MFD

I

OD

I

1

0.2492

1

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00001 -0.0009

FrameBrM-

23

2531 539-1 Bolt- AN23-13

24

Down-spring

1

I L

1

0.1895

1 +0.0010/

1

I

I

I

1

1 -0.0000 0.1860

1

1 +0.0000/ -0.0020

Frame-

2631 507-1, -8, -10, -12, -16

L

13

1

I

0.5628

I

1

1 +0.0000/

I

1 -0.0004

M

0.2505

1

1 +0.0000/

N

0.3125

1

1 +0.0005/

-0.0010 -Q.0000 22

26

Bearing- F3DD Bushing- 2631507-6

13

N

27

Stud-2631515-5

17

M

I

1

0.2492

1

28

Bolt-AN23-16

13

N

I

1

0.1860

1

29

Drawbar- 2631503-4, -6

13

25

1

0.3136

0.1560

f0.0100

P

0.6250

1

1 +0.0020/

Q

0.3750

1

1 +0.0000/

Q

0.2340

+0.0000/ -0.0005 1 +0.00001 -0.0009 1 +0.0000/ -0.0020

-0.0000 -0.0010 30 31

13

Bushing- 2631 5033

0.3760

+0.0050/

+0.0010/

-0.0000

-0.0000

1 Down-springRetainerP

13

2631 505-2 32

1

1

(Alt. 2631505-4) Down-spring Retainer-

I P

13 27

2631 505-1

26315053

33

Bushing-

34

Drawbolt- 2631 504-1, -2

0.6250

I

1

1

13

I 0.5150

I P

1

1 I 0.6250

0.51 50

P

I

N

1

R

I

1 0.3160

0.5000

1 +0.0020/ 1 -0.0000 1 +0.0000/ 1 -0.0050 +0.0000/ -0.0005

1

+0.0000/ -0.0020 1 +0.00001 -0.0050

1 +0.0040/

1

-0.0000 35

Stud- 263151 5-5

13

1

1

0.2492

1

1 +0.0000/ -0.0009

Elevator

ALL

System Allowable Wear and Repair Data Figure I (Sheet 15 of 29) 51-71-10

Page SRM-4

15

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

NO. 36

37

I DESCRIPTION Rod End 2531538-3

I EFF.

HOLE

17

R

13

M

HOLE

MFD

MFD

ALLOWANCE

WEAR

ALLOWANCE

I SHAFT

ID

I

0.2492

i

OD

I

OD

ID

ID

OD

1 Bearing

(Alt. HMK-4DA) Bearing Rod End

HMVV-4

Clevis Rod End 2331510-32

13

39

Bolt- NAS464P4-11

13

40

SectorAssy-

38

I

1

S

1 +0.0010/ -0.0000

S

I

1

0.2492

1

1 +0.00001 -0.0009

2315121-24

32

231 5147-2

41

33

43

S

0.7788

1

T

1.4363

1

S

0.7500

1

T

1.4370

1

1 +0.0005/ -0.0005 1 +0.0005/ -0.0000 1 +0.0030/ -0.0000 1 +0.0030/ -0.0000

1 BearingAN201 KP-4-A MS27645-4A

42

1

S S

32 33

(Alt. -KS4A) (Alt. -AN200KS4A) Bearing-

I

I

0.2500

0.9014

I

I

1

+0.0000/ -0.0005

+0.0000/ -0.0005

8-540-22

32

T

DPP-6 Bolt- AN6-17

33

T

34

T

I

1

0.3742

1

1 +0.0000/

35

T

I

1

0.3742

1

1 +0.0000/

-0.0009

NAS464P6-21,

-22

-0.0009 44

Bracket2331 006-11, -12, -18, -19, -25, -26, -49, 60

2331006-60, -61

41

1 1

1

T

I

0.3747

I

1 +0.0015/ 1 -0.0000 1 +0.0010/

1

I

42

T

0.3750

1

-0.0010

45

Pulley- MS20220A1

36

U

0.3125

46

Bracket- 2615114-1, -4

36

U

0.3120

47

Bolt- AN25-17

36

U

Elevator

)EFFECTIVITY:

ALL

I

1.7500

1 1

0.3110

~0.0005

Jr0.0050 1 +0.0100 -0.0000 1 1 +0.0000/ -0.0020

System Allowable Wear and Repair Data Figure 1 (Sheet 16 of 29) 51-71-10

Page 16 SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

I

ITEM

I

I HOLE I

EFF.

DESCRIPTION

NO.

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE OD

ID

3.0000

~0.0005 1 +0.01001

0.3110

1

36 36

V

Bracket- 2515115-1

50

Bolt- AN25-17

36

V

37

W

0.31 25

3.0000

10.0005

~t0.0050

38

W

0.3125

3.0000

f0.0005

~H).0050

Bracket251 2500-24

39

W

0.3120

1

1 +0.0060

2615119-1

40

W

0.3120

1

-0.0010 1 +0.0100

511

I

1 i

OD

-0.0000 1 +0.0000/ -0.0020

PulleyMS20220-2 MS20220A2

52

0.3125 0.3120

V

ID

ALLOWANCE

~0.0050

48 49

Pulley- MS20220A2

WEAR

1

-0.0000 53

Bracket251 2500-22

39

W

0.3120

1

1 +0.0060

2615112-2

40

W

0.3120

1

1 +0.0100

39

W

0.3120

1

40

W

0.3120

1

1 +0.0060 -0.0010 1 +0.0100/

36

WI

-0.0010 -0.0000 Bracket- 2512500-23

54

2615113-1

-0.0000

Bolt- AN25-27

55

1

0.3110

1

1 +0.0000/ -0.0020

56

1

Pulley- MS20220A2

1

X

0.3125

Bracket- 2512500-5, -6, -7,

1

X

0.3120

+0.0050

+0.0005/

3.0000

-0.0000

57

-8, -11,-12, -42, -44, -55, 1 -56,-57,-58

I X

1

59

Bolt- NAS464P5-44 NAS464P5-23 Pulley- MS20220A2

60

Bracket- 2512500-27, -28

58

1 +0.00601

1

I

I 1

Y

4

1

i

1

j

I

0.3117

+0.0010

1 +0.0000/

1

I

1 -0.0009 rt0.0050

M.0005

3.0000

Y

0.3125 0.3120

1

1 +0.0060/

Y

0.3120

1

1 +0.0060/

-0.0001

1

2488510-4, -5

5

2488710-4, -5

6

Y

0.3120

1

1 +0.0060/

2512500-6, -1 7, -1 8, -33, -34, -39, -40, -47

7

Y

0.3120

1

1 +0.0060/

-0.0001 -0.0001

61

Bolt- NAS464P5-44, -23

1 1

Y

I

I

I

1

1 0.3117

1

-0.0001

1 +0.0000/ -0.0009

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 17 of 29) 51-n-lo

Page SRM-I

17

Jun 6/98

I

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I DESCRIPTION

Pulley- MS20220A1 Bracket- 2312500-34, -35, -36 Bolt- NAS464P5-22

62 63

64

I

I

MFD

MFD

HOLE

SHAFT

OD

EFF.

HOLE

ID

1

Z

0.31 25

1

Z

0.3120

1

I

1.7500

I 1

Z

1

AA

Bolt- AN5-24, -25

1

AA

SectorAssy. -2315147-1,-9

1

As

1.3125

AC

0.7500

I

1

I I

1

MFD

ALLOWANCE

ID

OD

rt0.0005

~0.0050

WEAR ID

ALLOWANCE OD

1 +0.0060/

1 -0.0010 1 1 +0.00001

0.3117

-0.0009

65

1

Pulley-

MS20220-2

I

1

0.3120

1

1 +0.0000/ -0.0030

66

i +0.0010/ -0.0000

1

1 +0.0030/ -0.0000

BearingBearing-

67 68

8-540-ZZ

1

AB

MS21233-5

1

AC

0.3125

0.7500

+0.0000/

+0.0000/

-0.0005

-0.0005

801t-

69

NAS464P4-9,

-12

43

AC

I

1

0.2492

1

1 +0.00001

44

AC

I

1

0.3117

1

1 +0.0000/

-0.0009

NAS464P5-12

-0.0009 Clevis Rod End

70

2315121-14, -33

43

AC

0.2500

1

1 +0.0010/

2315168-5

44

AC

0.3117

1

1 +0.0010/

-0.0000 -0.0000 71

72

1

BearingRodEnd2315121-14,-33

43

RE5M6

44

AD AD

43

AD

I

1

0.3117

1

1 +0.0000/

44

AD

I

1

0.3117

1

1 +0.0000/

44

AD

(Alt. REP5M6FS464) (Alt. MS21151-10) Bolt- NAS464P4-9, -12

-0.0009

NAS464P5-27,

-32

-0.0009 73

Bushing- NAS75-5-13,

74

Bushing- NAS75-5-013

-018

1 44

Elevator

I

EFFECTIVITY: SRM-I

ALL

0.3125

I AE

0.4386

I 0.3125

+0.0015/

j -0.0000 0.4386

+0.0000/ -0.0005

+0.0015/

+0.0000/

-0.0000

-0.0005

System Allowable Wear and Repair Data Figure 1 (Sheet 18 of 29) 51-71-10

Page

18

Tun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I EFF.

DESCRIPTION

NO.

Yoke

75

I HOLE I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

WEAR

ALLOWANCE

ID

OD

ID

ALLOWANCE OD

Assembly 45

2415152-1, -3

(Alt. 2415152-5)

46

2615270-1

AD

0.4375

1

1 +0.0005

AE

0.4393

AF

0.3750

1 1

AG

0.3373

1

AD

0.4375

AE

0.4393

AF

0.3750

AG

0.3373

1 i i 1

1 ~0.0005 1 ~0.0005 1 +0.0005/ -0.0012 i f0.0005 I f0.0005 1 ~0.0005 i +0.0005/ -0.0012

1

-19,-26

Bearing Rod

77

AF

48

Bolt- NAS464P4-15, -17,

76

I

I

i

I

I

I

1

0.2492

1

1 +0.0000/

1

-0.0009

End

SM4-6D-1

48

AF

(Alt. RM4B) (Alt. RM4BH) 1 +0.0000/

78

Bolt- NAS464P4-10

48

AG

79

Bushing- NAS75-4-10,

48

AF

80

NAS77-4-27 I Servo Cable 2300003-256

1

K

81

Bolt- NAS464P3-7

1

K

i

i

0.1894

i

1 +0.0000/

82

Bolt- NAS1104-48D

1

H

I

1

0.2495

i

1 +0.0000/

83

Turnbuckle- 2631511-1

1

H

0.2510

1

1 +0.0030/

84

Bracket- 2331516-2, -17,

17

AF

0.2500

i

i +0.0050/

AF

0.2500

1

0.2492

1

-0.0009

I

I 0.1900

+0.0015/

0.3761

0.2500

I

1 -0.0000

1

1 +0.0020/

+0.0000/ -0.0005

-0.0000 -0.0009 -0.0010 -0.0000

-18, -20, -21 85

1

Pulley-

MS20219-A2

1

j 17

1

1

-0.0010

1 +0.0000/ -0.0005

AF

i

1

0.2490

1

1 +0.0100/

86

Bolt- AN4-10

17

87

Bracket- 2331516-3

17

i

AG

0.2500

1

i +0.0050/

88

Pulley-MS20219-A2

17

1

AG

0.2500

1

i +0.000/

89

Bolt- AN4-10

17

i

AG

Fork-2331519-8, -19

17

-0.0100

-0.0010 -0.0005

I

i

0.2490

1

1 +0.00101 -0.0010

90

1

AH

0.1890

i

+0.0050/

-0.0010

Elevator

EFFECTNITY:

ALL

System Allowable Wear and Repair Figure 1 (Sheet 19 of 29)

Data

57-71-10

Page SR~-4

19

Jun 6/98

1

Learpt

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

91

I

I EFF.

DESCRIPTION

1 Pin, Clevis- MS20392-2C19

I HOLE AH

17

MFD

MFD

HOLE

SHAFT

ID

OD

I

1 0.1380

MFD

ALLOWANCE

ID

1

OD

WEAR ID

ALLOWANCE OD

1+0.0000/ -0.0020

92

Fork, TurnbuckleNAS645-1 6RL

29

AJ

I

1 0.1900

1

1 +0.01001 -0.0100

1

1+0.00101

I

1

0.1930

1

1 +0.0010/ -0.0010

0.1900

1 1 0.1380

1 +0.0010/ 1 -0.0010 1 1+0.0000/

1

1+0.0015/

Eye -TurnbuckleNAS648-16RL 93

Link- 2431110-2

94

Eye-Turnbuckle-

AJ

30

I

(Ait. MS21254-3RL)

AJ

30

NAS64&1 6RL

30

95

(Alt. MS21254-3RL) I Pin, Clevis- MS20392-2C19

96

Angle,

97

Bushing- NAS77-6-22

0.1900

I

1

AJ

I

I

30

AJ

16

AK

0.3747

14

AL

0.3750

I

-0.0010

-0.0020

Attach- 2331006-49

-0.0000

0.5013

+0.0015/

+0.0000/

-0.0000 98

Bolt- NAS464P6-22

-0.0007

14

IAK,ALI

1 0.3742

1

1+0.0000/

15

IAK,ALI

1

1

1+0.0000/

14

AL

14

1 AM,

15

1

-0.0009

NAS464P6-17

0.3742

-0.0009 99

1 Bushing-

NAS77-6-25

0.3750

0.5013

+0.0015/

+0.0000/

-0.0000 100

Bolt- NAS464P6-23 NAS464P6-22

-0.0007

i

1 0.3742

1

1+0.0000/

AN

i

I

I

1 -0.0009

AM,

i

1 0.3742

1

1+0.0000/

I

14

AN AM

I 1

I 1 -0.0009 1+0.0015/

101

Bracket Assy.

102

Bolt- NAS464P6-17

15

AK

I

1 0.3742

1

1+0.0000/

103

Bolt- NAS464P6-22

15

AM

I

1 0.3742

1

1+0.0000/

104

Bolt- NAS464P4-10

18

R

I

1 0.2492

1

1 +0.0010 -0.0010

105

Bolt- NAS464P4-9

18

AK

I

1 0.2492

1

1 +0.0010

106

Frame

2331050-1

0.3747

-0.0000 -0.0009 -0.0009

-0.0010

Assy, Down-spring

2531 542-1, -7

19

AK

0.2492

1

1+0.0010/

AL

0.2725

1

1+0.0010/

-0.0000 -0.0000

Elevator

I

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 20 of 29) 51-71-10

Page 20 SRM-4

Jun 6/98

Learjet Learietl

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.

I

I

I HOLE

EFF.

DESCRIPTION

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

AM

0.5650 1

1 +0.0010/

AK

0.2492

1

i +0.00101

AL

0.2725 1

AM

0.5626 1

OD

WEAR ID

ALLOWANCE OD

-0.0000

20

2531542-13, -16

AK

21

2531542-17

i

-0.0000 1 +0.00101 -0.0000 1 +0.00021 -0.0002 +0.00001

0.2492

i

-0.0009 AL

0.2725

1

AM

0.5626

1

1 +0.00101 -0.0000

AN

I

1

1 +0.0002/ -0.0002 0.1860 1 1 +0.0010/

23

AL

i

1

0.1860

24

AO AP

0.5310 0.2485 i

AO

0.5310

AP

0.2500 i

AP

0.1870

107

Bolt- AN23-42

21

108

Bolt- AN23-15

109

Drawbar- 2531534-1

1

-0.0000

1 +0.00101 -0.0000

1

1 +0.0010/ -0.0000

25

2531 534-6

1 +0.00101 -0.0000

110

Bushing-

24

2531 534-4

2531 5346 111

Retainer, Fwd- 2531536-2 2531 54&1

112

Retainer, Aft- 2531536-2 253154&1

25

AP

0.1870

24

AQ

0.5310

26

AR

0.6250

24

26 28

+0.00051

0.2485

0.2500

+0.0010/

-0.0005

-0.0000

+0.0005/

+0.00001

-0.0000

-0.0010

1

1 +0.00201 -0.0000

AS

0.5310

AT

0.6250 i

1 +0.00201

AU AO

0.2485

0.5000

+0.00101 -0.0000

0.1870

0.2485

+0.0005

-0.0000 113

Drawbolt- 2531535-1, -4

AR 114

Bushing- 2531 535-3

28

AQ AU

+0.00101 -0.0000

-0.0005

115

Stud- 2631515-1

31

AV

i

1

0.2492

1

1 +0.00001 -0.0009

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 21 of 29) 51-71-10

Page SRM-I

21

Jun 6/98

1

Learjet E~ Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO. 1

2

3 4

5

6

DESCRIPTION

EFF.

Bellcrank

Assy. 2331511-15, -16, -33, -34, -45, -46, -61, -62, -83, -84, -101,-102,-801,-802

Bearing-

MS27645-4A

1

HOLE

A, B, C,I Replace

A

Pin

HL 18-8-9

2

A

Bolt

2331151 t -87

3

A

NAS464P4A-32 NAS464P4A-30

4

SB410F4-28S

6

5

Torque Tube 2434003-7 Bearing- BLFR-4-045

worn

part.

D 1

Bolt

REPAIR

1

B, B, B, B,

I Replace worn part. Stake new bearing primer or secure with Loctite. (Refer to 00.) Replace Replace Replace Replace Replace

part. part. worn part. worn part. worn part. Replace worn part. Replace worn part. Stake

C

C C C D

1

primer

in wet 51-70-

worn worn

or secure

new

with Loctite.

bearing

(Refer

in wet

to 51-70-

00.) 9 8

Bolt NAS464P4-14 Rod End Clevis 2331510-75 233151031

10

Hinge Assy. 2332018-16, -20, Bearing AN201 KP4A

11

Bolt

12

13

Hinge Assy. 2332013-19, -22, Bearing AN201 KP4A

14

Bolt

15

Bearing Rod End 2331510-28 Bearing- AN200KS-4

9

16

-22

AN4H11 A

AN4H11A

(Alt. MS27645-4)

7

D D

8

D

1

E

1

E

1

E

1

F

1

F

1

-24

1

F

1

G G

1

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Secure new Loctite. (Refer to 51-70-00.) After assembly to a push out proof pounds. I Replace worn part. Secure new Loctite. (Refer to 51-70-00.) After assembly to a push out proof

G

1

bearing with subject

cure,

load of 300

bearing with subject

cure,

load of 300

pounds. 17

1 Yoke

9 10

2531533-1

11

2531533-5

12

263150&2

13

18

Bolt

19

Cable

20

2331512-2

2331517-2

H, H, H, H, H,

NAS464P4-35

1

G

Fitting 2631509-1 (Alt. 2631509-2) 1 Hinge Bracket 2331510-17

1 1

H,K H,K

1

J

Elevator

I

G, G, G, G, G,

EFFECTIVITY:

ALL

J J J J

J

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part.

part. part. part. part. part. part. part.

System Allowable Wear and Repair Data Figure 1 (Sheet 22 of 29) 51-71-10

Page 22 SRM-(

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

23

NAS464P4-9 Frame Brkt 2531539-1 Bolt AN23-13

24

Down-spring

21

Bolt

22

Down-spring

i

Frame- 2631507-1, -8,

EFF.

HOLE

REPAIR

1

J

Replace worn part.

1

L

1

L

13

L, M,N

Replace worn part. Replace worn part. Replacewompart.

0, -12, -16

25

1 Bearing-F3DD

22

L

26

1 Bushing-2631507-6

13

N

Replace worn part. Install new bearing with flange inboard and secure with Loctite. (Refer to

51-70-00.)

I Replace

worn

flange inboard

part. Install and

Stud

2631515-5

17

28

13

M N

29

Bolt AN23-16 Drawbar 2631503-4, -6

13

P, Q

30

Bushing- 2631503-3

13

Q

13

P

Replace worn part.

1 Down-spring

(At2631505-4) 1 Down-spring Retainer2631505-1

33

34

Bushing

26315053

Drawbolt

2631504-1, -2

2631504-2

35

Stud

36

Bearing Rod End Bearing Rod End

37

2631515-5 253153&3 HMVV-4

41

Clevis Rod End 2331510-32 Bolt NAS464P4-11 Sector Assy. 2315147-2 Bearing MS27645-4A

42

(Alt. KSIA) (Alt. AN200KS4A) Bearing 8-540-ZZ

38

39 40

bushings with (refer to

Retainer-

26315052 32

new

with Loctite

51-70-00), and line ream 0.1895 (+0.0010/ -o.oooo). Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install new bushings with Loctite (refer to 51-70-00), and ream in line after cure to 0.2500 (+0.0010/-0.0000).

27

31

secure

13

P

Replace worn part.

27

P

Replace worn part.

13

AS AT N, P

11

N, P

13 17

R

13

M

13

S S

13 33

R

S,

T

32

S

1

T

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part.

part. part. part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Secure new bearing with Loctite. (Refer to 51-70-00.)

I Replace worn part.

Secure new bearing with (Refer to 51-70-00.) I Replace worn part. Secure new bearing with Loctite. (Refer to 51-70-00.) Loctite.

1

DPP-6

Elevator

EFFECTIVITY:

ALL

T

System Allowable Wear and Repair Data Figure 1 (Sheet 23 of 29) 51-71-10

Page 23 SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

EFF.

43

Bolt

44

NAS464P6-21, -22 Bracket 2331006-11, -12, -18, -19, -25, -26, -49, -50,

45 46 47

AN6-17

34

T

35

T

41

T

2331006-60, -61

42

T

Pulley MS20220A1

36

U

Bracket 2615114-4 Bolt AN25-17

36

MS20220A2

36

2615115-1

36

U U V V

48

Pulley

49

Bracket

50

Bolt

36

54

AN25-17 Pulley MS20220-2 MS20220A2 Bracket 2512500-24 2615119-1 Bracket 2512500-22 2615112-2 Bracket 2512500-23

55

2615113-1 Bolt AN25-27

56

Pulley MS20220A2

51 52

53

1

59

MS20220-2 Bracket- 2512500-5, -6, -7, -8, -11, -12, -42, -44, -55, -56, -57, -58 Bolt NAS464P5-44, -23 Pulley MS20220A2

60

Bracket

57

58

HOLE

36

V

37

W

38

W

39

W

40

W

39

W

40

W

39

W

40 36

W W

1

X

1

I

X

1

X

1

Y

4

Y

5

Y

6

Y

7

Y

1

Y

1

Z

61

2512500-27, -28 2488510-4, -5 2488510-4, -5 2512500-6, -17, -18, -33, -34, -39, -40, -47 Bolt NAS464P5-44, -23

62

Pulley

63 64

Bracket 2312500-34, -35, -36 Bolt NAS464P5-22

1

Pulley MS20220-2 Bolt AN5-24-25 Sector Assy. 2315147-1, -9 Bearing- B-540-ZZ

1

Z Z AA

1

AA

1

1

AB AB

Bearing MS21233-5 (Alt. LHBVV-5M) (Alt. RSST-5)

1

AC

65 65A 66 67 68

MS20220A1

Elevator

)EFFECTIVITY: SRM-I

ALL

1

REPAIR

Replace worn part. Replace worn part. Replace worn part. Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

part. part. part. part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part.

I

Replacewompart. Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install new bearing and cure with Loctite. (Refer to 51-70-00.) Replace worn part. Install new bearing and secure with Loctite. (Refer to 51-70-00.)

se-

System Allowable Wear and Repair Data Figure I (Sheet 24 of 29) 51-71-10

Page 24 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM I EFF.

DESCRIPTION

NO.

Bolt NAS464P4-9, -12 NAS464P5-12 Clevis Rod End 2315121-14, -33 231416&5 Bearing Rod End2315121-13, -33 RE5M6

69 70 71

(Alt. REP5M6FS464) (Alt. MS21151-10) Bolt NAS464P4-9, -12 NAS464P5-27, -32 Bushing NAS75-5-13, -018 Bushing NAS77-5-013 Yoke Assembly 2415152-1, (Alt. 2415152-5)

72

73 74

75

77

Bolt

82 83 84

worn worn

43

AC AC AD

1

AD

Replace worn part. Replace worn part. AD Replace worn part. AD Replace worn part. AD Replace worn part. AE Replace worn part. AD, AE,I Replace worn part.

44

44 44

45

AD, AE,( Replace AF, AG

46

NAS464P4-10

Replace worn part. I Replace worn part.

AD

43

-3

part. part. Replace worn part. Replace worn part.

AD

44

NAS77-4-27 Servo Cable 2300003-256 Bolt NAS464P3-7 Bolt NAS1104-48D Turnbuckle 2631511-1 Bracket 2331516-2, -17, -18,

81

Replace

j Replace

44

Bushing NAS75-4-10

80

AC AC

44

1 Bolt NAS464P4-15, -17 l\lAS464P4-19, -26 Bearing Rod End SM4-6D-1 (Alt. RM48) (Alt. RM4BH)

78 79

43

43

1

REPAIR

44

44

2615270-1 76

HOLE I

worn

part.

worn

part.

48

AF

Replace

48

AF

Replace worn part.

48

AG

48

AF

Replace worn part. Replace worn part.

1

K

1

K

1

H

1

H

17

AF

Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part.

-20, -21 86 87 88 89

90 91 92

MS20219-A2 Bolt AN4-10 Bracket 2331516-3 Pulley MS20219-A2 Bolt AN4-10 Fork 2331519-8, -19 Pin, Clevis MS20392-2C19 Fork, Turnbuckle NAS645-16RL Eye, Turnbuckle NAS648-16RL

Pulley

85

1

17 17

AF

Replace worn part.

AF

I Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. I Replace wompart.

17

AG

17

AG

17

AG AH AH AJ AJ

17

17 29

1

1

30

(Alt. MS212543RL)

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Figure Z (Sheel 25 of 29)

Data

51-71-10

Page 25 SRM-4

Jun 6/98

Leariet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM NO.

DESCRIPTION 2431110-2 Turnbuckle NAS64&16RL

93 94

Link

95

Pin, Clevis

Eye, (Alt. MS21254-3RL)

MS20392-2C19

EFF.

HOLE

30

AJ

30

AJ

30

97

Angle, Attach Bushing NAS17-6-22

16

98

Bolt- NAS464P6-22

14

15

105

NAS464P6-17 Bushing- NAS77-6-25 Bolt NAS464P6-23 NAS464P6-22 Bracket Assy. 2331050-1 Bolt NAS464P6-17 Bolt NAS464P6-22 Bolt NAS464P4-10 Bolt NAS464P4-9

106

Frame

96

99

100 101 102 103 104

2331006-49

Assy,

Down

14

14 14

15 14

15 15

18 18

REPAIR

Replace worn part. Replace worn part.

Replace worn part. Replace worn part. AL Replace worn part. AK, AL Replalceworn part. AK,AL Replaceworn part. AK, AL Replaceworn part. AM, AN~ Replace worn part. AM, AN I Replace worn part. AM Replace worn part. AK Replace worn part. AM Replace worn part. R Replace worn part. AK Replace worn part. AJ

AK

Spring 19

IAK,AL

Repiaceworn part.

2531542-13, -16

20

AM AK, AL AM

Replaceworn part.

2515542-17

21

IAK,AL

Replaceworn part.

2531542-1,-7

AM 21

110

Bolt AN23-42 Bolt AN23-15 Drawbar- 2531534-1 2531534-6 Bushing 2531534-4

25

111

25315346 Retainer, Fwd

107 108

109

23 24

25 24

2531536-2

24 26

253154&1 112

Retainer, Aft 2531536-2

24

26

113

253154&1 Drawbolt 2531535-1, -4

28

Replace worn part. Replace worn part. AO, AP I Replace worn part. AO, AP I Replace worn part. AP Replace worn pa~. AP Replace worn part. AQ Replace worn part. AR Replace worn part. AS Replace worn part. AT Replace worn part. AU, AO I Replace worn part. AN AL

AR, AQ 114 115

Bushing Stud

28

2531535-3

31

26315351

Elevator

I

EFFECTIVITY: sRM-a

ALL

AU AV

Replace worn part. Replace worn part.

System Allowable Wear and Repair Data Figure 1 (Sheet 26 o~ 29) 51-71-10

Page 26 lun 6/98

Learjet ~LearjetJ

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-001 thru 23-099; 24-100 and

Subsequent Except When Modified by SSK 995, "lnstallation of Equipped for 45,000 Foot Operation"; 25-001 and Subsequent Except When Modified by SSK 995, "lnstallation of Spare Elevator Aircraft Equipped for 45,000 Foot Operation"; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 thru 31-020; 35001 thru 35-659;

Spare Elevator

Aircraft

36-001 thru 36-063 3

4 5

Subsequent When Modified by SSK 995, "lnstallation of Spare Elevator Aircraft Equipped for 45,000 Foot Operation"; 25-001 and Subsequent When Modified by SSK 995, "lnstallation of Spare Elevator Aircraft Equipped for 45,000 Foot Operation" 31-021 and Subsequent; 35060 and Subsequent; 36-064 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 35-001 thru 35-421; 36-001 thru 36-048 31-001 and Subsequent; 35-422 and Subsequent and All 23, 24, 25, 28, 29, 31 and 35 Series Aircraft Modified Per SSK 995, "lnstallation of Spare Elevator Aircraft Equipped for 45,000 Foot Oper24-100 and

ation" 6 7

8

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and 001 and Subsequent 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 35-001 and 001 and

Subsequent;

29-

Subsequent;

36-

Subsequent

10

23-001 thru 23-099; 24-100 thru 24-121, 24-123 thru 24-132 and 24-134 thru 24-139 24-122, 24-133, 24-140 and Subsequent; 25901 thru 25-060 and 25-062 thru 25-066

11

25-061, 25-067 thru 25-125

12

25-126 and 2&001 and

9

13

36-001 and

Subsequent Subsequent; Subsequent

14

24-100 thru 24-129

15

24-130 and 24-100 and

16 17

29-001 and

Subsequent;

31-001 and

Subsequent;

35001 and

Subsequent;

Subsequent Subsequent

25-061, 25-064, 25-067 and Subsequent and Prior Aircraft Modified by AAK 70-058, "Automatic Flight Control Stability System and Trim Augmenter Installation" or AAK 76-04A, "Reduced Approach

Speed System"; 28001 and Subsequent; and Subsequent; 36-001 and Subsequent

29-001 and

Subsequent;

31-000 and

Subsequent; 35-001

18

25-061,25-064, 25-067 thru 25-224 and 25-226 and Prior Aircraft Modified by AAK 70-058, "Automatic Flight Control Stability System and Trim Augmenter Installation" or AAK 76-04A, "Reduced Approach Speed System" Except When Modified by AMK 77-09A, "lnstallation of Dual Elevator Upl

19

25-061, 25-067 thru 25-182

20

25-183 thru 25-224 25-225, 25-227 and

Down-spring Secondary

21

Pushrods"

Subsequent

and Prior Aircraft Modified

by AAK 70-058, "Automatic Flight Con-

Stability System and Trim Augmenter Installation" or AAK 76-04A, "Reduced Approach Speed System" or AMK 77-09A, "lnstallation of Dual Elevator Up/Down-spring Secondary Pushrods" 25-225, 25-227 and Subsequent and Prior Aircraft Modified by AAK 70-058, "Automatic Flight Control Stability System and Trim Augmenter Installation" or AAK 76-04A, "Reduced Approach Speed System" or AMK 77-09A, "lnstallation of Dual Elevator Up/Down-spring Secondary Pushrods"; 28 001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 25-061, 25-064, 25-067 and Subsequent and Prior Aircraft Modified by AAK 70-058, "Automatic Flight Control Stability System and Trim Augmenter Installation" or AAK 76-04A, "Reduced Approach Speed System" trol

22

23

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 27 of 29) 51-71-10

Page SRM-4

27

Tun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL CODES 24

EFFECTIVITIES 25-061,25-067 thru 25-253

25

25254 and

26

25-254 and

Subsequent Subsequent and

Prior Aircraft Modified by SSK 960, "Replacement of Elevator Up/DownDrawbolt and Retainer" 25-254 and Subsequent and Prior Aircraft Modified by SSK 960, "Replacement of Elevator Up/ Downspring Drawbolt and Retainer"; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent 25-061,25-067 and Subsequent 24-140 thru 24-217 and 24-219 thru 24-229 Except When Modified by SE 31-32-2, Installation of Digital Nose Wheel Steering"; 25-002 thru 25-060, 25-062 thru 25-067, 25-070, 25-074 and 25-075 Except When Modified by SE 31-32-2, Installation of Digital Nose Wheel Steering" 24-218, 24-230 and Subsequent and 24-140 thru 24-217, 24-219 thru 24-229 When Modified by SE 31-32-2, Installation of Digital Nose Wheel Steering"; 25-064, 25-071 thru 25-073, 25-076 and Subsequent and Prior Aircraft Modified by SE 31-32-2, Installation of Digital Nose Wheel Steering"

spring

27

28 29

30

31

25-225, 25-227 and Subsequent

32

23-001 thru 23-069

33

23-070 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 thru 24-357; 25001 thru 25-301; 28-001 thru 28-005; 29-001 thru 29-

34

002; 35-001 thru 35296; 36-001 thru 36-044

Subsequent;

25302 and

Subsequent;

Subsequent;

35

24-358 and

36

31-001 and Subsequent; 35297 and Subsequent; 36-045 and Subsequent 24-306 thru 24-308, 24-323 and Subsequent; 25-196, 25-202 and Subsequent; 2&001 and Subse-

28-006 and

29-003 and

Subsequent;

quent; 29-001 and Subsequent; 31-001 and Subsequent; 35-046 and Subsequent; 36-017 and Subsequent 38

23-001 thru 23-099; 24-100 and Subsequent 25001 and Subsequent; 28-001 and Subsequent; 29-001 and

39

35-001 and Subsequent; 36-001 and 25-001 thru 25-201 Except 25-196

40

25-196, 25-202 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and

41

23-001 thru

42

Subsequent; 31-001 thru 24-357 and Subsequent; 36-001 and Subsequent

37

Subsequent;

35-001 and

Subsequent;

31-001 and

Subsequent;

Subsequent

Subsequent;

36-001 and

Subsequent

23-099; 24-100 thru 24-356, 25-001 thru 25-372, 28-001 and Subsequent; 29-001 and 31-027 25-373 and

Subsequent;

31-028 and

Subsequent;

35-664 and

Subsequent;

43

23-001 thru 23-010, 23-013, 23-014, 23-016 thru 23-018, 23-020 thru 23-030, 23-032 thru 23-042, 23-044 thru 23-049, 23-050a, 23-052 thru 23-054, 23-056 thru 23-059, 23-061 thru 23-064, 23-065a thru 23-086, 23-088 thru 23-095, 23-097 thru 23-099

44

23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051, 23-055, 23-060, 23-065, 23-087, and 23-096; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and

45

31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 35-001 thru 35-487; 36-001 thru 36-050

46

31-001 and

47

24-122, 24-133, 24-140 and Subsequent and Prior Aircraft Equipped With Elevator Bob Weight;

Subsequent;

Subsequent;

35-488 and

Subsequent;

36-051 and

001 and Subsequent; 2&001 and Subsequent; 29-001 and 35-001 and Subsequent; 36-001 and Subsequent

Elevator

I

EFFECT~VITY:

ALL

Subsequent

Subsequent;

31-001 and

25-

Subsequent,

System Allowable Wear and Repair Data Figure 1 (Sheet 28 of 29) 51-71-10

Page 28 SRM-(

Jun 6/98

Learjet Leariet I

STRUCTURAL REPAIR MANUAL 48

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28001 and 001 and Subsequent; 31-001 thru 31-076; 35-001 thru 35-676; 36-001 thru 36-063

49

31-077 and

Subsequent;

35-677 and

Subsequent;

36-064 and

Subsequent; 29-

Subsequent

NOTES:

When 1. 2.

3.

replacement of the NAS464P4A-30

and the NAS464P4A-32 bolt is

required,

the

following

should be used: NAS6604-30 or NAS6604-32 should be used when an oversized bolt is not required. NAS6604-30X or NAS6604-32X should be used when an 1/64 inch oversized bolt is required. NAS6604-30Y or NAS6604-32Y should be used when an 1/32 inch oversized bolt is required.

Elevator

EFFECTIVITY:

ALL

System Allowable Wear and Repair Data Figure 1 (Sheet 29 of 29)

51-71-10( Page 29

SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL KEELBEAM ASSEMBLIES

ALLOWABLE WEAR AND REPAIR DATA

A

A

6

\4

B

(TYPICAL)

Detail A (UNDERWING KEELBEAM) 4-10C

EFFECTIVITY:

Keelbeam

ALL

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 1 of 3) 51-71-11

Page SRM-4

1

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM

NO.

DESCRIPTION

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID 0.3120

1

Fitting, Unden~ving Keelbeam

1

A

2

Aft LHIRH -2311611-5, -6 Bolt- MS20005-14

1

A

3

Fitting, Unden~ving Keelbeam

1

B

MFD

ALLOWANCE OD

ID

WEAR 10

ALLOWANCE OD

+0.0060/ -0.0010 +0.001 5/

0.31 02

-0.0000 Fwd LH/RH

+0.0060/ -0.0010

0.3120

2311611-7,

-8 4

Bolt- MS20005-36

1

B

5

Fitting, Aft Keelbeam, LH/RH

1

A

0.3120

6

Fitting, Fwd Fuselage

1

B

0.3120

+0.001 5/

0.31 02

-0.0000

-2312013-1, -2

Keelbeam, LH/RH-

+0.0060/ -0.0010 +0.0060/ -0.0010

2311241-1

Keelbeam

I

EFFECTIVITY: SRM-I

ALL

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 2 of 3) 51-71-11

Jun

6/98Page2

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO.

Fitting, Underwing Keelbeam,

1

REPAIR

HOLE

1

A

I

Replacewompart.

Aft LH/RH -2311 611-5, -6 2

Bolt

1

A

3

Fitting, Unden~ving Keelbeam,

1

B

4

Bolt

1

B

5

Fwd LH/RH 231 1611-7, -8 MS20005-36 Fitting, Aft Keelbeam, LH/RH

1

A

6

Fitting, Fwd Fuselage Keelbeam,

1

B

MS20005-14

Replace worn part. Replace worn part. Replace worn part. Replace worn part.

-2312018-1, -2

I

Replacewompart.

LH/RH- 2311241-1

CODES 1

EFFECTIVITIES 23-002 thru 23-099; 24-100 thru 24-357; 25-002 thru 25-373; 28-001 thru 28004; 29-001 thru 29004; 31-001 and Subsequent; 35-001 and Subsequent; 36001 and Subsequent

Keelbeam

EFFECTIVITY:

ALL

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 3 of 3) 51-71-11

Page 3 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL MACH TRIM SYSTEM

ALLOWABLE WEAR AND REPAIR DATA

A 0000~

D

,6

~-B

rc~,

r\

1

4

(TYPICAL)

Detail A &nB

EFFECTNITY: SRM-4

Mach Trim

System Allowable Wear and Repair Figure 1 (Sheet 1 of 3)

Data

28-001 AND SUBSEQUENT; 29-001 AND SUBSEQUENT; 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

51-71-12

Page 1 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

NO. 1

I EFF.

DESCRIPTION Bracket

I

Assy., 2605206-2,

HOLE A

1

1

-7

I

I

2

Link- 2605206-5

1

3

Bolt- NAS1103-6

1

4

Bushing- NAS74A3-003

1

5

Bolt- NAS1103-4

1

6

Bushing- NAS74A3-003

1

7

Arm, Mach Trim System

HOLE

MFD

ALLOWANCE

ID

I

0.1895

1 I

1 +0.00101 1 -0.0000

0.3725

1

1 +0.00101 -0.0000

I B

MFD

A,B I

WEAR

ALLOWANCE

I SHAFT

1

OD

0.1895

I

ID

1

OD

ID

OD

1 +0.0000/ -0.0010

A

0.1900

B,C I

+0.0010/ -0.0005

0.3730

1

0.1895

1

+0.0000/ -0.0020

1 +0.0000/ -0.0010

1

2605206-4

B

1

0.1900

0.3730

C

0.1895

1

D

0.2500

1

+0.0010/ -0.0005

+0.0000/ -0.0020

1 +0.0010/ -0.0000 1 +0.0040/ -0.0000

Mach Trim

I""""": SRM-4

28-001 AND

System Allowable Wear and Repair Data Figure 1 (Sheet 2 of 3)

SUBSEQUENT; 29-001 AND SUBSEQUENT; 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

51-71-12

Page 2 Jun 6/98

Learjet

STRUCTURAL REPAIR IlrlANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

HOLE

1

A

1

Bracket Assy.

2

Link

3 4

Bolt

1

Bushing

1

2605206-2, -7

1

2605206-5

NAS1103-6 NAS74A3-003 Bolt NAS1103-4 Bushing NAS74A3-003 Arm 2605206-4

5 6 7

CODES 1

2&001 and

1

Subsequent; 29-001 and Subsequent; Subsequent

31-001 and

Subsequent;

35-001 and Subse-

36-001 and

Mach Trim

SRM-4

1

Install oversize bushing and ream bushing to original hole size. (Refer to 51-70-00.) B I Install oversize bushing in place of bushing (4 or 6). Ream oversize bushing to original bushing l.D. (Refer to 51-70-00.) A, B Replace worn part. A Replace worn part. B, C Replace worn part. B Replace worn part. C Replace worn part.

EFFECTIVITIES

quent;

EFFECTIVITY:

1

REPAIR

System Allowable Wear and Repair Data Figure 1 (Sheet 3 of 3)

SUBSEQUENT; 29-001 AND SUBSEQUENT; 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 28-001 AND

51-71-12

Page 3 Tun 6/98

STRUCTURAL REPAIR MANUAL CONTROL COL UMN ASSEMBL Y ALLOWABLE WEAR AND REPAIR DA TA

P

~o

I

3

B’ A

~plB"’b a63e

EFFECTIVITY:

4

Control Column

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 1 of 7)

ALL EXCEPT MODEL 23, EARLY MODEL 24

AND EARLY MODEL 25 AIRCRAFT SRM-(

51-71-13

Page

1

Jun 6/98

Learjet I

STRUCTURAL REPAIR MANUAL CONTROL COLUMN ASSEMBLY

ALLOWABLE WEAR AND REPAIR DATA

A

21

c

B/

K~B",

e

L’20//~i

B

M

Detail B

9

L´•

Detail C

Control Column

EFFECTIVITY:

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 2 of 7)

23-001 THRU 23-099, EARLY 24 AND 25 MODEL AIRCRAFT

51-71-13

Page2 SRM-I

Jun 6/98

~Learjet S~RUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

CONTROL COLUMN ASSEMBLY

F,

b

9" 11

Ilr

(TYPICAL)

Detail A 861B2

Control Column Assembly

Figure

EFFECTIVITY:

ALL

1

Allowable Wear and

Repair Data

(Sheet 3 of 7)

51-71-13

Page3 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I

I EFF.

DESCRIPTION

I HOLE

MFD

MFD

HOLE

SHAFT

ID

OD

I

0.4995

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Pin, Control Column Pivot

1

2315152-9 2

A

1

(Alt. 2315152-33) Block Assy., Bearing

1

23151525, -6, 31

I

I

1

1

1 +0.00001

I

I

I

1 -0.0010

1

1 +0.01001

1

A

1

0.7500

1

A

1

0.5000

-0.0100

Bearing- MS27641 KP8A (Alt. AN201 KP8A) Yoke Assy.

3 4

I

2415152-1

I B

2

(Alt. 2415152-3, -5)

1

261 5270-1

I

I

0.3773

I B

3

0.3773

1.1250

+0.0000/ -0.0005

I

1

1

1 +0.0005/

I

1

+0.0000/ -0.0005

-0.0005 1 +0.0005/

1

-0.0005 5

Bolt- MS20004H15

6

Bushing-

B,C I

4

1

0.2485

1

1 +0.0070/ -0.0080

7

1

NAS75-4-015

4

Bushing-NAS75-5-013

5

NAS77-5-50 8

Bushing- NAS75-4-010 NAS77-4-27

9

Block

Assy., Bearing

11

Bearing- MS27640KP4 (Alt. MS20200KP4) I Yoke Casting 2315153-32

0.3125

0.4386

+0.0015/ -0.0000

-0.0010

B

0.3125

0.4386

+0.0015/

6

B

0.31 25

0.4386

5

B

0.2500

0.3761

-0.0000 +0.0015/ -0.0000 +0.0015/

+0.0000/ -0.0005 +0.0000/ -0.0005 +0.0000/

0.3761

-0.0000 +0.0015/

+0.0000/

-0.0000

-0.0005

1

6

1

B

0.2500

4

1

C

0.9002

4

I 1

C

1

2415164-5 10

B

I

I

I 7

1

I

-0.0005

1 +0.0005/

I 0.2500

+0.0000/

1 -0.0000 0.9014

I

1

+0.0000/ -0.0005

D

0.8750

1

1 +0.01001

E

1.1865

1

1 +0.0020/

D

0.8750

1

1 +0.0100/

E

1.1865

1

1 +0.0020/

D

0.8750

1

1 +0.0100/

1.1865

1

1 +0.00201

D

0.8750

1

1 +0.01001

E

1.1865

1

1 +0.0020/

+0.0000/ -0.0005

-0.0100 -0.0000 2315153-716-2

8

-0.0100 -0.0000

2315153-40

9

i

-0.0100 E

1

-0.0000

2315153-41

10

-0.0100 -0.0000

Control Column

EFFECTIVITY:

ALL

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 4 of 7) 51-71-13

Page4 SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I

I

I

EFF.

DESCRIPTION

11

241 5152-8-495

i

2415152-9-495

HOLE I

I

D

MFD

MFD

HOLE

SHAFT

ID

OD

MFD ID

I

0.8750

1

1 +0.01001

E

1.1865

I i

1 -0.0100 1 +0.0020/

D

0.3750

I

I

WEAR

ALLOWANCE OD

I

ID

ALLOWANCE OD

-0.0000 12

13 14 15

Bearing- MS27641KP6A (Alt. AN201 KP6A) I B-539-ZZ Bearing1 I (Alt. B639-DD) 1 Capstan Assy. 2415160-3, 1 -5,-7 1 Shaft, Main Control Wheel

1

I

I

I

E

1

I

-0.0005

1.1875

+0.0007/ -0.0007

I 1

1 +0.0010/

j

I

1

F

I

+0.0000/

1

0.7500

I

12

0.8750

0.7500

+0.0000/ -0.0005 +0.0000/ -0.0010

-0.0000

2315153-28

13

1

G

I

1

0.3740

1

i +0.0002/

23151536

14

1

G

I

1

0.3740

1

1 +0.0002/

-0.0003

(Alt. 2315153-49)

16

I

I

H

i

1

15

1

H

I

I 0.7490

1

-0.0003

i +0.0000/ -0.0010

Shaft, MainControlWheel261 5271-1

17

1

1 Torque Tube

2315151-2

G

1 J

16

I

1 0.7485

I

0.3739

1

1

1 +0.0003/ -0.0002

1 +0.0005/ -0.0005

1

1.9050

1

i +0.0000 -0.0020

181 BlockAssy., Bearing2315151-6

16

1

K

2.6250

16

1

K,L

2.0610

1

1 +0.0010 -0.0000

19

1 Bearing-

B-545-22

I

(Alt. &545-DD) 20

Bellcrank- 2315151-4, -7

I

2.6250

+0.0005

+0.0010 -0.0000

I

1

-0.0005 +.0000

17

M

1.9050

i

1

18

M

1.9050

1

1

-0.0020

2315154-1

+.0000 -0.0020

231 521 6-1

19

M

1.9050

1

1

+.0000

-0.0020

211 Bearing-LS4

20

Control Column

EFFECTIVITY:

ALL

N

2.2500

0.7500

Assembly Allowable Wear and Repair Data Figure 1 (Sheet 5 of 7) 51-71-13

Page 5 SRM-4

Jun 6/98

Learjet t~j´•tl STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

EFF.

DESCRIPTION

1

Pin, Control Column Pivot2315152-9, -33

2

Block

4

Bearing MS27641 KP8A (Alt. AN201 KP8A) 1 Yoke Assy -2415152-1 (Alt. 2415152-3, -5) 2615270-1

10

MS20004H15 Bushing NAS75-4-015 Bushing NAS75-5-013 NAS77-5-50 Bushing NAS75-4-010 NAS77-4-27 Block Assy, Bearing 2415164-5 Bearing MS27640KP4

11

(Alt. MS20200KP4) Yoke Casting-2315153-32

6 7

8 9

12

1

Replacewompart.

1

A

1

A

Replace worn part. Replace worn part.

B

primer. Replacewornpart.

1

3

B

B, C

4

B

5

B

6

B

5

B

6

B

4

C

4

C

D, D, D, D, D, D,

7

2315153-40 2315153-41

10

9

2415152-&495 2415152-9-495 Bearing- MS27641KP6A

I

4

8

11

11

E

Replace Replace Replace Replace Replace Replace Replace Replace Replace primer. Replace Replace Replace Replace Replace

E

Replace worn

E

E E E

Install

new

bearing

with wet

part. part. part. part. part. part. Install

new

bearing

with wet

part. part. part. part. part. part. part. Install

new

bearing

with wet

Install

new

bearing with

worn

part.

worn

part. part.

worn worn

worn worn worn worn worn

worn

worn

worn worn

worn

1

D

1

E

12

F

Replace worn primer. Replace worn part. primer. Replace worn part.

2315153-28

13

2315153-5

14

G, H G, H

Replace worn part. Replace worn part.

14

15

Shaft, Main Control Wheel

1

A

2315153-716-2

(Alt. AN201 KP6A) Bearing- 8-539-ZZ (Alt. B-539-DD) Capstan Assy 2415160-3, -5,

13

1

2

Bolt

5

REPAIR

Assy, Bearing

2315152-6, -31 3

HOLE

-7

wet

(Alt. 2315153-49) 16

1

Shaft, Main Control Wheel 2615271-1

17 18 19

20

15

G, H

Torque Tube 2315151-2 Block Assy., Bearing 2315151-6 Bearing B-545-ZZ (Alt. B-545-DD)

16

I

Bellcrank

2315151-4, -7

2315154-1

2315216-1 21

Bearing

LS4

Control Column

16

J

16

K, L

17

M

18

M

19

M

20

N

Assembly Figure

EFFECTIVITY:

ALL

I

1

Replace worn Replaceworn Replace worn Replace worn

Replace worn part. Replace worn part. Repace worn part. Replace worn part.

Allowable Wear and

(Sheet

part. part. part. part.

6 of

Repair Data

7)

51-71-13

Pageb SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL CODES 1 2

EFFECTIVITIES 23-00 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29.001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 24-247 and Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-082 thru 25-360 and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 28-001 thru 28-005; 29-001 thru 29-003; 35-001 thru 35-487; 36-001 thru 36-050 25-361 and

5

Subsequent; 28-006 and Subsequent; 29-004 and Subsequent; 31-001 and Subsequent; Subsequent; 36-051 and Subsequent 24-247 and Subsequent and Prior Aircraft Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-082 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 24-247 and Subsequent; 25-187 and Subsequent; 28-001 thru 28-005; 29-001 thru 29-003; 35-018

6

thru 35-487; 36-009 thru 36-050 25-361 and Subsequent; 28-006 and

3

35-488 and

4

35-488 and

Subsequent;

Subsequent; Subsequent 24-109 Except

7

23-001 thru 23-099; 24-100 thru

8

proach Speed System" 24-210 thru 24-169 Except Aircraft Modified by 25-001 thru 25-081 Except Aircraft Modified by

9 10

11 12

13

14

29-004 and

Subsequent;

31-001 and

Subsequent;

36-051 and

Aircraft Modified

by AAK 76-04A, "Reduced Ap-

AAK 76-04A, "Reduced AAK 76-04A, "Reduced

Approach Speed System" Approach Speed System" 23-001 thru 23-099; 24-100 thru 24-109 When Modified by AAK 76-04A, "Reduced Approach Speed System"; 24-210 thru 24-169 When Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-001 thru 25-081 When Modified by AAK 76-04A, "Reduced Approach Speed System" 24-170 and Subsequent; 25-082 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 and Subsequent When Modified by A 2396003 Special Spares Kit; 24-100 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly" 23-001 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 and Subsequent When Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 35-018 thru 35-487; 35-500, 35-502, 35-503, 35-505, 35-509 thru 35-567; 36-009 thru 36-060 and Prior Aircraft With 2315153-49 Shaft

17

Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 24-100 and Subsequent Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 25-001 thru 25-081 Except Aircraft Modified by SSK 947A, "Replacement of Control Column Pulley and Shaft Assembly"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-488 thru 35-499, 35-501, 35-504, 35506 thru 35-508, 35-568 and Subsequent; 36-061 and Subsequent 23-001 thru 23-099; 24-100 thru 24-246 Except When Modified by AAK 76-04A, "Reduced Approach Speed System"; 25-001 thru 25-081 Except When Modified by AAK 76-04A, "Reduced Approach Speed System" 23-001 and Subsequent

18

24-100 thru 24-152; 25-001 thru 25-016

19

23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051, 23-060, 23-065, 23-087, 23-096;

15

16

23-001 and

24-153 and 20

23-001 and

Subsequent; 25-017 and Subsequent Subsequent Except 23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051,

23-060,23-065,23-087,23-096 NOTES:

Machined finish

Control Column

EFFECTIVITY:

ALL

Assembly Allowable Wear Figure 1 (Sheet 7 of 7)

and

Repair Data

1 51-71-13

Page SRM-4

7

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

24

CA

CL’ 25

i C’B

i7~---

cc

CA

2

CP

N 3

cc

4’

~n

7~

CC

CD3 Cc

4

3 S\

5

co

CD

cc

f

3~

CC

~..1

Detail N 2-19C 2-91A-3 2-7B1

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 1 of 24) 23-001 THRU 23-099

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-4

cc

3

’L

;\4 cc

Data

51-71-14

Page

1

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

_-d~

c?i.

CL 25

CF 7

CG

CG

M

7-CJ

8

CH

CJ

i 9

CJ

CH 9

cJ

Ed

5

cJ

ck 2-19C 2-7B1

EFFECTIVITY:

SRM-4

Detail M Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 2 of 24)

MODEL 24 AND 25 SERIES AIRCRAFT EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

51-71-14

Page 2 Jun 6/98

L~arjet Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

23

~g

a

,,,e

A CL’

12

D

11

Detai IA

Detail B H

17

A

I

cr~-

E

c~B D

i

’8~

F

´•-L

DetailC

DetailD M

21

J\

DetailE 2-7B1

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 3 of 24) ALL MODEL 31, 35 AND 36 SERIES AIRCRAET

WJTH 36-INCH PASSENGER/CREW DOOR SRM-I

DetailF

EQUIPPED

Data

51-71-14

Page 3 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

Q

27~

P

?8 29

26~

CR

U

CQ CP

CN

~ad

(23-001 thru 23-059 Eauitltled with 36-Inch Door. Excetlt Modified bu SSK 23-133. "Retllacement of Utlt~er Door Torsion Bay")

Detail Q 2-27c

I

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 4 of 24) NOTED

51-71-14

Page4 SRM-4

Jun 6/98

Learjet I

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

R

37

36 35

;X

42

CS

f

\1

CT

CV

33

39 40

CZ CY

CX

41

CW

with 36 Inch Door, Excetlt Modified by SSK 23-133, "Retllacement with 36-Inch Door, Excettt ModifJed of Ut~tter Door Torsion Bar": 24-100 thru 24-180 b; SSK23-133. "Retllacement of LIt~t7er Door Torsion Bar": 25-001 thru 25-024 Eauiotled with 36Inch Door, Excettt Modified by SSK 23-133, "Retllacement of Utlt~er Door Torsion Bar")

(23-060 thlrr 23-099

Detail R 2-36C

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 5 of 24) NOTED

51-71-14

Page5 SRM-(

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

G X

;U

s

Q ~B

’B

U

T 46

45

(23-060 thru 23-099 EauiPtled with 36-Inch Door and t~rior Aircraft Modified by SSK23-133, "ReDoor Torsion Bar": 24-181 and Subseauent Eauitlt~ed with 36-Inch Door and ttlacement of tlrior Aircraft Modified bu SK 23-133, "Retllacement of Utltler Door Torsion Bar": 25-025 and Subseauent

with 36-Inch Door and tltr’or Aircraft Modified bu SK 23-133, "Ret~Iacement of

Door Torsion Bar": All 28, 29 31, 35 and 36 Series Aircraft

with 36-Inch Door

Detail G BBIOC B4-6A C4-581

(EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 6 of 24) NOTED

51-71-14

Page6 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

B

r

58

DetailH 2-3C-1

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 7 of 24)

ALL AIRCRAFT

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-4

‘1

~59

Data

51-71-14

Page 7 Jun 6/98

6~ Learjet Learjetl STRUCTURAL REPAIR MANUAL PASSENGERICREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

K

AD

s3------IS leB AE

Detail J Passenger/Crew Upper Door Figure

IEFFECTIVI?Y: SRM-B

ALL AIRCRAFT

1

Allowable Wear and

Repair Data

(Sheet 8 of 24)

EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

51-71-14

Page 8 Jun 6/98

Learjet Learjetj

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

PASSENGER/CREW UPPER DOOR

A71

AM 13

AK

AJ AR

e,

!18 \AN

7q

AK72

AJ 74 68

736

AL

B

AN 69

68

AP

AR

71

70

AL

AG 75

68

\cl AR

as

74

DetailK

AQ

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 9 of 24) EFFECTIVITY:

ALL AIRCRAET

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-4

Data

51-71-14

Page 9 Tun 6/98

~9 Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

AY AZ

BA ED

BE BF

8~

81

s2

BG 82

"Gii-- BC

1’80

78

BE

AS AX

AU A

7s

AW

68

76

77

AS AT

I(O

se

BH BN

j

BQ

BJ

83

r.

BK

/s 78

85-----~\

BL

84

C"i--BR

BM 81

BP 86 Z1R

EFFECTIVITY:

87

sv/

Detail L

,I 87

BT

86

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 10 of 24) ALL AIRCRAFT

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-I

~les

51-71-14

Page

10

Tun 6/98

Learjet ~Leariet]

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

I

ITEM NO.

I DESCRIPTION

1

Plate-

2

Guide Assy. -103

EFF.

2311280-75,

-83

1

CA

MFD

MFD

HOLE

SHAFT

ID

OD

0.5100

I

+0.0100/

1

2311281-23

CC

0.6250

1

2311281-33

CC

0.6400

1

j

OD

WEAR ID

ALLOWANCE OD

+0.0080/ -0.0010 0.6250

0.6250

ALLOWANCE

ID

I CC

4

MFD

1

0.6250

CB

4

1 -82

I HOLE

4

2311280-77,

Plate-2311280-67,

3

I

+0.0080/ -0.0010

-0.0000

+0.0080/ -0.0010 +0.0080/ -0.0010

1 +0.0100/ -0.0100

4

1 GuideAssy.

-2311280-66

4

CB

0.51 00

0.6250

5

Plate, Striker-2311295-1,-2

2

CE

0.5310

6

Plate- 2311280-83

5

CF

0.6250

7

Guide Assy.

5

CG

0.5100

CH

0.6250

1

CH

0.6250

1

I CH

0.6400

CJ

0.5100

+0.0100/ -0.0000

+0.0080/ -0.0010

1 +0.0060/ -0.0010

1

1 +0.0080/ -0.0010

2311280-77,

1

-103

1

8

Plate- 2311280-82

I 5

2311281-23 2311281-33

0.6250

1

+0.0100/ -0.0000 1 +0.0080/ -0.0010

+0.0080/ -0.0010

1 +0.0080/ -0.0010 +0.0100/ -0.0100

1

9

GuideAssy. -2311280-66,

5

1

-88, -104

I

2411281-10 10

0.6250

I

I

+0.0100/

I

CJ

0.51 00

CK

0.6250

1

1 +0.0080/

2411281-23, -25

CK

0.6250

1

1 +0.0080/

2411281-33, -35

CK

0.6400

1

1 +0.0100/

A

0.6400

1

1 +0.0100/

Plate- 2311280-82, -111

5

0.6400

+0.0080/

1 +0.0100/ -0.0000

-0.0000

+0.0100/ -0.0100

-0.0010 -0.0010 -0.010

I

11

Plate-2411280-33

6

-0.0100 12

1

Guide, PlateAssy. 2411281-10

6

B

0.6400

1

1 +0.0100/

7

C

0.6250

1

1 +0.0080/

8

C

0.6400

1

1 +0.0100/

-0.0100 13

Plate- 2411281-25

-0.0010

2411281-35

-0.0100

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 11 of 24) EFFECTIVITY:

NOTED

Data

51-71-14( Page

SRM-a

11

Jun 6/98

Learjet I

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I HOLE

EFF.

DESCRIPTION

NO.

I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Guide, PlateAssy.

14

6

2411281-10

Plate- 2411281-34

15

10

1

D

0.6400

1

E

0.6400

1

1 +0.0100/ -0.0100 1 +0.0100/ -0.0100

16

Guide, PlateAssy.

1

2411281-10 17

1

Plate-2411281-23 2411281-33

6

F

0.6400

1

7

G

0.6400

1

9

G

0.6400

1

1 +0.0100/ -0.0100 1 +0.01001 -0.0100

1 +0.0100/ -0.0100

18

Guide, PlateAssy.

1

H

0.6400

1

1 +0.0100/

7

J

0.6400

1

1 +0.0100/

8

J

0.6400

1

1 +0.0100/

11

2411281-10

i

-0.0100

Plate- 2411281-23

19

-0.0100 2411281-33

-0.0100

Guide, Plate Assy.

20

2411281-10

6

K

0.6400

1

i +0.0100/

7

L

0.6400

1

1 +0.0100/

8

L

0.6400

1

1 +0.0100/

-0.0100 21

1

Plate-2411281-24

-0.0100 2411281-34

-0.0100

Guide, Plate Assy.

22

6

2411281-10

M

0.6400

1

1 +0.0100/ -0.0100

23

1

Hinge, Half-Fuselage 2311280-19, -98, -108

2

CL

0.0700

1

1 +0.0000/ -0.0050

24

Hinge, Half- Fuselage 2411283-3, -8, -11,-014

25

Hinge,

3

CL

0.0700

1

1 +0.00001 -0.0050

2

CL

0.0700

1

1 +0.0000/

Half- Door

241 1 280-20

-0.0050 26

1 Hinge,

Half-Door

2411283-2, -6, -10, -013

3

CL

0.0700

1

1 +0.00001 -0.0050

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 12 of 24)

I

EFFECTIVITY:

NOTED

Data

51-71-14

Page SRM-4

12

Tun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

EFF.

Link-2311492-15

26

I

I HOLE I

12

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

CM

0.2500

1

1 +0.0050/

CN

0.3160

1

1 +0.0010/

OD

WEAR ID

ALLOWANCE OD

-0.0010 -0.0090 27

Pin, Clevis- MS20392-3C17

12

28

Link-2311492-21,

12

29

Plate Guide

30

PlateBearing

-22

CM

1

I

1

0.2480

+0.0000/ -0.0020

CM

0.2500

1

1 +0.0050/

12

CP

0.3750

1

1 +0.0060/

12

CQ

0.3750

1

1 +0.0060/

CR

0.5000

1

1 +0.0060/

-0.0010 2311492-10

-0.0000 -2311492-17

-0.0000 31

1

Doubler-2311492-19

32

1

FittingAssy.

12

1

-0.0000

2311280-63, -64

12

1

CN

I

1

0.3140

1

1 +0.0000/ -0.0050

Link, Lwr, Torsion Bar Arm

33

2311688-14

13

1

CS

0.2500

1

1 +0.0050/

CZ

0.3160

1

1 +0.0010/

-0.0010 -0.0090 34

Pin, Clevis- MS203923C17

35

Arm

36

13

CS

13

CT

0.4125

1

1 +0.0020/

Spacer- NAS43HT7-18

13

CU

0.4600

1

37

Plate

13

CV

0.4690

1

1 +0.0300/ -0.0200 1 +0.0060/ -0.0010

38

Torsion Bar-231168&1

13

CU

39

Angle, Torque Adj. Support

I

0.2480

1

1 +0.0000/ -0.0020

Assy.

-231168&8

-0.0000

Bearing -2311688-13

I

1

0.3750

1

1 +0.0060/ -0.0000

2311688-6, -7

13

CW

13

1 CW

13

CX

0.1890

1

1 +0.00501 -0.0000

Bolt- MS20073-03-12

40

I

1

0.1890

1

1 +0.00001 -0.0030

41

1

Plate

Bearing-2311688-9

0.5020

1

1 +0.0050/ -0.0000

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 13 of 24) EFFECTIVITY:

NOTED

Data

51-71-14

Page SRM-I

13

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM i

I

NO.

I EFF.

DESCRIPTION

HOLE

Link, Upper- 2311688-3, -181 13

42

I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD

ALLOWANCE

ID

CY

0.4125

1

1 +0.0020/

CS

0.2500

1

-0.0000 1 +0.0050/

OD

WEAR ID

ALLOWANCE OD

-0.0010

Bushing- DBS-7-030 (Alt- AJ07C-125) Support, Torsion Bar

43 44

Link- 2411682-1, -5, -6, 14 -17, -18, -27, -28, -31,-32 1

Link

45

N

11

N

i

0.4300

1

I

1 +0.0090/ 1 -0.0000

1

I

I

Assy., Lower Arm

2411681-1

24

N

0.4690

1

1 +0.0060/

2411681-15, -21

25

N

0.6259

1

1 +0.0000/

45A

Bushing- DBS-7-30 (Alt. AJ07C-030)

24

N

46

Pin, Clevis-MS20392-3C17

14

P, Q

47

Link, Upper Torsion BarArm -2311688-3,-16, 14 -17,-18 1

-0.0010

-0.0005

I

1

0.2480

1

1 +0.0000/ -0.0020

48

Arm

49

Angle, Torsion Bar-

Assy.

2311688-8

0.2500

Q

I

I R

14

0.4125

1

1 +0.0050/

I

1 -0.0010

1

1 +0.0020/ -0.0000

2311688-7

Bolt- NAS1003-12H

50

14

1

S

14

1

S

0.1890

I

1 +0.0050/ -0.0000

1

1

0.1880

1

1 +0.0015/ -0.0010

51

1

Plate,Bearing2311688-9

52

1 Spacer-NAS43HT7-18

14

T

0.5020

14

U

0.4650

i 0.5600

53

Plate, Bearing-231168&13

14

V

54

Bar, Torsion- 2311688-1

14

T, U, V,W

I

1

I

I

X

I

1

0.4390

1 +0.0050/

1

-0.0000 +0.0250/

+0.0180/

-0.0250

-0.0120

1 +0.0050/ -0.0000

55

1

Bolt-NAS1003-12H

14

1

0.4375 0.1880

1

1

I

1 -0.0020

1

1 +0.0015/

+0.0000/

-0.0010 56

Angle, Torsion Bar2311688-6, -7

14

X

0.1890

1

I c0.0050/ -0.0010

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 14 of 24)

)EFFECTIVITY:

NOTED

51-71-14

Page sRM-4

14

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I

I

I

I HOLE I

EFF.

DESCRIPTION

57

Plate- 2311271-17

58

Guide Assy., Pin 2311271-12

Y

1

MFD

MFD

HOLE

SHAFT

ID

I

0.4950

1

OD

I MFD I

WEAR

ALLOWANCE

ID

OD

I

ID

ALLOWANCE OD

1 +0.0050/ -0.0000

59

1

62

63

0.4950

1

1 +0.0050/ -0.0000

1

AA

0.4950

1

1 +0.00501 -0.0000

0.4950

1

1 +0.0050/

I

1 -0.0000

1

1 +0.0050/ -0.0000

1 GuideAssy. 2311276-1, -2, -5, -6, -9, -10

61

Z

1 GuideAssy. 2311279-1, -2

60

1

1

64

65

AB

1

1

I

I

HingeArm-231127&3

1

AC

Bolt- AN4-27A

1

AD,

I

1

1

1 +0.0010/

AE

I

I

I

1 -0.0020

1 +0.0050/

0.4950

Guide-2311502-4,-12

1

AD

0.2500

1

Clevis- 2311502-5, -11,-17

1

AE

0.2500

1

AF

0.3117

1

Bolt- NAS464P5A12

1

AF

SupportAssy. -2311495-28,

1

AG

I

0.2480

-0.0010 1 +0.0050/ -0.0010 1 +0.0010/ +0.0000

1

0.3117

1

1 +0.0000/ -0.0009

66

1

1

-69, -134 67

Bearing,

I

1

1 +0.01001

I

1

-0.0100

ThrustAH

1

2411515-1

68

I

1.0100

1.2000

2.1800

+0.0300/

+0.0300/

-0.0300

-0.0300

Control Rod Assy. 15

2311288-1

1

AJ

1.0100

1

1+0.0050/ -0.0050

AK

0.1890

1

AS

0.1880

1

+0.0300/ -0.0300

1 +0.0100/ -0.0100 1 +0.0050/ -0.0010

Quadrant Assy. 16

2411513-1

AJ

1

1.0100

i

1+0.0050/ -0.0050

AK

0.1890

1

1 +0.0100/

AS

0.1880

1

1 +0.0050/

+0.0300/ -0.0300

-0.0100 -0.0010

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 15 of 24) EFFECTIVITY:

NOTED

51-71-141 Page

SRM-I

15

Jun 6/98

Learjet Ledrjet/ STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I DESCRIPTION

NO.

I HOLE I

IEFF.

Bolt- 2311490-8

69

I

I

HOLE ID

MFD

MFD

ALLOWANCE

WEAR

ALLOWANCE

SHAFT I

OD

ID

OD

17

AK

I

1

0.1894

1

1 +0.00001

16

AK

i

1

0.1894

1

1 +0.00001

18

1 AL,

1

0.1860

1

1 +0.0000/

I

1 -0.0020

1 I

1 +0.0000/ 1 -0.0020

ID

OD

-0.0009

2311490-12, -13

-0.0009

Pin,Clevis-AN23-34A

70

AM,

I

I

I I

1 I

AN

MS20392-2C63

AL, AM,

19

0.1860

AN 71

1

HandleAssy.,Outer2311286-3, -6, -9

20

AL

0.2504

1

2411286-1, -3

21

AL

0.2504

1

1

AM

0.2140

1 +0.0005/ -0.0000 1 +0.0005/ -0.0000

72

Spacer, NAS43DD3-26,

-22

0.3120

+0.0200/ -0.0200

73

Cover Assy., Outer Handle- 2311287-3

AN

18

0.1880

1

+0.0100/ -0.0100

1 +0.0100/ -0.0100

AP

2311287-4, -7 2411287-2, -3, -4

0.1880

I

1

0.8600

1

I AP

i

1

0.8600

AP

I

1

0.1890

I

1

0.8450

73A

Bolt- NAS221-28

18

738

Plug, Handle-

18

CZ

74

Tube Handle 2311491-19

17

AR

2311491-5

1

AN

19

1

I

AQ

0.1890

I

1

1

1

1 +0.0000/ -0.0050

1 +0.0100/ 1 -0.0100 1 1 +0.0000/ -0.0050 1 1 +0.0000/ -0.0009 1 1 +0.0050/ -0.0050 1 +0.0000/ -0.0010

1.0000

1

1 +0.0300/ -0.0300

2411491-14

18

AR

0.1890

1 +0.0000/

1

-0.0010

AQ

I

1

1.0000

1

1 +0.0300/ -0.0300

2411516-1, -2, -3

16

AR

AQ

0.1890

I

1 +0.0000/ -0.0010

1

1

1.0000

1

1 +0.0300/ -0.0300

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 16 of 24)

I

EFFlECTIVITY:

NOTED

51-71-14

Page SRM-4

16

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I

I

I

HOLE

MFD

MfD

ALLOWANCE

WEAR

ALLOWANCE

I SHAFT

NO.I

DESCRIPTION

EFF.

HOLEI

ID

75

Bolt- NAS221-23

17

AR

I

I

NAS464 P3A1 9

16

AR

I

OD

I

0.1890

1

1+0.0000/

1 0.1894

1

1+0.0000/

ID

OD

I

ID

OD

-0.0009

-0.0009 76

Pushrod

Assy.,

Pin 1

231149&1,3

77

Pin-2311491-18

1

AT

0.1900

1

1+0.0020/ -0.0000

AU

0.1900

1

1+0.00201

AV

0.1880

1

-0.0000 1+0.0050/ -0.0010

AW

I

1

0.4850

1

1+0.0000/ -0.0050

78

Rod

Assy.

2311494-1

22

AX AY

2311490V1-004

23

AX AY

79

1 ArmAssy.,Rocker2311277-1

1

AZ

0.1880

1

1 +0.0100/

BA

0.1880

1

BE

0.1880

1

BC

0.2504

1

1+0.0100/ -0.0100 1 +0.0100/ -0.0100 1+0.0005/ -0.0000

-0.0100

80

1 Pin,ClevisMS20392-2C25

1

BC

I

1

0.2480

1

1+0.0000/ -0.0002

81

1 PushrodAssy.,Pin2311496-5, -7, -9

2311490V1-002

22

23

ED

0.1900

1

BE

0.1900

1

ED

0.1900

1

1+0.0020/ -0.0000 1+0.0020/ -0.0000 1+0.0020/

BE

0.1900

1

1+0.0020/

BF

0.1880

1

1+0.0050/ -0.0010

1 0.4850

1

-0.0000

-0.0000 82

Pin- 2311491-17

1

BG

I

1+0.0000/ -0.0050

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 17 of 24) EFFECTIVITY:

NOTED

51-n-14/ Page

SRM-I

17

Jun 6/98

E~ Learjet Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO. 83

I

1

Pushrod

I

MFD

MFD

HOLE

SHAFT OD

ID

MFD

OD

ID

EFF.

HOLE

1

BH

0.1900 1

I

+0

BJ

0.1900 1

I

+0

WEAR

ALLOWANCE I

ID

ALLOWANCE OD

Pin

Assy.,

2311497-1, -3

-0.0000 -0.0000

Bellcrank

84

Assy.,

Fwd 1

2311284-1

BK

0.1880 1

1

+0.01

BL

0.3754 1

I

+0.

BM

0.1880 1

1

+0.01 -0.0100

BN

0.1880 1

1

BP

0.1880 1

1

+0.01 -0.0100 +0.01 -0.0100

BQ

0.1890 1

I

+0

BR

0.3754 1

I

+0

BS

0.2504 1

I

+0

-0.0100 -0.0000

85

1

Bellcrank

Assy., Aft 1

2311283-1, -3, -5

-0.0010 -0.0000

Link

86

Assy.,

Lwr Pins

1

1

2311491-1

I

I

1

-0.0000

BT

I

0.2504 1

I

+0.

BU

0.1880

-0.0000

Pin-2311491-16

87

1

-0.0010 BV

I

1

0.4850 1

I

+0 -0.0050

88

1

Pin, ClevisMS20392-2C17

1

AS, AU, AX, AZ, BE, BE,

AT,I AV~

1 I

0.1860

1 I

0.1860

1 I

I 1

+0.

I 1

+0

-0.0020

AY ED BF

BH

89

1

Pin, ClevisMS20392-2C21

1

BJ, BK,( BM, BN1 BP, BS BT, BU

I

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 18 of 24)

1EFFECTIVITY:

NOTED

-0.0020

Data

51-71-14

Page 18 SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

4

Plate 2311280-75, -83 Guide Assy. 2311280-77, -103 Plate 2311280-67, -82 2311281-23 2311281-33 Guide Assy. 2311280-66

5

Plate, Striker 231 1295-1,

6

Plate

7

Guide Assy. 2311280-77, -103 Plate 2311280-82 2311281-23 2311281-33 Guide Assy. 2311280-66, -88, -104 2411281-10 Plate-2311280-82, -111

1

2 3

8

9

10

1

-2

8

J

6

K

7 8

L L

6

M

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replacewompart. Replace worn part. Rep\acewompart. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

2

CL

Replace worn part.

3

CL CL

Replace worn Replace worn Replace worn Replace worn

4

CA

4

CA

4

CC CC

6

CC CB CE CF CG CH CH CH CJ CJ CH CH CH A B

7

C

8 6

C D

10

E

4 2

5

2311280-83

5 5

5 5

2311281-23, -25 2311281-33, -35

1 6

2411281-33

11

Plate

12

Guide, Plate Assy.

13

Plate

14

2411821-35 Guide, Plate Assy.

2411281-10

2411821-25 2411281-10

2411281-34

15

Plate

16

Guide, Plate Assy. 2411281-10

6

F

17

Plate 2411281-23 241128133

7

9

G G

18

Guide, Plate Assy. 2411281-10

11

H

19

Plate

7

J

2411281-23

22

241128133 Guide, Plate Assy. 2411281-10 Plate 2411281-24 241128134 Guide, Plate Assy. 2411281-10

23

Hinge Half, Fuselage

24

Hinge Half, Fuselage

25

Hinge Half, Door

26

Link

27

28

Pin,Clevis- MS20392-3C17 Link 2311492-21, -22

29

Plate Guide

30

Plate

20 21

REPAIR

EFF. IHOLE

DESCRIPTION

NO.

2311280-19, -98, -108

2411280-3, -8, -11, -104 2411280-20

241 1 283-2, -6, -10, -01 3

2311492-15

2

3

CL

12

CM,

12

CM

12

CM

I I

part. part. part. part.

CN

Bearing

2311492-10 2311492-17

12

CP

12

CQ

Replacewompart. Replace worn part. Replace worn part. Replace worn part.

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 19 of 24) EFFECTIVITY:

NOTED

51-71-141 Page 19

sRM-a

Jun 6/98

Leariet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM NO. 31

Doubler

2311492-19

12

32

Fitting Assy. 2311280-63, -64 Link, Lower Torsion Bar Arm

12

CR CN

13

CS, CZ

13

CS

38

2311688-14 MS20392-3C17 Arm Assy. 2311688-8 Spacer NAS43H57-18 Plate Bearing 231168&13 Torsion Bar 2311688-1

39

Angle, Torque Adj. Support

40

Bolt

33 34 35 36 37

Pin, Clevis

42

MS20073-03-12 Plate Bearing 2311688-9 Link, Upper- 2311688-1, -18

43

Bushing

41

13

CT

13

CU

13

CV CU

13

CW CW

13

2311688-6, -7

13

DBS-7-030

REPAIR

HOLE

EFF.

DESCRIPTION

I

13

CX

13

ICY,CSJ

1

N

Replace worn part. Replace worn part. Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Rep\acewompart. Replace worn part.

44

(Alt. AJ07C-125) Support, Torsion Bar Link

45

2411682-1,-5, -6, -17, -18, -27, -28, 31,-32 Link Assy., Lower Arm,

14

N

Replace worn part.

2411681-21

24

N

2411681-15, -21

25

N

Bushing DBS-7-30

24

N

Replace worn part. Replace worn part. Replace worn part.

14

P,Q

Replace worn part.

47

(Alt. AJ07C-030) Pin, Clevis MS20392-3C17 Link, Upper Torsion Bar Arm 2311688-3, -16, -17, -18

48

Arm

45A 46

1

14

Q

Assy. 231168&8 Angle, Torsion Bar 231168&7

14

R

14

S

14

S

14

T

14

U

54

NAS1003-12H Plate, Bearing 23116889 Spacer NAS43H17-18 Plate, Bearing 231168&13 Bar, Torsion 2311688-1

55

Bolt

56

Angle, Torsion Bar 2311688-6,

57

Plate 2311271-17 Guide Assy., Pin 2311271-12

49

50 51 52 53

58 59 60

Bolt

NAS1003-12H

Guide Assy. Guide Assy.

Install

new

bushing with

Loctite.

-7

14

V

14

T, U, V, W

14

X

14

X

1

Y

1

Z

2311279-1, -2

1

AA

2311276-1, -2, -5,

1

AB

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part. part.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

-6,-9,-10

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 20 o~ 24)

(EFFECTIVITY:

NOTED

51-71-14

Page 20 SRM-4

Jun 6/98

Learjet ~Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESC RI PTION

NO.

Arm

231127&3

EFF.

IHOLE

1

AC

1

AD, AE

61

Hinge,

62

Bolt

63

1

AD

1

AE, AF

65

Guide 2311502-4, -12 Clevis 2311502-5, -11, -17 Bolt NAS464P5A12

1

AF

66

Support Assy. 2311495-28, -69,

1

AG

64

AN4-27A

REPAIR

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

-134

Bearing, Thrust 2411515-1 Control Rod Assy. 2311288-1

67 68

1

AH

15

AJ, AK,

16

IAJ,AK,

Replace worn part. Replace worn part.

AS

Quadrant

Assy.

2411513-1

Replace worn part.

AS

Bolt Bolt

69

2311490-8

17

AK

2311490-12, -13

16

AK

18

AL,AM,I

19

IAL,AM,I

Pin, Clevis- AN23-34A

70

Replace worn part. Replace worn part. Replaceworn part.

AN

MS20392-2C63

Replacewompart.

AN 71

1

Handle

Assy., Outer

2311286-1,-3, -9 2411286-1,3 Spacer NAS43DD3-22, -26

72

Cover Assy., Outer Handle 2311287-3

73

2311287-4, -7 2411287-2,-3,-4

20

AL

21

AL AM

Replace worn part. Replace worn part. Replace worn part.

19

AN,AP AN,AP

Replace worn part. Replace worn part.

1

18

73A

Bolt

NAS221-28

18

AP

738

Plug,

Handle

18

CZ

17

2311491-5

2411491-14

18

2411516-1,-2, -3

16

AQ, ARI AQ, ARI AQ, ARI

17

AR

Tube, Handle -2311491-19

74

75

Bolt

76 77

NAS464P3A219 Pushrod Assy., Pin Pin -2311491-18

78

Rod

79

2311490V1-004 ArmAssy., Rocker-2311277-1

1

NAS221-23

Assy.

80

Pin, Clevis

81

Pushrod

2311494-1

MS20392-2C25

Assy.,

AR

1

AT, AU

1

AV,AWI

22

AX, AY AX, AY AZ, BA,I BE, BC

23 1

part. part. part. part. part. part. part. part. part. part. part.

part.

1

BC

Replace worn part.

22

ED, BE ED, BE BF, BG

Replace worn part. Replace worn part. Replace worn part.

Pin

2311496-5, -7, -9 82

2311498-1, -3

16

Replace worn Replace worn Replaceworn Replaceworn Replaceworn Replace worn Replace worn Replace worn Replaceworn Replace worn Replace worn Replaceworn

2311490V1-002 Pin 2311491-17

23 1

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 21 of 24) EFFECTIVITY:

NOTED

51-71-14

Page 21 SRM-I

Jun 6/98

1

Leariet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

Pushrod Assy., Pin 2311497-1, -3 Bellcrank Assy., Fwd 2311284-1

83 84

EFF.

HOLE

1

BH, BJ BK, BL,

1

REPAIR

Replace worn part. Replace worn part.

BM 85

j

Bellcrank Assy., Aft

1

-5

Link Assy., Lwr Pins 2311491-1 Pin -2311491-16 Pin, Clevis- MS20392-2C17

86 87 88

1

2311283-1, -3,

1

1 1

BN, BP,I I BQ, BR BS, BT BU, BV

AS,AT,I

Replacewompart. Replace worn part. Replace worn part. Replaceworn part.

AU, AV AX, AY AZ, BE, ED BE, BF BH 89

1

Pin, Clevis

MS20392-2C21

1

BJ, BK, BM, BP,BS, BT, BU

Replace worn part.

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 22 of 24)

(EFFECTNITY:

NOTED

51-71-14

Page 22 SRM-I

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES NOTE:

The

following effectivities

are

applicable provided

Aircraft is Eauiooed with 36-inch Pas-

senger/Crew Door 29-

Subsequent; Subsequent

2

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28001 and 001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and 23-001 thru 23-099; 24-100 thru 24-229; 25001 thru 25-066, Except 25-061

3

24-230 and

Subsequent; 25-061,25-067 and Subsequent; 2&001 and Subsequent; sequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

29-001 and Sub-

4

23-001 thru 23-099

5

24-100 thru 24-229; 25-001 thru 25-066, Except 25-061 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and 35-001 thru 35-051; 36-001 thru 36-016 31-001 and Subsequent; 35-052 and Subsequent; 36-017 and

1

6 7 8 9 10 11

12 13

14

15

16

Subsequent Subsequent

35-052 thru 35-510; 36-017 thru 36-053 31-001 and Subsequent; 35-511 and Subsequent; 36-054 and Subsequent 35-001 thru 35-510; 36-001 thru 36-053 23-001 thru 23-059, Except Aircraft Modified by SSK 23-133, "Replacement of

Upper Door Torsion

Bar" 23-060 thru 23-099, Except Aircraft Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; 24-100 thru 24-180, Except Aircraft Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; 25-001 thru 25-024, Except Aircraft Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar" 23-060 thru 23-099 When Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; 24180 and Subsequent and Prior Aircraft Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; 25-025 and Subsequent and Prior Aircraft Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099 Except Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 24-100 thru 24-356 Except Aircraft Modified by AMK 76-02, "Replacement of Door Handle Mechanism"; 25001 thru 25-238 Except Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism";35-001 thru 35-167 Except Aircraft Modified by AMK 78-02, "Replacement of Door

Handle Mechanism"; 36-001 thru 36-038 Except Aircraft Modified by AMK 7&02, "Replacement of Door Handle Mechanism" 23-001 thru 23-099 When Modified by AMK 7&02, "Replacement of Door Handle Mechanism"; 24357 and Subsequent and Prior Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 25-239 and Subsequent and Prior Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-168 and Subsequent and Prior Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 36-039 and Subsequent and Prior Aircraft Modified by AMK 7&02. "Replacement of Door Handle Mechanism"

17

Subsequent and Prior Aircraft Modified by SSK 23-114, "Upper Door Handle ReplaceExcept When Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 24-100 thru 24356 Except When Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 25-001 thru 25-238 Except Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 35001 thru 35-167 Except Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mechanism"; 36-001 thru 36-038 Except Aircraft Modified by AMK 78-02, "Replacement of Door Handle Mecha23-050 and ment"

18

nism" 23-001 thru 23-049

Except

Except Aircraft Modified by SSK 23-114, "Upper Door Handle Replacement" by AMK 78-02, "Replacement of Door Handle Mechanism"

Passenger/Crew Upper Door Figure EFFECTIVITY:

ALL AIRCRAFT

Allowable Wear and

Repair

Data

1 (Sheet 23 of 24)

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-4

and

When Modified

51-71-14

Page 23 Jun 6/98

I

Learjet STRUCTURAL REPAIR MANUAL CODES 19

EFFECTIVITIES 23-050 and

Subsequent

and Prior Aircraft Modified by SSK 23-114, "Upper Door Handle Replaceby AMK 7802, "Replacement of Door Handle Mechanism"; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent ment" and/or Modified

20 21

23-001 thru 23-099; 24-100 thru 24-241 24-242 and Subsequent and Prior Aircraft

2411287

28-001 and

and

Subsequent; 36-001 and Subsequent

22

29-001 and

31-119 and

24

23-001 thru 23-099 When Modified

25-001 and

35-001 and

Subsequent; Subsequent;

Subsequent

by SSK 23/24/25-321, "Upper Door Torsion Bar Linkage Replaceby AMK 71-06A, "Upper Door Torsion Bar Linkage Replacement", or AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links"; 24-181 thru 24-241 Except Aircraft Modified by AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links", and Prior Aircraft Modified by SSK 23/24/25-321, "Upper Door Torsion Bar Linkage Replacement", Except Aircraft Modified by AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links"; 25-025 thru 25-077 Except When Modified by AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links", and Prior Aircraft Modified by SSK 23/24/25-321, "Upper Door Torsion Bar Linkage Replacement" Except When Modified by AMK 71-06A, "Upper Door Torsion Bar Linkage Replacement" 23-001 thru 23-099 When Modified by SSK 23-133, "Replacement of Upper Door Torsion Bar"; AMK 71-06A, "Upper Door Torsion Bar Linkage Replacement", or AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links"; 24-242 and Subsequent and Prior Aircraft Modified by AMK 71-06A, "Upper Door Torsion Bar Linkage Replacement"; 25078 and Subsequent and Prior Aircraft Modified by AMK 71-06A, Upper Door Torsion Bar Linkage Replacement, or AMK 71-05, "lnstallation of Anti-Friction Bushing in Upper Cabin Door Torsion Bar Links"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent ment"

I

Handle;

Subsequent;

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 thru 31-118; 35-001 and Subsequent; 36-001 and Subsequent

23

25

Equipped With Subsequent; 31-001

Except When

Modified

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 24 of 24)

I""""": sRM-4

ALL AIRCRAFT

EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

51-71-14

Page 24 jun 6/98

Learjet I

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

12

H D 8.\

I

E

YI

E

D

~10

C

8

7

11

F

AI5 B

9E

C

8

C

AQ

n´•p-/B

~e, 2A

(TYPICAL)

Detail A

AR 2-14C

Passenger/Crew Lower Door

Allowable Wear and

Repair Data

Figure 1(Sheet 1 of 13) EFFECTIVITY:

ALL AIRCRAFT

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-I

51-71-15

Page

1

Tun 6/98

Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

16

N

,13

L

14

M

17

15

i’

B

R

H

18

S T

L 15

,13

16

"N~-n

14

19

K

20 S

PR Detail B

2-14C 2-s5c

IEPPEC’IIYITY: SRM-I

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 2 of 13) ALL AIRCRAFT

EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

51-71-15

Page 2 Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

AF 31

AE

t

30

no~

V

CAB

AB

AC 23

U (P

X\y

32

2~A

28

29

‘22

Z

W 25 24

Detail C 2-16C-1

EFFECTIVITY:

SRM-4

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 3 of 13) ALL AIRCRAFT

EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

51-71-15

Page 3 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

AL

AH

AK

AJ

34

AG

Detail D 2-8C

EFFECTIVITY:

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 4 of 13) ALL AIRCRAFT

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-I

51-71-15

Page 4 Tun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

42

AQ

\44

E =s=

i;’

39

M

AM

AP

AN 39

pb

(TYPICAL)

AM

Detail E 2-15C-2

EFFECTIVITY:

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 5 of 13) ALL AIRCRAET

EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR SRM-I

51-71-15

Page 5 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I DESCRIPTION

I

I

MFD

MFD

HOLE

SHAFT

IEFF.

HOLE

ID

I

1

1

Plate-2311271-17

1

A

0.4950

2

Housing- 2311291-2

2

AQ

0.6250

Bolt- 2311291-3

2

AR

0.5000

MFD

OD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00501 -0.0000

2A

1

1 +0.00061 -0.0000

Guide

3

Assy.,

Pin

2511278-1

3

B

1

A,B

0.5050

1

1 +0.0050/ -0.0000

Pin, Door- 2311291-6

4

j

1

1 +0.0100/

0.4850

-0.0000 C

0.1880

1

1 +0.0050/ -0.0010

Pin, Clevis-

5

MS20392-2C17

TurnbuckleAN165H32LS

6

1

C,D, I E,F, I

1 0.1860 1 I I

1 +0.0000/ 1 -0.0020

22

D

0.1900

1

1 +0.0020/

23

D

0.1900

1

1 +0.0020/

-0.0000

2411242-1

-0.0000

TurnbuckleAN165H32RS

7

22

E

0.1900

1

1 +0.0020/

23

E

0.1900

1

1 +0.0020/

1

D, E

2311293-1

4

F

0.1880

1

1 +0.0050/

2411224-1

5

F

0.1880

1

1 +0.0050/

-0.0000 2411242-2

-0.0000 8

Bushing- AA226-1

9

Crank, Lower Door-0.0010 -0.0010

10

1

Pin, Door,Aft2311491-16

1

G

0.1880

1

1 +0.00501 -0.0010

H,J

I

1

0.4850

1

1 +0.0000/ -0.0050

11

I GuideAssy.,

Pin-

2311271-12

1

H

0.6310

1

1 +0.0000/

1

J

0.4950

1

1 +0.00501

-0.0050 12

Plate- 2311271-17

131

PanAssy.

-0.0000 2311229-2

6

K

0.4380

1

1 +0.0060/ -0.0010

Passenger/Crew Lower Door Allowable Wear and Repair Figure 1 (Sheet 6 of 13)

IEFFECTNITI: SRM-I

NO~D

Data

51-71-15

Page6 Tun 6/98

Learjet I Leariet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I

I

I

I

MFD

MFD

HOLE

SHAFT OD

MFD

ALLOWANCE

DESCRIPTION

EFF.

HOLE

ID

2311300-1

7

K

0.4380

i

1 +0.0060/

2381 403-2

8

K

0.6600

1

2411221-1

9

K

0.6600

1

2411221-3, -6

10

K

0.6600

1

1 +0.03001 -0.0300 1 +0.0300/ -0.0300 1 +0.0300/ -0.0300

ID

OD

WEAR I

ID

ALLOWANCE OD

-0.0010

141 Bushing-2411223-2

1

K

1

I

1

0.6200

1

1 +0.0300/ -0.0300

L

0.5030

1

1 +0.001 0/

M

0.3800

1

N

0.1400

1

1 +0.0300/ -0.0000 1 +0.0100/

-0.0000

151 Bushing-2311340-5

11

-0.0100 16

17

1

Pin, Spring- NAS561 P4-8 (Alt. NAS561 P4-1 0)

11

Shaft, Handle-2311302-1

12

N,P

I

I

1

I P

0.1250

1

1 +0.0040/

I

I

1

1

1 +0.0050/

0.1310

-0.0000

-0.0000

Q

I

1

0.3700

1

1 +0.0020/ -0.0000

R

0.1890

1

1 +0.0050/

P

0.1250

1

1 +0.0050/ -0.0000

-0.0010 11

24112236

I

Q

i

1

0.3700

1

1 +0.0020/ -0.0000

R 18

Bolt- NAS464P3A16

4

R,S

19

Pin, Clevis- MS20392-2C55

5

R,S

20

Bushing- NAS77-3-31

5

S

0.1900

1 +0.0010/ -0.0000

1

1

0.1894

1

1 +0.00001

0.1880

1

1 +0.0000/

-0.0009

I

-0.0020 0.1900

1

1 +0.0015/ -0.0000

T

I

i

0.3136

1

1 +0.0000/ -0.0005

211 HandleAssy. 2311301-11, -15

4

2411222-1

5

(Alt. 2411222-2)

1

T

0.1890

1

1 +0.0050/ -0.0010

T

0.3121

i

1 +0.0005/

I

1

-0.0000

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 7 of 13) EFFECTIVITY:

NOTED

51-71-15

Page 7 SRM-Q

Jun 6/98

1

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO.

I DESCRIPTION Block Assy., Bearing, Fwd- 2311305-3, -9, -23

22

Block

23

I

I

MFD

MFD

HOLE

SHAFT OD

MFD

WEAR

ALLOWANCE

EFF.

HOLE

ID

1

U

1.0000

i

1 +0.00051 -0.0005

1

V

1.0000

1

1 +0.00051 -0.0005

1

W

0.6870

1

1 +0.0030/

ID

OD

I

ID

ALLOWANCE OD

Assy., Bearing, Aft

2311305-4, -10, -24 Plate, Retaining-

24

2311309-2

-0.0030 25

1

Eccentric, Fwd2311306-1, -2

13

IWI

1

0.6200

1

1 +0.0100/ -0.0100

14

2481108-1

X

0.1880

1

Y

0.5000

1

IWI

1 +0.0050/ -0.0010 1 +0.0060/ -0.0000

1

0.6200

1

1 +0.0100/ -0.0100

X

0.1880

1

0.5000

1

1 +0.0050/ -0.0010 1 +0.0060/

Y

i

W

I

X

1

0.1880

1

1 +0.0050/

Y

1

0.5000

1

1 +0.0060/

W

I

-0.0000 15

2311306-3

1

0.6200

1

1 +0.0100/ -0.0100 -0.0010 -0.0000

16

2311306-4

1

0.6200

1

i +0.0100/ -0.0100

X

0.1880

i

1 +0.0050/

Y

0.5000

1

1 +0.0060/ -0.0000

-0.0010

26

Pin, Clevis- MS20392-2C31

17

X,Z

I

1

0.1860

1

1 +0.0000/

18

X,Z

I

1

0.1860

1

1 +0.0000/

1

Y

I

1

0.4900

1

1 +0.0050/

-0.0020 HL1 &6-14

-0.0020 27

1 Plug,

Fwd-2311305-11

-0.0000 Z

0.1880

1

1 +0.0050/

AA

0.2492

1

1 +0.00101 -0.0000

-0.0010

Passenger/Crew

Lower Door

Figure

I

EFFECTIV~I"Y:

NOTED

1

Allowable Wear and

Repair Data

(Sheet 8 of 13)

51-71-15

Page8 SRM-I

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I HOLE I

EFF.

DESCRIPTION

NO.

I

28

Tube, Torque- 2311305-22

1

29 1

Bolt-NAS4~4P4-15

1

AB

1 Plug, Aft-2311305-11,-26

19

Eccentric, Aft-2311307-1

21

22

2311307-2

MFD

I

0.2492

1

1 +0.001 01 -0.0000

1 0.2492

1

1 +0.0000/

I

I

1 -0.0009

1 +0.001 0/

I 0.2492

1

AD

0.1880

1

OD

ID

I

OD

AE

0.5000

1

AF

0.1880

1

AE

0.5000

1

-0.0000 1 +0.0050/ -0.0010 1 1 +0.0050/ -0.0000 1 +0.0060/ -0.0010 1 +0.0050/ -0.0010 1 +0.0060/

AF

0.1880

1

1 +0.0050/

I

1

0.4900

WEAR

ALLOWANCE

ID

AC

AE

311

MFD SHAFT

AA, AB I AC

30

MFD HOLE

I

ID

ALLOWANCE OD

-0.0010 -0.0010

32

1

Pin, Clevis- MS20392-2C31 HL1 &6-14

17

X,Z

I

1

0.1860

1

1 +0.0000/

18

X,Z

I

1

0.1860

1

-0.0020 +0.0000/ -0.0020

33

Fitting Assy., Torsion Bar 2311272-19

i

1

1 +0.0030/

1

AG

1

AG

0.2500

1

1 +0.0100/

AH

0.3160

1

1 +0.0100/

AJ

0.1900

1

1 +0.0015/ -0.0000 1 1 +0.0000/ -0.0005 1 1 +0.0015/ I 1 -0.0015 1 +0.01001 1 -0.0100 1 1 +0.0030/ -0.0000

0.2450

1

-0.0020 34

Link- 2311272-5, -23

-0.0100 -0.0100 35

Bushing-

NAS75-3-11

1

I

1

0.3136

AH, AJ I

1

0.1875

AK AK

I

I 1 I

I

1

AK 36 37

Screw- NAS221-8 Bar

1

Assy., Torsion 1

2311272-20

I AL

38

Bearing Assy.,

I 0.3160

0.2450

End 1

2311272-8

AL

0.3440

1

1 +0.0100/ -0.0100

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 9 of 13) EFFECTIVITY:

NOTED

51-71-15

Page9 SRM-4

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 39

1

I DESCRIPTION

EFF.

Arm, DoorLatch2311273-1, -2, -3, -5

(Alt. 2311273-7) (Alt. 2311273-9) .1

I

I HOLE I

1

AM

1

I

MFD

MFD

HOLE ID

SHAFT

MFD

OD

0.4950

ALLOWANCE

ID

1

1 +0.0050/

I

1

1

1 +0.0050/

I

OD

WEAR ID

ALLOWANCE OD

-0.0000

Arm, Door Latch,

40

Center Fwd

2311274-1, -3, -5, -7

(Alt. 2311274-9) (Alt. 2311274-11) (Alt. 231 1 274-13) (Alt. 2311274-15) 41

1

AN

1

1

I

0.4950

I

I

-0.0000

Arm,DoorLatch, Center Aft-

2311274-2, -4, -6, -8 (Alt. 2311274-10) (Alt. 2311274-12) (Alt. 2311274-14) (Alt. 2311274-16) Hinge Half, Fuselage

42

1

1

2311280-1 6-96

AP

I

0.4950

I

AQ

24

0.0700

1

1 +0.0050/

I

1 -0.0000

1

1 +0.0000/ -0.0050

43

44

1

HingeHalf, Fuselage2411282-4, -5, -12, -20, -23, -024 Hinge Half, Door2311280-17

45

AQ

25

1

I AQ

24

1

0.0700

I

I

0.0700

I

1

1 +0.0000/

I

1 -0.0050

1

1 +0.0000/

I

1 -0.0050

1

1 +0.0000/

I

1 -0.0050

Hinge Half, Door 2411282-3, -9, -11,-16, -19, -21,-22, -96

25

1

AQ

I

0.0700

I

Passenger/Crew Lower Door Allowable Wear and Repair Figure 1 (Sheet 10 of 13) EFFECTIVITY:

NOTED

Data

51-71-15

Page SRM-I

10

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

EFF.

DESCRIPTION

NO. 1

Plate

1

A

2

Housing 2311291-2 Guide Assy., Pin 2511278-1

2

AQ

3

B

1

5

Pin, Door 2311291-6 Pin, Clevis MS20392-2C17

1

A, B, C C, D, E F, G

6

Turnbuckle

23

7

AN165H32LS 2411242-1 AN165H32RS

22

Turnbuckle Turnbuckle Turnbuckle

22

E

2411242-2

23

E

1

D, E

4

F

3 4

2311271-17

Bushing

8 9

AA226-1

Crank, Lower Door

2311293-1

2411224-1

Pin, Door, Aft 2311491-16 Guide Assy., Pin 2311271-12 Plate 2311271-17 Pan Assy. 2311229-2 2311300-1 2381403-2 2411221-1 2411221-3, -6

10 ii

12 13

Bushing 2411223-2 Bushing 2311340-5 Pin, Spring NAS561 P4-8 (Alt. NAS561 P4-1 0)

14

15 16 17

1

2411223-5

H

1

J

6

K

7

K

8

K

9

K

10

K

1

K, L M, N N, P

2411222-1

part. part. part. part. part. part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

T

5

T

U

I Replace worn part. Replace worn part. Replace worn part. Replacewompart. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part.

(Alt. 2411222-2) Assy., Fwd Bearing,

22

Block

2311305-3, -9, -23 Block Assy., Aft Bearing,

1

23

2311305-4, -10, -24 Plate, Retaining 2311309-2 Eccentric, Fwd- 2311306-1, -2

1

V

1

W

13 14

W,X, Y W, X, Y W, X, Y W, X, Y X, Z X, Z

24

25

24811081

26

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

1

5

2311301-11, -15

worn

4

4

Pin, Clevis

Handle Assy.

worn

P, Q, R P, Q, R R, S R, S S, T

11

Bolt

21

part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

1

19

20

Replace

D

F

18

NAS464P3A16 MS20392-2C55 Bushing NAS77-3-31

D

G, H, J

12

1 Shaft, Handle 2311302-1

part. part. part. part. part.

1

11

Replace

Replace worn Replace worn Replace worn Replace worn

5

11

REPAIR

HOLE

1

2311306-3 2311306-4 Pin, Clevis MS20392-2C31

15 16 17 18

HLI&6-14

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1(Sheet 11 of 13) EFFECTIVITY:

NOTED

51-71-151 Page

SRM-I

11

Jun 6/98

Learpt

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM NO.

DESCRIPTION

Plug,

27

Fwd

EFF.

2311305-11

HOLE

Y, Z

REPAIR

Replace worn part.

AA 28

Tube, Torque 2311305-22

29

Bolt

30

Plug, Aft-2311305-11,-26

NAS464P4-15

1

AB

1

AA, AB

19

AC,ADI

Replace Replace

worn worn

part. part.

AC

Replaceworn part.

AE 31

1

Eccentric, Aft-2311307-1 2311307-2

Pin, Clevis- MS20392-2C31

32

HL1&6-14 33

Fitting Assy., Torsion Bar

34

Link- 2311272-5, -23

35

Bushing

36

Screw- NAS221-8

37

Bar

38

Bearing Assy., Arm,DoorLatch-

2311272-19

NAS75-3-11 I

20

AE,AFI

21 17

AE,AFI AD,AFI

18

X,Z

1

AG

1

AG,AY

Replaceworn Replaceworn Replaceworn Replace worn

part. part. part. part.

Replace worn Replaceworn Replace worn Replaceworn

part. part. part. part.

1

AJ, AK

1

AH,AJ,I

1

AK,ALI

1

AL

Replaceworn part. Replace worn part.

1

AM

Replace worn part.

1

AN

Replace worn part.

1

AP

Replace worn part.

24

AQ

Replace worn part.

25 24

AQ AQ

Replace worn part. Replace worn part.

25

AQ

Replace worn part.

AK

39

Assy., Torsion

2311272-20 End 2311272-8

2311273-1,-2, -3, -5 2311273-7 2311273-9

Arm, Door Latch, Center Fwd 2311274-1,-3, -5, -7

40

2311274-9

2311274-11 2311274-13 2311274-15 41

1

Arm, Door Latch, Center Aft 2311274-2, -4, -6, -8 2311274-10 2311274-12 2311274-14 2311274-16

42

Hinge Half, Fuselage-

43

Hinge Half, Fuselage

44

Hinge Half, Hinge Half,

231 1 280-1 6, -96

2411282-4, -5, -12, -20, -23, -024 45

Door

2311280-17

Door-

2411282-3, -9, -11,-16, -19, -20, -22,-96

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 12 of 13) I

EFFECTIVITY:

NOTED

51-71-15

Page sRM-4

12

Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL EFFECTIVITIES

CODES

NOTE:

The

following effectivities

are

applicable provided

Aircraft is Eauiooed with 36-inch Pas-

senoer/Crew Door 1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

23-001 thru 23-099; 24-100 thru 24-159; 25-001 thru 25-009 24-160 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29-001 and 001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 thru 24-209; 25-001 thru 25-049 24-210 and Subsequent; 25-050 and Subsequent; 2&001 and Subsequent; 29-001 and

3 4

5

001 and

Subsequent;

6

23-001 thru 23-049

7

23-050 thru 23-099

35-001 and

Except

Subsequent;

Aircraft Modified

36-001 and

by

Subsequent;

31-

Subsequent;

31-

Subsequent

AMK 74-2 "Lower Cabin Door Handle Installation Im-

provement" Except Aircraft Modified by AMK

74-2 "Lower Cabin Door Handle Installation Im-

provement" 8

9

10 11

23-001 thru 23-099 When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvement"; 24-100 thru 24-209 When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvement"; 25-001 thru 25049 When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvement" 24-210 thru 24-229; 25250 thru 25-066, Except 25-061 24-230 thru 24-049; 25-061, 25-067 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099 When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvement"; 24-210 and Subsequent and Prior Aircraft Modified By AMK 74-2 "Lower Cabin Door Handle Installation Improvement"; 25-050 and Subsequent and Prior Aircraft Modified by AMK 74-2 "Lower Cabin Door Han-

12

dle Installation Improvement"; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 38001 and Subsequent 23-001 thru 23-099 Except When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvemenr’; 24-100 thru 24-209 Except When Modified by AMK 74-2 "Lower Cabin Door Handle Installation Improvement"; 25-001 thru 25049 Except When Modified by AMK 74-2 "Lower Cabin Door Handle Instal-

13

lation Improvement" 23-001 thru 23-039 Except When Modified 23-001 thru 23-017 Except When Modified

14

15 16 17 18 19

20 21 22 23

by SSK 909 "Replacement of Cabin Door Lock Actuator" by SSK 909 "Replacement of Cabin Door Lock Actuator" 23-040 thru 23-044 Except When Modified by SSK 909 "Replacement of Cabin Door Lock Actuator" 23-045 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-018 thru 23-099 and Prior Aircraft Modified by SSK 909 "Replacement of Cabin Door Lock Actuator" 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 31001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-018 thru 23-099 Except When Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit"; 24-100 thru 24-219 Except When Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit"; 25-001 thru 25059 Except When Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit" 23-018 thru 23-099 When Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit"; 24-220 and Subsequent and Prior Aircraft Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit" 23-001 thru 23-017 Except When Modified by AAK 71-1 "Cabin Door Hook Manual Release Kit" 35-001 thru 35400; 36-001 thru 36-047 31-001 and Subsequent; 35-401 and Subsequent; 36-048 and With 2311291-6 Door Pin

Subsequent,

and Prior Aircraft

Equipped

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 13 of 13) EFFECTIVITY:

ALL AIRCRAFT

EQUIPPED WITH 36-INCH

PASSENC;ER/CREW DOOR SRM-4

51-71-15

Page

13

Jun 6/98

Lear Learjet

I

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

A

ALLOWABLE WEAR AND REPAIR DATA

~c--A

t3 --~Qln

~eiihc-- B

L.U

C

c

A

~ij

i Detail A

1

a

D

D--´•t~!

TII;

A

I~

1t

J

2

Detail B

o o

~P,

o

o

O

E

A

~11

A 2

f

Detail C 219C-1

2-7C

EFFECTIVITY:

2

1IDetail D

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1(Sheet 1 of 16) ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

i cs

51-71-16

Page

1

Jun 6/98

Leariet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

121

B/ J. H 11

~u

~1

h"~´•ai a

1Zs

hj Detail E Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 2 of 16) EFFECTIVITY:

SRM-I

ALL AIRCRAFT

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

51-71-16

Page 2 Jun 6/98

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

21------

13

Detail F

K

’I

sp~’

I

L

H

G

"I

w

,16

Detail H

P

Detail G 2-3C-1 2-sc

2-3(3-2

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 3 of 16) ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

Data

51-71-16

Page

3

Jun 6/98

1

Learjet ~tl STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

J23

27

V

24

T

X25

OAM AA

W AB

Z

~4t

AL

J30

26

Detail J BB~IOC B4-6A C4-5B1

EFFECTIVITY:

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 4 of 16) ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

AC

51-71-16

Page 4 Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

PASSENGER/CREW UPPER DOOR

K AR

34

3\1

AS

35

AJ AN

AP 33

AQ

34

AQ

AK

AH

A6

AV

AV 29

AY AE

39 37

AE AW AQ 34 AT 36 AT AK

AU

AF Ax

O AF AZ

AU 37

2 318

AX~YV’ BH 45

BJ 44

L

42

AT AW

36

40

BE BC

BE AZ

ED

BN

BH BC

46 BM

BPBK

BE BM

BG BK 2-3C-1

EFFECTIVITY:

BL 46 BK 47

BQ

49

34

BQ84

416 Bg~BR

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 5 of 16) ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

Detail K

AT

BK 46 BL 47

43 BF

AQ

51-71-16

Page 5 Jun 6/98

Leariet STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

ALLOWABLE WEAR AND REPAIR DATA

so

BS

Br

BU

Detail L Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 6 of 16) EFFECTIVITY:

SRM-4

ALLAIRCRAFTEQUIPFEI)WITH PASSENGER/CREW DOOR

24-INCH

51-71-16

Page 6 Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

Plate-2511281-6,-7

Fitting Assy.,

2

I

I HOLE I

EFF.

DESCRIPTION

NO.

1

I

MFD

MFD

HOLE

SHAFT

ID

I

MFD

ALLOWANCE

ID

OD

1

A

0.8280

1

B

0.5625

1

1 +0.0020 -0.0000

1

E

0.0700

1

1 +0.0000

OD

WEAR ID

ALLOWANCE OD

Pin Guide

2511286-9, -10, -13, -15

Hinge Assy.,

3

2511283-1,-6,-7,-11

-0.0050 4

1 Support,Torsion

Bar-

2411682-7, -8, -11,-12, -19, -20, -29, -30, -33, 34

B

1

I

1

0.4300

i

1 +0.0090/ -0.0000

Link

5

Assy., Lower Arm

2411681-19, -21

1

C

6

Bushing- DBS-7-030 (Alt. -AJ07C-125)

1

C

7

Pin, Clevis- MS203923C17

1

D

0.6259

1

1 +0.0000/ -0.0005

I

1

0.2480

1

1 +0.00001 -0.0020

8

1

Link, UpperTorsion2511301-9 Arm

9

1

D

1

0.2500

1

1 +0.0040/ -0.0010

1

F

1

0.4125

1

1 +0.0020/

Assy., 2511301-1,

-801, -802

-0.0000 10

1 Angle,TorqueAdjustment Support, Fwd 8 Aft 2511301-4, 3

1

G

11

I

Plate, Bearing-231168&9

1

H

12

1

Spacer-NAS43HT7-18

1

J

1

0.1890

1

0.4390

1

1 +0.0050/ -0.0000 1 +0.0050/ -0.0000

0.4650

+0.0250/

0.5600

-0.0250 13

1 BracketAssy.,

+0.0180 -0.0120

PinGuide-

2411294-1,-2, -3, -4, -5

2

K

0.5620

1

i +0.0080/

3

K

0.7500

1

1 +0.0050/

I

1

1 +0.0080/ -0.0010 1 +0.0050/ -0.0000

-0.0010

Plate-2411496-63, -265, -266 14

1

I

I

-0.0000

1 GuideAssy.,Pin2411491-1, -5, -7

2

L

0.5620

1

Plate-2411496-63

3

L

0.7500

1

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 7 of 16) EFFECTIVITY:

NOTED

51-71-16

Page 7 SRM-I

Jun 6/98

1

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

DESCRIPTION

NO. 15

I

I

I

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

M

0.5620

MFD I

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

1 GuideAssy., -2411497-1, -2, -7, -8

1

1 +0.0080/ -0.0000

Guide

16

Assy., 2411493-7,

-11 17

1

1

N

0.4950

1

1 +0.0050/ -0.0010

1

P

0.4950

i

1 +0.0050/

Arm, Guide-231127&3, -4, -6

-0.0000 18

Q, RI

1

1

1 +0.0010/

Bolt- AN4-27A

1

Guide-2311502-12

1

R

0.2500

1

1 +0.0050/

231 1 502-1 1

1

Q

0.2500

1

-0.0010 1 +0.0050/

Bolt-NAS464P5A12

1

S

Cover Assy., Outer Handle- 2311287-3, -4

1

T

0.2480

-0.0020 19

1

Clevis

20

-0.0010 21

22

1

I

1

0.1880

0.3117

1

1 +0.0100/ -0.0000 1 1 +0.0000/ -0.0050 1 1 +0.0000/

1

U

I

1

0.8600

I

1

0.1880

23

Pin, Clevis- MS20392-2C63

1

T

24

Spacer- NAS43DD3-26,

1

V

25

Tube, Handle- 2511293-2,

1 +0.0000/ -0.0009

-0.0020 -22

0.2140

0.31 20

+0.0200/

+0.0100/

-0.0200

-0.0100

-44

2

WI

1

1.0000

1

2411516-2, -4

3

WI

1

0.1890

1

1

X

0.1885

1 +0.0010/ -0.0000 1 1 +0.0010/

0.2492

1

26

Bolt- NAS1103-16, -19

1

X

27

Cover

1

Y

1.1250

1

1 +0.0030/

28

Spacer- 2511293-62

Z

1.0200

1

-0.0000 1 +0.00001 -0.0000

Z

1.2000

i

1

1 +0.0060/ -0.0060 1 +0.0000/ -0.0010

-0.0000

Assy., 2411496-355

2

1

Bearing, Thrust- 2411515-1 -2

3

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 8 of 16)

I

EFFECTIVITY:

NOTED

51-71-16

Page 8 SRM-I

Tun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

29

1

I

MFD

ALLOWANCE

MFD

MFD

HOLE

SHAFT OD

ID

OD

1.1200

+0.00001

EFF.

HOLE I

ID

2511287-1, -6, -9

2

AA

1.0060

2411517-1

3

AB

1.0050

AE

0.2492

1

1 +0.0050/ -0.0000 +0.0020/ -0.0000 1 +0.0010/

AF

0.1894

1

1 +0.0010/

AL

0.2492

1

AM

0.2500

1

DESCRIPTION

NO.

I

WEAR ID

ALLOWANCE OD

QuadrantAssy., 1

-0.0020

-0.0000

-0.0000 1 +0.0010/ -0.0000 1 +0.0005/ -0.0001

30

Bolt- NAS1154E40P

2

Eyebolt- 2411520-1

3

AC

I

1

0.2485

1

1 +0.0010/

AD

I

1

0.2485

1

1 +0.0010/

-0.0000

i

-0.0000

31

1

BellcrankAssy., Upper1

251128&3

AG

AH

0.3160 1 nearside 0.1894 1 far side 0.4376 1

1 +0.0005/ -0.0005 1 +0.0010/

0.3160 1 nearside

1 +0.0005/ -0.0005 1 +0.0010/ -0.0000

-0.0000

1 +0.0015/ -0.0000

AJ

0.1894 1 far side

Assy., Upper

Bellcrank

32

Rod

33

2511293-78 Rod Assy., Upper Fwd 251129361

1

AK

1

AN AP

Pin, Locking- 2511293-36

34

1

AQ

0.3160

1

0.3160

1

1 +0.0005/ -0.0005 1 +0.0005/

1

1 +0.0010/

-0.0005

nearside 0.1894

-0.0000

far side 35

1

RodAssy.,UpperAft2511293-50,-80,-83

1

AR

AS

0.3160

1

1 +0.0005/ -0.0005

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 9 of 16) EFFECTIVITY:

NOTED

51-71-16

Page9 SRM-I

Jun 6/98

1

Learjet Learjet/

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

Link,Pin-2511293-28

36

1

37

1 BellcrankAssy.,Aft2511289-3

I

I

MFD

MFD

MFD

ALLOWANCE

HOLE

SHAFT

EFF.

HOLE

ID

OD

1

AT

0.3160

1

1 +0.0005/ -0.0005

1

AU

0.3160

1

1 +0.00051 -0.0005 1 +0.0010/

1

far side 0.1894 near

AV AW

1 1

OD

0.3160

1 1

side

38

RodAssy.,AftBe\bank2511293-72 Rod Assy., Fwd Bellcrank-

1

AX

39

2511293-73 Rod Assy., Ctr Bellcrank 2511293-77 BellcrankAssy., LwrCtr-

1

AY

1

AZ

1

BA

0.5000

1

1 +0.0005/

BE

0.3747

1

1 +0.0015/

BE

0.6250

40 41

1

2511290-1

ID

OD

1 +0.0015/ -0.0000 1 +0.0005/ -0.0005 1 +0.0010/ -0.0000

far side 0.1894

ID

ALLOWANCE

-0.0000

side

0.4376

near

I

WEAR

-0.0000 -0.0000

Bushing- NAS77-4-10 42 43

Rod Assy., Aft Bellcrank 2511293-74 Bellcrank Assy., Lwr Aft

1

+0.0015/ -0.0000

+0.0000/ -0.0010

BC

1

2

2511292-3, -5

0.81 42

1

ED

0.3747

1

BE

0.3160

1

BF

1 +0.0015/

far side 0.1894 1 near side 0.5000 1

-0.0000 1 +0.0005/ -0.0005 1 +0.0010/ -0.0000

1 +0.0005/ -0.0000

BG

0.3160 near

1

1 +0.0005/

1

1 +0.001 0/ -0.0000

-0.0005

side

0.1894

farside

Passenger/Crew Upper Door Figure

(EFFECTIVITY:

NOTED

Allowable Wear and

Repair

Data

1 (Sheet 10 of 16)

51-71-16

Page SRM-I

10

Jun 6/98

Learjet ~Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I IEFF.

DESCRIPTION

NO.

Bellcrank

Assy.,

I

I HOLE I

HOLE

MFD

MFD

ALLOWANCE I WEAR

ALLOWANCE

I SHAFT

ID

I

0.3770

1

1 +0.00051

0.3160 1 far side 0.1900 1 near side

1 +0.00051 -0.0005 1 +0.0010/

1 +0.0010/

OD

ID

OD

I

ID

OD

Lwr Aft 3

2511285-1

ED

-0.0000

BE

-0.0000

BF

0.5000

1

BG

0.3160

1

near

-0.0000 1 +0.0005/ -0.0005 1 +0.00101 -0.0000

side

0.1900

1

far side

Link, Pin-2511293-30, -37,

44

1

-60

BH

0.3160

1

1 +0.00051 -0.0005

Pin, Locking- 2511293-29,

45

1

-61, 36

BJ

0.3160

1

1 +0.0005/ -0.0005 1 +0.00101

1

1 +0.0010/

46

Link, Pin-2511293-30

1

BK

side 0.1894 1 far side 0.3160 1

47

Pin, Locking- 2511293-35

1

BL

0.1894

48

Rod Assy., Fwd Bellcrank 2511293-74 BellcrankAssy., LwrAft-

near

-0.0000

1 +0.00051 -0.0005 -0.0000

49

1

2511291-5

1

BM

1

BN

0.3747

1

BP

0.3160 far side

1

1 +0.0015/ -0.0000 1 +0.0005/ -0.0005 1 +0.0010/

0.1894 1 side

-0.0000

near

BQ BR

0.5000

1

0.3160

1

near

1 +0.0005/ -0.0000 1 +0.0005/

side

0.1894

-0.0005

1

farside

Bushing-

NAS77-4-10

i~

BN

0.6250

0.8142

1 +0.00101 -0.0000 +0.0015/ -0.0000

+0.00001 -0.0010

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1(Sheet 11 of 16) EFFECTIVITY:

NOTED

51-71-16

Page 11 SRM-4

Jun 6/98

IL~i´•t STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD I

ITEM NO. I

I

I

I EFF. I HOLE I

DESCRIPTION

51

Housing- 2411236-1 Cap- 2411237-3

52

Pin, Guide- 5415573-3, -6

3

BM BN BP

53

Sleeve- 5415578-2, -7

3

BQ

50

2

1

2

I

HOLE

MFD

I MFD

ALLOWANCE I WEAR

ALLOWANCE

SHAFT

rD

I

0.3440 0.3440 0.3230

1

0.3230

1

OD

I

rD

OD

I

ID

OD

1 +0.0005! -0.0000 1 +0.0005! -0.0000

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 12 of 16)

JEFFECTIVITY:

NOTED

51-71-16

Page sRM-4

12

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO.

2311281-6, -7

Plate

1

1

A

I

Replaceworn part.

1

B

I

Replaceworn part.

1

E

1

B

1 1

C C

Replace worn part. Replace worn part.

Replace worn part. Replace worn part. Replace worn part.

Pin Guide

2

Fitting Assy.,

3

Hinge Assy.,

4

Support, Torsion

2511286-9, -10, -13, -15

2511283-1, -6, -7,

-11

Link

6

Bushing DBS-7-030 (Alt. -AJ07C-125)

1

2411681-19, -21

1

D

1

D

1

F

10

Upper Torsion 2511301-9 Arm Assy., 2511301-1, -801,-802 Angle, Torque Adjustment Support, Fwd 6 Aft 2511301-4, -3 Plate, Bearing 231168&9

1

G

11

1

H

Spacer NAS43HT7-18 Bracket Assy., Pin Guide

1

J

13

2

K

3

14

2411294-1, -2, -3, -4, -5 2411496-63, -265, -266 GuideAssy., Pin-2411491-1,6,-7

K L

3

L

1

M

1

N

17

Plate 241149663 Guide Assy., 2411 497-1, -2, -7, -8 Guide Assy., 2411493-7, -11 Arm Guide 2311278-3, -4, -6

18

Bolt

19

Guide

Pin, Clevis

8

Link

9

12

MS20392-3C17

Plate

15

16

1

AN4-27A

2

1

P

1

Q,R

2311502-12 Clevis 231 1502-11 Bolt NAS464P5A12 Cover Assy., Outer Handle

1

R

1

1

Q S

1

T,U

1

T

25

2311287-3, -4 Pin, Clevis MS20392-2C63 Spacer NAS43DD3-26, -22 Tube, Handle 2511293-2, -44

26

Bolt

27

Cover

20 21 22

23 24

2411516-2, -4

28

29

I

Replaceworn part.

Lower Arm

5

7

Replace worn part.

Bar-

2411682-7, -8, -11,-12, -19, -20, -29, -30, -33, -34

Assy.,

REPAIR

HOLE

NAS1103-16, -19

Assy., 2411496-355 Spacer 2511293-62 Bearing, Thrust 2411515-1, -2 Quadrant Assy., 2511287-1, -6, 2411517-1

-9

1

V

2

W

3

W

1

X

1

Y

2

Z

3

Z

2

AA

3

AB,AE AF,AL

Replacewompart. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part. part. part. part. part. part.

AM

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 13 of 16) EFFECTIVITY:

NOTED

51-71-16

Page SRM-4

13

Jun 6/98

1

Learjet Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

31

NAS1154E40P

Bolt

30

Eyebolt 2411520-1 1 BellcrankAssy., Upper-251128&3

EFF.

REPAIR

HOLE

2

AC

3

AD

1

AG, AH

Replace worn part. Replace worn part. Replace worn part.

AJ 32

Rod Assy., Upper Bellcrank 2511293-78

33

Rod

34

36

Pin, Locking 251129336 Rod Assy., Upper Aft 2511293-50, -80, -83 Link, Pin 2511293-28

37

Bellcrank

38

Rod

2511293-51 35

1

AK

Replace worn part.

1

AN, AP

1

AQ

Replace worn part. Replace worn part.

1

AR, AS

1

AT

1

AU, AV

Assy., Upper Fwd

Assy.,

Aft

2511289-3

Replace worn part. Replace worn part. Replace worn part.

AW

Assy., Aft Bellcrank

2511293-72 39 40

1

Rod Assy., Fwd Bellcrank 2511293-73 Rod Assy., Ctr Bellcrank 2511293-77

41

1 BellcrankAssy.,

AX

Replace worn part.

1

AY

Replace worn part.

1

AZ

Replace worn part.

1

BA, BE

1

BE

Replace worn part. Replace worn part.

1

BC

Replace worn part.

LwrCtr-

2511290-1 42

Bushing NAS77-4-10 Rod Assy., Aft Bellcrank

43

Bellcrank

2511293-74

Assy.,

1

Lwr Aft 2

1 ED, BE BF, BG

Replace worn part.

Bellcrank Assy., Lwr Aft 2511285-1

3

ED, BE BF, BG

Replace worn part.

44

Link Pin

1

BH

45 46

1 1

BJ BK

47

Pin, Locking 2511293-29, -61,-36 Link, Pin 251129330 Pin, Locking 2511293-35

1

BL

Replace worn Replace worn Replace worn Replace worn

48

Rod

1

BM

Replace worn part.

1

BN, BP BQ,BR

Replace worn part.

1

BN

2

BM

Replace worn part. Replace worn part.

2511292-3, -5

2511293-30, -37, -60

Assy.,

Fwd Bellcrank

2511293-74 49

1 BellcrankAssy.,

LwrAft-

2511291-5

50

part. part. part. part.

Bushing NAS77-4-10 Housing 2411236-1

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 14 of 16)

I

EFFEC~TVITY:

NOTED

Data

51-71-16

Page SRM-I

14

Jun 6/98

Leariet Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM DESCRIPTION

NO.

2411237-3

51

Cap

52

Pin, Guide 5415575-3, -6 Sleeve 5415573-2, -7

53

EFF.

HOLE

2 3

BN BP

3

BQ

REPAIR

Replace worn part. Replace worn part. Replace worn part.

Passenger/Crew Upper Door Allowable Wear and Repair Figure 1 (Sheet 15 of 16) EFFECTIVITY:

NOTED

Data

51-71-16

Page SRM-I

15

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL EFFECTIVITIES

CODES

NOTE:

The following effectivities senoer/Crew Door

are

applicable provided

Aircraft is

Eouiooed

with 24-inch Pas-

1

24-272, 24-295 and Subsequent; 25-134, 25-168 and Subsequent; 2&001 and Subsequent; 29-001

2

24-272; 25-134; 2&001 and 28-002; 31-001 thru 31-091; 35-001; 36-001 and 36-002

3

24-295 and

and

Subsequent;

31-092 and

31-001 and

Subsequent;

35-001 and

Subsequent;

36-001 and

Subsequent

Subsequent; 25-168 and Subsequent; 28-003 and Subsequent; 29-001 and Subsequent; Subsequent; 35-002 and Subsequent; 36-003 and Subsequent

NOTES:

I~ Apply

wet

primer

in bore

prior to bearing installation.

Passenger/Crew Upper Door Allowable Wear and Repair Data Figure 1 (Sheet 16 of 16) EFFECTIVITY:

ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

51-71-16

Page 16 Jun 6/98

I

Learjet Learjefl

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

74

AM

F

d

3

8

DCq

k~o EYs

GZhC

6

4

3 2

Detail A

1 2-14C

(TYPICAL)

Passenger/Crew

Lower Door

Allowable Wear and

Figure 1(Sheet 1 EFFECTIVITY:

SRM-I

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR ALL AIRCRAFT

Repair

Data

of 10)

51-71-17

Page

1

Jun 6/98

Learjet ~Zearjetl STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

.B

d:

N

K

M 11

$e

Ils

13L

15S

Q

,41 c

~o’

//I

Detail B 2-14C

2-55C

EFFECTIVITY:

Passenger/Crew Lower Door Allowable Wear and Repair Figure 1 (Sheet 2 of 10) ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-(

Data

51-71-17

Page 2 Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

PASSENGER/CREW LOWER DOOR

26

B

18

25 U

22

~Be 4~’

AA

AC AB 20 y

23

z

IU~-h

Y~

16

Detail C 2-16C-1

Passenger/Crew

Lower Door

Figure EFFECTIVITY:

SRM-4

1

Allowable Wear and

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

ALL AIRCRAET

Repair Data

(Sheet 3 of 10)

51-71-17

Page 3 Jun 6/98

Learjet I~´•ri´•t!

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

ALLOWABLE WEAR AND REPAIR DATA

33

D

Ad

AE

AF

30

Detail D Passenger/Crew

Lower Door

Figure EFFECTIVITY:

ALL AIRCRAFT

Allowable Wear and

Repair Data

(Sheet 4 of 10)

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR sRM-a

1

AD

51-71-17

Page 4 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

PASSENGER/CREW LOWER DOOR

AH I’

36

AK

35 AJ (TYPICAL)

AH

2-15G2

Passenger/Crew

Detail E

Lower Door

Figure EFFECTIVITY:

SRM-4

1

Allowable Wear and

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

ALL AIRCRAFT

Repair

Data

(Sheet 5 of 10)

51-71-17

Page 5 Jun 6/98

Learjet

STRUCTURAL REPAIR IVIANUAL WEAR ALLOWANCES

ITEM I

I

NO.

DESCRIPTION

1

Plate-251129&1

2

Guide

I

I

MFD

MFD

HOLE

SHAFT OD

MFD

ALLOWANCE

EFF.

HOLE

ID

1

A

0.4950

1

1 +0.00501 -0.0010

1

B

0.4950

1

1 +0.00501

I

ID

OD

WEAR ID

ALLOWANCE OD

Assy., Pin

2511297-1

-0.0010

Pin, Door- 2311299-1

3

A,B I

1

1

0.4850

1

1 +0.0100/ -0.0000

C

0.1880

C,D I

1

1 +0.00501 -0.0000

1

4

Pin, Clevis- MS20392-2C17

1

5

Turnbuckle- 2511226-3

1

D

0.1890

1

6

Turnbuckle- MS21242S3

1

E

0.1900

1

7

Spacer-

1

F

0.6520

8

Bellcrank, Lower Door1

G

0.1890

1

1

K

0.6600

1

1

K

0.1860

1

1 +0.0000/ -0.0020

2511298-4

2411227-2

Pan

9 10

Assy. 2411221-3,

-6

1 Bushing-FF-520-10

I

1 +0.0000/ -0.0000 1 +0.0020/ -0.0000

1 +0.0000/ -0.0000 1 +0.0300/ -0.0300

1

0.6200

1

1 +0.0300/ -0.0300

111 Bushing-2311340-5

1

L

0.5030

1

M

0.3800

1

N

0.1400

1

1 +0.0010/ -0.0000 1 +0.0300/ -0.0000 1 +0.0100/ -0.0100

12

1 Pin, Spring- NAS561 P4-8

13

(Alt. NAS561 P4-1 0) Shaft, Handle-24112236

1

1

I

N,P I

1

I

I 1

P

Q

0.1250

I

1

1 +0.0040/

I

I

1

1

1 +0.0050/ -0.0000

1

0.1310

0.3700

1

-0.0000

1 +0.0020/ -0.0000

R

0.1900

1

1 +0.0010/ -0.0000

14

1

15

1 Bushing-NAS43HT3-16

Pin, Clevis-MS20392-2C55

1 1

R,S I S T

1 0.2140

I

0.1880

1 1

0.3120

1

1 +0.0000/

-0.0020 1 +0.0200/ -0.0200 1 1 +0.01001 -0.0100

Passenger/Crew Lower Door Allowable Wear and Repair Figure 1 (Sheet 6 of 10)

I""""": SRM-(

ALL AIRCRAFT~

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

Data

51-71-17

Page 6 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I 16

I DESCRIPTION

17

Fwd- 2511317-4

I

MFD

MFD

HOLE

SHAFT

HOLE

IEFF.

HandleAssy. -2411222-1 (Alt. 2411222-2) BlockAssy., Bearing,

1

I

T

1

1

1

I

0.3121

1

1 +0.0005/

I

1

1

1 +0.001 0/

1.0020

ID

OD

WEAR

ALLOWANCE

ID

I U

1

h(FD

OD

I

ID

ALLOWANCE OD

-0.0000

-0.0000 18

1 BlockAssy., Bearing,Aft2311317-3

19

1

21

Plate- 231130541

1

V

1.0020

1

1 +0.0010/ -0.0000

1

W

0.6870

1

1

X

0.6900

1

1 +0.0030/ -0.0030 1 +0.0000/ -0.0000

Plate, Retaining2311309-2

20

1

Eccentric,Fwd251 1 306-2

13

1

W

I

1

0.6200

1

1 +0.0100/ -0.0100

Y

0.1890

1

1 +0.0050/

Z

0.5000

1

1 +0.0060/

-0.0010 -0.0000 22

Bolt- NAS221-20

1

AA

23

Bearing-81210

1

24

Retainer- 2511316-3

1

U AB

I

1

0.1890

1

1 +0.0000/ -0.0009

0.7520

1

1 +0.0015/

-0.0015 AC

I

1

0.1960

1

1 +0.0050/

1

AC

I

1

0.1860

1

1 +0.0000/

1

V

2511667-2

1

AD

28

Boit- AN4-15A

1

AD

29

Bushing- NAS75-4-010

1

AD

0.2500

30

Link- 2511268-1

1

AE

0.3160

1

AD

0.3770

1

AE

0.1900

-0.0000 25

Pin, Clevis- MS20392-2C31

26

Bearing-

27

Fitting Assy.,

-0.0020 81210 Torsion Bar 0.2570

I

1

1

1 +0.0050/ -0.0010 0.2490

1

1 +0.0000/ -0.0030

0.3761

+0.0015/ -0.0005 1 +0.0050/

+0.0000/ -0.0005

-0.0000

311 Bushing-NAS75-3-007

1

Passenger/Crew

Lower Door

Figure EFFECTIVITY:

SRM-I

ALL AIRCRAFT

1 +0.0050/ -0.0000 0.3136

1

Allowable Wear and

1 +0.0000/ -0.0005

Repair Data

1 (Sheet 7 of 10)

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

51-71-17

Page 7 Jun 6/98

Learjet Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

32

Screw- 2511269-6

33

(MS24694-54) BarAssy., Torsion-

AF

1

1

I HOLE

EFF.

DESCRIPTION

NO.

I

I 1

I

AG

MFD SHAFT

MFD

ID

OD

I

0.1890

ID

OD

1

1

1 +0.00001

I

I

I

1

1

1 +0.0000/

0.1890 I

I

I

1

1

0.2180

WEAR

ALLOWANCE

I

AF

2511267-1

MFD HOLE

I

ID

ALLOWANCE OD

-0.0003

-0.0003

1

1 +0.0000/ -0.0030

34

1 Bearing Assy.,

End

2511269-3 35

1

1

AG

0.2210

1

1 +0.0050/ -0.0000

1

AH

0.4950

i

1 +0.0050/

Arm, Door Latch 2311273-10

-0.0000 36

Arm, Door Latch, Center Fwd

2311274-7, -13, -15,

-17

1

AJ

0.4950

1

1 +0.0050/ -0.0000

37 1

Arm, Door Latch, Center Aft

2311274-8, -14, -16, -18

1

AK

0.4950

1

1 +0.0050/

-0.0000

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 8 of 10)

I""""": sRM-4

ALL AIRCRAFT

EQUIPPED WITH 24-INCH

51-71-17

Page8 Tun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

REPAIR

IHOLE

1

A

1

B

1

4

Plate 251129817 Guide Assy., Pin 2311297-1 Pin, Door 2311299-1 Pin, Clevis MS20392-2C17

1

A, B, C C, D

5

Turnbuckle

2511226-3 Turnbuckle MS21242S3 Spacer 2511226-3 Bellcrank, Lower Door 2411227-2

1

D

1

E

1

F G

Pan Assy. 2411221-3, -6 Bushing FF-520-10 Bushing 2311340-5 Pin, Spring NAS561 P4-8 (Alt. NAS561 P4-1 0)

1

K

1 1

K, L M, N

1

N, P

Shaft, Handle 2411223-5 Pin, Clevis MS20392-2C55

1 1 1

T

Replace worn part. Replace worn part. Replace worn part. Replace worn part.

17

Bushing NAS43HT3-16 Handle Assy. 2411222-1 (Alt. 2411222-2) Block Assy., Fwd Bearing,

P, Q, RI R, S S, T

1

U

Replace worn part.

18

1 BlockAssy., AftBearing,1

V

1

W

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replaceworn part. Replace worn part. Replace worn part.

1 2 3

6 7

8 9

10 11 12

13 14

15 16

2511317-4 2311317-3 2311309-2

1

1

19

Plate, Retaining

20

Plate

1

X

21

Eccentric, Fwd

1

W, X, YI

22

Bolt

NAS221-20 Bearing 81210 Retainer- 2511316-3 Pin, Clevis MS20392-2C31

1

AA

27

Bearing 81210 Fitting Assy., Torsion

28

Bolt

29

Bushing

NAS75-4-010

1

AD

30

1

AD,AEI

31

Link- 2511268-1 Bushing NAS75-3-007

1

AE

32

Screw

1

AF

33

Bar

1

AF,AGI

23 24

25 26

2311305-41 231 1 306-2

U

1

AB,ACI

1

AC

1

V

1

AD

1

AD

Bar

2511667-2 AN4-15A

2511269-6

(MS24694-54) Assy., Torsion

1

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

2511267-1

Replace worn Replace worn Replace worn Replaceworn Replace worn Replace worn

part. part. part. part. part. part.

Replaceworn part.

Passenger/Crew Lower Door Allowable Wear and Repair Data Figure 1 (Sheet 9 of 10) EFFECTIVITY:

SRM-I

EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

ALL AIRCRAFT

51-71-17

Page 9 Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM NO.

REPAIR

DESCRIPTION

EFF.

HOLE

End

1

AG

Replace worn part.

1

AH

Replace worn part.

1

AJ

1

AK

2511269-3

34

Bearing Assy.,

35

Arm,DoorLatch-

36

Arm, Door Latch, Center Fwd 2311274-7, -13, -15, -17

2311273-10

I

Replacewompart.

Arm, Door Latch, Center Aft

37

2311274-8, -14, -16, -18

CODES

Replace

worn

part.

EFFECTIVITIES NOTE:

The

following effectivities

are

applicable provided Airoraft is Eaui~ed with 24-inch

Pas-

senger/Crew Door 1

24-272, 24-295 and Subsequent; 25-134, 25-168 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

Passenger/Crew Lower Door Allowable Wear and Repair Figure 1 (Sheet 10 of 10) EFFECTNITY:

ALL AIRCRAFT

EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR SRM-I

Data

51-71-17

Page

10

Tun 6/98

Learjet

STRUCTURAL REPAIR MANUAL QUADRANT ASSEMBLY

ALLOWABLE WEAR AND REPAIR DATA

J

O 7 5

rA

6~

4\ 3,

C

2~

i

1\B

C

9M 10

1.1

13

b’

12 10

Detail A 2-12C

EFFECTIVITY:

Quadrant Assembly Allowable Wear and Repair Data Figure 1(Sheet 1 of 11) NOTED

51-71-181 Page

SRM-I

1

Jun 6/98

Learjet Learjet/ STRUCTURAL REPAIR MANUAL QUADRANT ASSEMBLY ALLOWABLE WEAR AND

REPAIR DATA

00~´•

B

26

AA

Lu\

23

‘AC

ls,V\ AB

i

’5 a w

a

Detail B 2-12C

(EFFECTIVITY:

Quadrant Assembly Allowable Wear and Repair Figure 1 (Sheet 2 of 11) NOTED

Data

51-71-18

Page 2 SRM-I

Tun 6/98

Learjet ~Learjet STRUCTURAL REPAIR MANUAL QUADRANT ASSEMBLY ALLOWABLE

WEAR AND REPAIR DATA

000

AY c

AW

3

39

AQ

AX/

7

36

32

44

AS AR

AJ AP AN

b

o

34 AL 33 30 29 AF 27

AE

Detail C 2-12C

Quadrant Assembly Allowable Wear and Repair

Figure EFFECTIVITY:

NOTED

1

Data

(Sheet 3 of 11)

51-71-18) Page3

SRM-Q

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL QUADRANT ASSEMBLY ALLOWABLE WEAR AND REPAIR DATA

00000

55

D so

3~ 47, BO

g~

~53

-´•---i49 54

AZ

c

d

t:r~

i

\I,

1-

BE

Be

53

~j Detail D

Z12C

Quadrant Assembly Allowable Wear and Repair

Data

Figure 1 (Sheet 4 of 11)

I

EFFECTIVITY:

NOTED

51-71-18

Page$ SRM-I

Jun 6/98

Learjet ~tl

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I DESCRIPTION

NO.

I

I

EFF.

HOLE

1

A

HOLE

MFD

ID

I

1

1

Tube-2315131-2

2

Handle-Park, Brake231513-80,-180

1

B

0.8750

Bushing- 23151 31-26

1

B, C

0.7500

MFD

WEAR

ALLOWANCE

ALLOWANCE

I SHAFT OD

I

0.7490

1

ID

OD

I

ID

OD

1 +0.0000/ -0.0000

1

1 +0.00301 -0.0000

3 4

Lever, Throttle- 2315131-12

5

Wheel

1

D

1.6200

0.8740

+0.00301

-0.0000 1 +0.00001

1

+0.00001 -0.0000

-0.0000

Assy., Sector-

23151’31-65, -72

1

E

1

E

1

E, F

1.0000

2315131-46, -70

1

G

0.7500

7A

Spacer- 2315131-48

1

8

Plate Lock- 2315131-7

1

J

0.7500

9

Spacer- 2315131-41

1

J, K

1.0000

10

Plate Lock- 2315131-47

1

J

0.7500

1

J, K

1.0000

1

N

0.8750

1

N, P

0.7500

0.9375

1

1 +0/0005/ -0.0005

6

Bushing- NAS76A-12-16 Spacer- 2315131-10

7

Plate

Assy.,

0.7500

+0.00001 +0.0100/ -0.0000 1 -0.0000

Lock

11

I Spacer-2315131-19

12

1 Handle,FlapControl2315131-74

G,

H

1

1.0000

1 +0.00301 0.7500

1 0.7500

1 0.7500

1

-0.0000 +0.00001 -0.0000 1 +0.0010/ -0.0000 +0.00001 -0.0000 1 +0.0010/ -0.0000 +0.0000/ -0.0000

+0.01001

-0.0000

+0.01001 -0.0000

+0.01001 -0.0000

1 +0.0030 -0.0000

13

1

Bushing-2315131-26

0.8740

+0.0030/

-0.0000 14

1

Tube-2315131-2

15

1

HandleAssy.,

2

Q

I

1

0.7490

1

+0.0000/ -0.0020

1 +0.0000/ -0.0020

ParkBrake-

2315131-1 08, -141

3

R

0.8750

1

2415167-1

4

R

0.8750

1

1 +0.0030/ -0.0000 1 +0.00301 -0.0000

Quadrant Assembly Allowable Wear and Repair

Figure EFFECTIVITY:

NOTED

1

Data

(Sheet 5 of 11)

51-71-18

Page5 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO. 16

Spacer-2315131-26,

1

-137

I

I

MFD

MFD

HOLE

EFF.

HOLE

ID

SHAFT OD

2

R, S

0.7500

0.8740

MFD

ALLOWANCE

ID

OD

+0.0030! -0.0000

+0.0000/

WEAR ID

ALLOWANCE OD

-0.0020

Lever,Throttle-

17

T

2

2315131-101

1.6200

1

1 +0.0000/ -0.0000

WheelAssy.,SectorLH-

18

2315131-99, -117, -136 19

I CamAssy.,

LH2315131-85

Spacer- 2315131-88

20

2

U

0.7500

1

2

V

0.7500

1

2

V, W

1.0000

1 +0.0000/

0.7500

-0.0005 1 +0.0030/ -0.0000 +0.0000/ -0.0000

21

1

+0.0100/ -0.0000

PlateAssy.,Lock2315131-70

2

X

0.7500

2

X, Y

1.000

1

1 +0.0030/ -0.0000

22

Spacer- 23151 31-96

23

Lever, Throttle2

1.6200

1

1 +0.0000/ -0.0000

2

AA

0.7500

1

1 +0.0000/

2

AB

0.7500

1

1 +0.0100/ -0.0000

0.7600

2

2315131-101

1

+0.0000/ -0.0000

0.7500

-0.0100/ -0.0000

Wheel Assy., Sector RH

24

231 5131-100, -116, -135

-0.0005 25

1

26

1 Spacer-2315131-94

Platelock-2315131-7

2

1

AC,

1

AE

I

1

27

Tube- 2315131-149

5

28

Handle Assy., Park Brake 231 51 31-141

6

AF

0.8750

1

7

AF

0.8750

1

5

AF,

0.7500

24151 67-1 29

1 Spacer-2315131-137

+0.0050/ -0.0050

1.0000 0.7490

1

0.8740

1 +0.0030/ -0.0000 1 +0.0030/ -0.0000 +0.0030/

AG 30

1

-0.0000

+0.0000/ -0.0020

Lever,ThrottleLH2315164-69

31

1 +0.0000/ -0.0020

5

AH

1.2500

5

AJ

0.7510

1 WheelAssy.,SectorLH2315131-145

1

1 +0.00051 -0.0005

Quadrant Assembly Allowable Wear

Figure EFFECTIVITY:

NOTED

and

Repair Data

1 (Sheet 6 of 11)

51-71-18

Page 6 SRM-4

Jun 6/98

Learjet ~jLearjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

NO.I 32

DESCRIPTION

1 CamAssy., LH-2315131-851

I

I

ID

5

AK

0.7500

1

AL

0.3160

1

j Spacer-231513180

5

AL

Screw- NAS220-6 Spacer- 2515164-51

5

AL

5

AK, AM, AP,

34 35 36

Trunnion-2315131-91

1

OD

HOLE

AL

1

MFD SHAFT

EFF.

5

33

MFD HOLE

I

1 0.3150

I

0.3150

1 1

MFD I

WEAR

ALLOWANCE

ID

OD

I

ID

ALLOWANCE OD

1 +0.0030 -0.0000 1 +0.00301 -0.0000 1 1 +0.0000/ -0.0030 1 +0.0000/ -0.0030

0.1640

0.7500

1.0000

+0.01 00/

-0.0000

AQ 37

1 PlateAssy.,

Lock2

2315131-70

AN

0.7500

AP,

0.7500

1

1 +0.0030/ -0.0000

5

Spacer- 2513164-51

38

1

1.0000

AQ 39

1

Wheel Assy., Sector2315131-146

AR

0.7510

5

AS

1.2500

5

AT

1

1 +0.0005/ -0.0005

0.7500

1

1 +0.01001 -0.0000 1 +0.0100/ -0.0000 1 +0.0030/ -0.0000 1 +0.0030/

Lever, Throttle RH

40

2515164-70 41

5

+0.01 00/ -0.0000

1 LockPlateAssy.,Flap Switch- 2514164-75

42

Spacer- 2515164-78

5

AT

0.7500

1

43

Flap Cam

5

AU

0.8750

1

44

Lever, Flap- 251 5164-74

5

AV

0.8750

1

45

Bushing, Flap Lever

2515164-76

-0.0000

2515164-49 46

1

Spacer-

5

2315131-10

5

AV, AX,

0.7500 1.0000

0.8740 0.7500

+0.0030/ -0.0000

-0.00020

+0.0000/

+0.0010/

-0.0000

-0.0000

Quadrant Assembly Allowable Wear and Repair

Figure EFFECTIVITY:

NOTED

1

(Sheet

7 of

+0.0000/

Data

11)

51-71-18

Page 7 sRM-a

Jun 6/98

Leariet Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I

DESCRIPTION

NO.

Link

47

I

MfD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

8

AZ

1.0623

1

BA

0.1920

1

BE

0.2520

1

MFD

WEAR

ALLOWANCE

ID

OD

I

ID

ALLOWANCE OD

Assy, Output

2615260-3, -6

1 +0.0002/ -0.0003 1 +0.0020 -0.0020 1 +0.0020 -0.0020

Shaft, Quadrant-

48

BC

8

2615137-3

I

1

0.6243

1 +0.0002/

1

-0.0003 49

1 Spacer- 2615172-19

8

1

BC

+0.01 00

+0.0050 -0.0050

0.81 20

0.6300

-0.0100

Lever, Thrust Reverser-

50

8

261 5242-14

1

ED

0.9290

1

1 +0.0050

BE

0.0630

1

1 +0.0020/

-0.0050 -0.0010 51

1

BE

8

RollPin-MS16562-8

I

1

0.0680

1 +0.0010/

1

-0.0020

Output

52

Link

Stop 9

BF

0.2530

1

1 +0.0010/

2615290-1

10

BF

0.2530

1

1 +0.0010/

NAS43DD4-29

8

261 5266-1, -2

-0.0020

Tie 53

Strap

1 Spacer-

54 1

Bolt- NAS1104-16

55

Idle

1

1 BF

8

I

-0.0020 +0.0220/ -0.0190

0.3750

0.2750

1

0.2485

1

+0.0100 -0.0100

1 +0.0002/ -0.0004

Stop Assy. 1

-13 56

57

BG

8

2615203-7, -9, -10, -11,

I

0.7500

1

1 +0.0100/ 1 -0.0100

0.3180

1

1 +0.0020 -0.0020

I

Lever, Ignition Switch 2615255-2, -7

8

BH

Pin- MS20392-2C11

8

BH

I

1

0.3110

1

1 +0.0000/ -0.0020

Quadrant Assembly Allowable Wear and Repair Figure 1 (Sheet 8 of 11) EFFECTTVITY:

NOTED

Data

51-71-18

Page 8 SRM-4

Jun 6/98

Learjet ~Learjetl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION

EFF.

HOLE

1

Tube -2315131-2 Handle-Park, Brake- 2315131-80, -180 Bushing 2315131-26 Lever, Throttle 2315131-12 Wheel Assy., Sector Bushing

1

A

2 3 4 5

7

7A

8 9 10 11 12

13 14

15

Spacer 2315131-10 Plate Assy., Lock 2315131-46, Spacer 2315131-48

B

1

B, C

1

D

1

-70

Plate Lock 2315131-7 2315131-41 Plate Lock 2315131-47 Spacer 2315131-19 Handle, Flap Control 2315131-74 Bushing 2315131-26 Tube 2315131-2 Handle Assy., Park Brake

Spacer

I

1

1

NAS76A-12-16 6

E

E,

F

1

G

1

G, H

1

J

1

J, K

1

L

1

L, M

1

N

1

N, P

2

Q

2315131-108, -141

3

R

2415167-1

4

R

2

R, S

2

T

-137

16

Spacer 2315131-126,

17

Lever, Throttle 2315131-101

18

Wheel

19

Cam

20

Assy., Sector

REPAIR

2

U

LH

2

V

Spacer 2315131-88 Plate Assy., Lock 2315131-70 Spacer 2315131-96

2

V, W

2

X

2

X, Y

2

Z

24

Lever, Throttle 2315101-101 Wheel Assy., Sector RH 2315131-100, -116, -135 Plate, Lock 2315131-7

2

25

2

AA AB

26

Spacer- 2315131-94

2

AC, ADI

27

Tube 2315131-149 Handle Assy., Park Brake 2315131-141

5

AE

6

AF

7

AF

21 22

23

28

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn Replace worn Replace worn Repalce worn

part. part. part. part.

Replace Replace Repalce

Replace worn Replace worn Replace worn

part. part. part. part. part. part.

Replace worn Replace worn Replaceworn Replace worn

part. part. part. part.

Replace Replace Replace

part. part. part. part.

LH

2315131-99, -117, -136

Assy.,

Replaceworn part.

2315131-85

2415167-1

worn worn

worn

worn worn

29

Spacer

2315131-137

5

AF, AG

30

Lever, Throttle LH 2515164-69

5

AH

Replace worn

31

Wheel

32

2315131-145 Cam Assy., LH 2315131-85

33

Trunnion

Replace worn part. Replace worn part. Replace worn part.

Assy.,

worn

Sector LH

2315131-91

1

5

AJ

5

AK, AL

5

AL

Quadrant Assembly Allowable Wear and Repair

Figure EFFECTIVITY:

NOTED

Data

1 (Sheet 9 of 11)

51-71-18

Page 9 sRM-a

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

HOLE

REPAIR

34

Spacer

5

AL

35

Screw

5

AL

5

AK,AMI

2

AN

5

AP,AQ1

5

AR

5

AS

5

AT

5

AT

5

AU

5

43

2315131-90 NAS220-6 Spacer- 2515164-51 Plate Assy., Lock 2315131-70 Spacer- 2515164-51 Wheel Assy., Sector 2315131-146 Lever, Throttle RH 2315164-70 Lock Plate Assy., Flap Switch 2515164-75 Spacer 2515164-78 Flap Cam 2515164-76

44

Lever, Flap 2515164-74

36 37 38 39 40 41 42

45 46 47

AV

Bushing, Flap Lever- 2515164-49 Spacer 2315131-10 1 Link Assy., Output 2615260-3, -6

1

5

AV, AWJ AX, AY

8

AZ,BA,(

Replace worn part. Replace worn part. Replaceworn part. Replace worn part. Replaceworn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replaceworn part. Replace worn part. Replacewompart.

BE 48

Shaft, Quadrant 2615137-3

8

49

Spacer

8 8 8

BC BC ED, BE BE

9

BF

50

51 52

2615172-19 Lever, Thrust Reverser Roll Pin MS16562-8

Output

Link

2615242-14

Stop 2615266-1,

-2

Tie Strap

55

2615290-1 Spacer- NAS43DD4-29 Bolt NAS1104-16 Idle Stop Assy. 2615203-7, -9, -10,

56

Lever, Ignition Switch 26i 5255-2,

57

Pin-MS20392-2C11

53 54

-11, -13 -7

8

BG

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replaceworn part. Replace worn part.

8

BG BH BH

Replace worn part. Replace worn part. Replacewornpar.

BF

10 8

8 8

1

I

I

Quadrant Assembly Allowable Wear and Repair Data Figure 1 (Sheet 10 of 11) EFFECTIVITY:

NOTED

51-71-18

Page 10 SRM-II

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL CODES 1 2

EFFECTIVITIES 23-001 thru 23-010, 23-013, 23-014, 23-016 thru 23-018, and 23-020 thru 23-029 23-011, 23-015, 23-019, 23-030 and Subsequent; 24-100 and Subsequent, Except Aircraft With

Thrust Reversers Installed; 25-001 and Subsequent Except United Kingdom Certified Aircraft and Except Aircraft With Thrust Reversers Installed; 2&001 and Subsequent; 29-001 and Subsequent 3

23-011, 23-015, 23-019, 23-030 and Subsequent; 24-100 thru 24-357 Except Aircraft With Thrust Re-

Instailed; 25-001 thru 25-277 Except United Kingdom Certified Aircraft and Except Aircraft With Thrust Reversers Installed; 28-001 thru 28005; 29-001 thru 29-002 24-358 and Subsequent; 25-278 and Subsequent; 2&006 and Subsequent; 29-003 and Subsequent 25-135 and Subsequent When Certified for United Kingdom 25135 thru 25-277 When Certified For United Kingdom 25277 and Subsequent When Certified for United Kingdom 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent versers

4

5 6 7

8

Quadrant Assembly Allowable

Wear and

Figure 1(Sheet 11 EFFECTnTITY:

NOTED

Repair Data

of 11)

51-71-18

Page SRM-Q

11

Jun 6/98

Learjet Learjetj

STRUCTURAL REPAIR MANUAL MLG POWER BRAKE VALVE LINKAGE

ALLOWABLE WEAR AND REPAIR DATA

3

4

i,

B´• 7111

s\

C

F

A

5

7

s 9’

lD (TYPICAL)

Detail A MLG Power Brake Valve

Linkage Allowable Wear and Repair Data Figure 1 (Sheet 1 of 3)

EFFECTIVITY:

ALL

51-71-19

Pagel SRM-4

Jun 6/98

1

Learjet Learjeti STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.

I

I

MFD

MFD

HOLE

SHAFT OD

MFD

ALLOWANCE

EFF.

HOLE

ID

2315141-24, -33

2

A

0.3750

1

1 +0.0030/

2384010-2, -6

3

A

0.3750

1

2415171-1

4

A

0.3750

1

i +0.0030/ -0.0010 1 +0.0030/

2415171-9

5

A

0.3750

1

1 +0.0030/

2415175-1

6

A

0.3750

1

1 +0.00301

1

B

0.6557

1

1 +0.00201

DESCRIPTION Pedal

1

I

I

ID

OD

WEAR ID

ALLOWANCE OD

Assy., Rudder-0.0010

-0.0010 -0.0010 -0.0010 Link

3

Assy. 2315167-22 (Alt. 2315167-29) Bolt- NAS464P439, -40

4

Bolt- NAS464P4-9

5

1 ArmAssy.,Brake-

2

1

I

I

I

1

-0.0000

1

A,B

1

1

1 +0.0000/

1

B, C, I D,E I

1 0.2492 1 I I

1 +0.0000/ 1 -0.0009

0.2492

-0.0009

Alt. 2315166-15

C

1

2315166-19

1

I

0.2500

1 I

0.3120

1 1

I

Link-2315167-27

1

E

7

Nut

2315167-16

1

F

0.3140

8

Bushing- NAS75-3-004

1

F

0.1900

9

Lever- 2315167-3, -28

1

G

0.1910

1

G

0.1910

1

6

1

Assy.

1

1 +0.0050/ 1 -0.0010 1 +0.001 0/ -0.0010 1 +0.0010/ -0.0000

(Alt. 2315167-25)

0.31 36

+0.0015/ -0.0000 1 +0.0050/ -0.0010 1 +0.0050/

+0.0000/ -0.0005

-0.0010 10

Bolt- NAS464P3-16

1

F,G I

1

0.1894

1

1 +0.0000/ -0.0009

MLG Power Brake Valve

Linkage Allowable Wear and Repair Data Figure 1 (Sheet 2 of 3)

IEFFECTIVITY:

ALL

51-71-19

Page2 SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

NO.

DESCRIPTION Pedal -33 Pedal Pedal Pedal

1

Assy.,

Rudder- 2315141-24

Assy., Rudder 2484010-2, Assy., Rudder 2415171-1 Assy., Rudder 23151718 Pedal Assy., Rudder 2415175-1 Link Assy. 2315167-22

2

EFF.

-6

2

A

3

A

4

A

5

A

6

A B

1 1

4

Alt. 2315167-29 Bolt NAS464P4-39, -40 Bolt NAS464P4-9

5

Arm

1

3

1

Assy., Brake 231516619 (Alt. 2315166-15)

6

Link

7

Nut

HOLE

A, B B, C, D, E C, D C, D

2315167-27

1

E

1

F

8

Assy. 2315167-16 Bushing NAS75-3-004

1

9

Lever

1

F G G F, G

2315167-3, -28

(Alt. 2315167-25) 1

10

Bolt- NAS464P3-16

CODES

1

REPAIR

I

Replacewompart. Replace worn Replace worn Replace worn Replace worn Replace worn

part.

part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25001 and 001 and Subsequent; 36-001 and Subsequent

2

Subsequent Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 24-100 thru 24357 Except When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" or AMK 81-03, "Rudder Pedal Heel Support Replacement"; 25-001 thru 25-302; 2&001 and Subsequent; 29001 and Subsequent; 35-001 thru 35-299; 36-001 thru 36-045 23-001 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 24-100 thru 24-139 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement" 24-358 and Subsequent and Prior Aircraft Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 25-303 thru 25-338 and Prior Aircraft Modified AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 35-300 thru 35-400; 36-046 and 36-047 23-001 and Subsequent When Modified by AMK 81-03, "Rudder Pedal Heel Support Replacement"; 24-100 thru 24-357 When Modified by AMK 81-03, "Rudder Pedal Heel Support Replacement"; 25001 thru 25357 When Modified by AMK 81-03, "Rudder Pedal Heel Support Replacement"; 35-401

3

4

5

6

Subsequent;

31-001 and

Subsequent;

35

23-001 and

thru 35-617; 35-621 thru 35-624; 36-048 thru 36-055 23-001 and Subsequent When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 24-140 thru 24-357 When Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 25339 and Subsequent and Prior Aircraft Modified by AMK 81-02, "Rudder Pedal Rework and Heelplate Replacement"; 31-001 and Subsequent; 35-618 thru 35-620, 35625 and Subsequent; 36-056 and Subsequent

MLG Power Brake Valve

Linkage Allowable Wear and Repair Data Figure 1 (Sheet 3 of 3)

EFFECTIVITY:

ALL

51-71-19

Page 3 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL MAIN GEAR DOOR AND UPLATCH

ALLOWABLE WEAR AND REPAIR DATA

B

8

3

~5

2

A

14-90C-2

Main Gear Door and

A63C-1 A66C

EFFECTIVITY:

ALL

6~

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 1 of 6) 51-71-20

Pagel SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL MAIN GEAR DOOR AND UPLATCH

ALLOWABLE WEAR AND REPAIR DATA

~6´• 8

11/

,10 E

23

K´• 22

21

13

G

F

12

,P ~20

18

J 17

Detail A Main Gear Door and

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 2 of 6) 51-71-20

Page2 SRM~

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

I

I

MFD

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

A

0.2500

MFD

ALLOWANCE

ID

OD

WEAR ID

ALLOWANCE OD

Plate, Adjustable-

1

23270213

1

1 +0.00501 -0.0010

2

i

Bolt-NAS464P4-14

1

A

I

1

0.2492

1

1 +0.0000/

3

1

Bolt-AN174HC12A

1

B

I

1

0.2492

1

1 +0.0000/

4

1 ActuatorSupportPlate-

-0.0005 -0.0010 B

0.2495

1

1

C

0.2505

1

Bolt-AN174-12A

1

C

RodEnd-DREM-4-050

1

C C

2311623-27, -28

1

5

1 Fitting-2322522-1

6

1

7

1

I

I

i +0.0010/ -0.0000 1 +0.0000/ -0.0010

1

0.2492

1

1 +0.0000/ -0.0005

(Alt. ARYHT4E) Bolt- NAS464P4-23, A23 A22 Deleted Bracket Assy.

8 9 10

2348042-1, -2 11

I

Bolt-AN24-36

12

1

Bracket

D

1

I

I

i

1

1

1 +0.0000/

I

I

I

1 -0.0009

1

1 +0.0050/ -0.0010 1 1 +0.0000/

1

E

1

1

E

I

0.2500

0.2492

1

0.2480

-0.0020

Assy.

1

14

Bushing- 6L6-F Bushing- NAS75-4-122

F G F

1

F

15

Bolt- AN24-36

1

G

Roller-2317060-6

1

I

1

0.4445

Spacer-

1

I

1

0.2970

1

2348041-1, -2 13

0.4380

0.2500

0.2500

I

1 ~0.0010/ I ~t0.0100

1 1

+0.0015/ -0.0000

+0.0000/ -0.0005 1 +0.0000/

0.5620

+0.0000/ -0.0010

f0.0100/

0.3750

+0.0000/

+0.0000/

-0.0410

-0.0100

0.3761

1

0.2480

1

-0.0020 16

17

i

1

2317065-4

1

Bushing- 6L8-D BracketAssy. -2311630-11,

H

1

1

-12

I

0.1890

I

1 I

1 +0.0050/ 1 -0.0010

(Alt. 2311630-13, -14) (Alt. 2311630-17, -18) (Alt. 2311630-23, -24)

Main Gear Door and

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 3 of 6) 51-71-20

Fage3 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

NIFD ITEM I

I

I

I

EFF.

Bolt- AN23-19

1

H, J I

1

Bushing-231162&7

1

H, J

1

1

Lever- 2311628-1, -2, -9 -10, -001, -002 Bolt-AN24-17

18

MFD 1 MFD I SHAFT

ID

DESCRIPTION

NO.

HOLE

HOLE

OD

ID

OD

1

A1IOWAtJCE

WEAR I

ID

ALLOWA~JCE OD

1 +0.0000/

0.1860

1

0.2500

+0.0050/ -0.0010 1 +0.0050/ -0.0010

0.2480

1

-0.0020 19 20 21

0.1 930 0.2570

J

I G

1

1

I I

1

M.0100

1 +0.00001 -0.0020

22

Support, Actuator2348044-1, -2

1

K K

23

Bolt-AN26-21

1

24

Spacer- NAS43HT6-13

1

I

Main Gear Door and

EFFECTIVITY:

ALL

0.3750

1

1

0.3730

1

1

0.4270

0.51 50

1 +0.0060/ -0.0012 1 +0.0000/ -0.0020 +0.0000/ +0.0000/ -0.0400 1 -0.0300

Uplatch Allowable Wear and Repair Figure 1 (Sheet 4 of 6)

Data

51-71-20

Page 4 sRM-a

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

lr Plate, Adjustab\e- 2327021-3 2 3 4

Bolt Bolt

NAS464P4-14 AN174HC12A Actuator Support Plate

2311623-27,

IHOLE

1

A

1

A

1

B

1

B

REPAIR

Replacewompart. Replace worn part. Replace worn part. Replace worn part.

-28 5

1 Fitting-2322522-1

7

Bolt AN174-12A Rod End DREM-4-050

8

Bolt

9

Deleted

6

1

CJReplacewompart.

1

C

1

C

1

C D

(Alt. ARYHT4E)

10 11

12

13 14 15 16

17

NAS464P4-A22, -23, -A23

Bracket Assy. 2348042-1, -2 Bolt AN24-36 Bracket Assy. 2348041-1, -1 Bushing 6L6-F Bushing NAS75-4-122 BoR- AN24-36 Roller- 2317060´•6

Spacer-2317065-4 Bushing- 6L8-D 1 BracketAssy-2311630-11, (Alt. 2311630-13, -14) (Alt. 2311630-17, -18)

1

E E

1

F, G

1

F

1

F

1

G(Replacewompart. I Replacewompart. I Replacewompart. I Replacewompart.

1

I

1

1 1

-12

I I

20 21

Bolt

AN23-19

1 Bushing- 231162&7

Replace worn part. Replace worn part.

H

1

I

H H

H, J H, J(

1 1

part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replacewompart. Replace worn part.

Lever

1

J

Bolt- AN24-17 Actuator-

1

GIReplacewompart.

2348044-1,-2

1

K

1

K

2311628-1, -2, -9, -10, -001, -002

22

Support,

23

Bolt

24

Replace worn Replace worn Replace worn Replace worn Replace worn

H

1

(Alt. 2311630-23, -24) 18 19

Replace worn part. Replace worn part. Replace worn part. Replace worn part.

NAS464P6-16 Spacer- NAS54HT6-13

Main Gear Door and

EFFECTNITY:

ALL

1

I

I

Replace worn part Replace worn part. Replacewompart.

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 5 of 6) 51-71-20

Page 5 SRM-4

Jun 6/98

Learjet i

STRUCTURAL REPAIR MANUAL CODES 1 2

3 4

5

6

EFFECTIVITIES 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 31001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099 When Equipped With Goodrich Brakes 23-011 thru 23-099 When Equipped With Goodyear Brakes 24-330 thru 24-340 Except Aircraft Modified by AAK 78-03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 25-206 thru 25-213 Except Aircraft Modified by AAK ~&OSA,"Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 35-067 thru 35-091 Except Aircraft Modified by AAK 7&03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 36-018 thru 36-023 Except Aircraft Modified by AAK 78-03A,

"Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing" 24-100 thru 24-329, 24341 and Subsequent and 24-330 thru 24-340 When Modified by AAK 7& 03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 25-001 thru 25-205, 25-214 and Subsequent and 25-206 thru 25-213 When Modified by AAK 78-03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 2&001 and Subsequent; 29-001 and Subsequent; 31-001 thru 31-121, 31-135 and Subsequent; 35001 thru 35-066, 35092 and Subsequent and 35-067 thru 35-091 When Modified by AAK 78-03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing"; 36-001 thru 36-017, 36-024 and Subsequent and 36-018 thru 36-023 When Modified by AAK 78-03A, "Replacement of Main Landing Gear Strut Piston Assembly for Improved Snubbing" 31-122 thru 31-134

Main Gear Door and

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 6 of 6)

1 51-71-20

Page 6 SRM-4

Tun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

MAIN GEAR SHOCK STRUT

A oi

E

c

\F

i

/P

N

8’

/Q Detail A

Main Gear Shock Strut

Allowable Wear and

Figure EFFECTIVITY:

ALL

1 (Sheet 1 of

Repair Data

5)

51-71-211 Pagel

SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

NO.

1

I DESCRIPTION

Arm

Torque

I

HOLE

I

EFF.

HOLE

ID

2

E

0.7200

MFD

MFD

ALLOWANCE

I

OD

ID

OD

0.9383

+0.0050/

+0.0010/ -0.0000

-0.0000

E

3

2341126-2

0.7505

+0.0010/

0.9383

-0.0000

Torque

ALLOWANCE

ID

OD

Bushing

2341126-1

2

WEAR

I SHAFT

Arm

+0.0010/ -0.0000

0.7525

Bushing

2341120-1

4

F

0.7200

0.8765

+0.00501 -0.0000

lt0.0005

5

F

0.7200

0.9078

+0.00501 -0.0000

M.0003

4

F

Torque Arm Bushing 2341120-2 3

Upper Torque

Arm Pin

2341118-1

I

1

0.7500

1

1 +0.000011

1 0.7440

-0.0005

314111&1 4

F

1

G

0.5320

0.6892

+0.0050/ -0.0000

+0.0000/ -0.0005

6

H

0.7200

0.8765

+0.0050/

M.0005

I

1

0.7500

1

1 +0.0000/ -0.0005

Torque Arm Bushing 2341127-1, -3, -4

5

5

Torque Arm Bushing 2341120-1

-0.0000 7

H

234111&1

6

H

I

1

0.7500

1

314111&1

7

H

I

1

0.7500

1

2341120-2 6

Lower

Torque Arm

0.7200

+0.0050/ -0.0000

0.9078

f0.0003

Pin

1 0.7440

1 +0.0000/ 1 -0.0005 1 +0.0000/ -0.0005

7

Torque Arm Apex

Pin

J

1

234112&1

0.3750

0.5620

+0.0100/ -0.0000

8

Torque Arm Bushing 2341127-1

4

1

J

0.5320

0.6892

+0.0050/ -0.0000

2341127-2

5

J

0.5320

0.7045

+0.0050/ -0.0000

Main Gear Shock Strut

Allowable Wear and

Figure

I

1 0.5580

+0.0000/1 -0.0005

ALL

1

+0.0000/ -0.0005

0.5660

+0.0000/ -0.0005

0.5660

Repair Data

(Sheet 2 of 5)

51-n-21

Fage 2 SRM-I

Tun 6/98

Learjet ~jLearjetl

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I DESCRIPTION

NO.

Strut Assy. Fwd Trunnion Pin Hole

9

I

MFD SHAFT OD

HOLE

ID

1

K

1.2608

1

1.1260

i

I

125 RMS) Bearing (Finish 125 RMS) Axle(Outer Ends) (Finish 32 RMS)

MFD HOLE

EFF.

L

1

Aft Trunnion Pin Hole in Strut

I

I

I

MFD

I

ID

1

1.2620

1

1.1280

1 +0.0000/ 1 1 1 -0.0020 1 1 +0.0000/

3.0080

ID

OD

1 +0.00001 1 -0.0010 1 +0.00001 i 1 -0.0010

I

WEAR

ALLOWANCE

ALLOWANCE OD

(Finish

10 11

1 I

12

13

1

I

32

I N

1

I

PistonHead

(Finish

M

1

Lower

I P

1

RMS)

I

Cylinder (Finish 16 RMS) Cylinder(Finish 63 RMS)

I Q

1

Piston

I

I 1

3.0020

1

I

I

I

1

I

I

I

1

I

I

I

1

I

I 1

1 +0.0000/ 1

Q

3.2520

1.4998 3.2480

2.9980

I

1

1

1 +0.0000/ i

I

1

1

1 +0.000/ 1

I

1 -0.0020

1 1.4970

-0.0010

1 3.2400

-0.0040

1

1 2.9945 3.2560

-0.0020

Main Gear Shock Strut

Allowable Wear and

Figure EFFECTIVITY:

ALL

1

Repair Data

(Sheet 3 of 5)

51-71-211 Page 3

SRM-I

Jun 6/98

Learjet tearjetl STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

HOLE

2

E

3

E

REPAIR

Torque Arm Bushing

1

2341126-1

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

2

2341126-2 Torque Arm Bushing

4

F

5 4

F

3

Torque Arm Bushing 2341120-2 Upper Torque Arm Pin 2341 1 18-1

5

F

4

314111&1 Torque Arm Bushing 2341127-1 Arm Bushing

1

G

2341120-1

6

H

2341120-2

7

H

6 7

H H

Replace worn part. Replace worn part.

1

J

Replace

4

J

5

J

Replace worn part. Replace worn part.

1

K

1

L

1

M

1

N P

5

6

7

8

9

1

2341120-1

F

I

Replaceworn part.

Torque

Lower Torque Arm Pin 234111&1 314111&1 Torque Arm Apex Pin 234112&1 Torque Arm Bushing 2341127-1 2341127-2 Strut Assy. Fwd Trunnion Pin Hole Aft Trunnion Pin

(Finish

125

10

Axle

11

Piston Head

12

Piston

13

Cylinder (Finish

I

1

Q Q

1

Cylinder 63

1

RMS)

Main Gear Shock Strut

part.

j~

Replace wom part. Replace worn part. Replace worn Replace worn Replace worn Replace worn Replace worn

Allowable Wear and

Figure ALL

worn

RMS)

Bearing (Outer Ends)

Lower

IEFFECTnrITY:

Replace worn part. I! Replace worn part. I!

part. part. part. part. part.

Repair Data

1 (Sheet 4 of 5)

51-71-21

PageB SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35-0b1 and Subsequent; 36-001 and Subsequent

2

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and and Subsequent; 31-001 thru 31-003; 35-001 thru 35-642; 36-001 thru 36-057

3

31-004 and

Subsequent;

29-001

Subsequent; 35-643 and Subsequent; 36-058 and Subsequent and Prior Aircraft Equipped With 2341126-2 Bushing 23-001 thru 23-099; 24-100 and Subsequent; 25001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 31-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 35-001 thru 35-629; 36-001 thru 36-058 31-001 and Subsequent; 35-630 and Subsequent; 36-059 and Subsequent

4

5

6 7

NOTES:

Line

ream

bushings to 0.7505 (+0.0005/-0.0000) after installation.

Line

ream

bushings to

0.5625

(+0.0005/-0.0000) after installation. (Finish

Main Gear Shock Strut

Allowable Wear and

Figure EFI:;ECTIVlTY:

ALL

1

32

RMS)

Repair Data

(Sheet 5 of 5)

51-71-211 Page 5

SRM-4

Jun 6/98

Learjet ~ii

STRUCTURAL REPAIR MANUAL NOSE GEAR SHOCK STRUT

ALLOWABLE WEAR AND REPAIR DATA

~t;

Qb

:t .~a

I

.F

E

3

G

I

1

A620C

Detail A Nose Gear Shock Strut

Figure EFFECTIVITY:

ALL

Allowable Wear and 1

(Sheet

Repair Data

1 of 3)

51-71-22( Page 1

SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 1

I DESCRIPTION Axle-2342117-1

I

I

EFF.

HOLE

1

D

MFD

MFD

HOLE

SHAFT

ID

I

MFD

I

OD

I

1

1.4998

1

WEAR

ALLOWANCE

ID

ID

OD

1 +0.0000! 1

ALLOWANCE OD

1 1.4980

-0.0010 2

Cylinder- 23421 02-1 2342100-2042-1 thru -12 2342101-1

3

Torque Block

4

Cam Follower-2342106-1 23421 06-3 2342100-2043-1 thru-12

5

Upper Cam 2342103-1

1

E

3.0000

1

2

E

3.0000

1

1

F

12200

1

2.5000

1 I 1

G

1

1

I

I

2

G

1

H

2.5000

I

1

1 +0.0020/ 1 -0.0000 1 +0.002011 -0.0000 1 +0.0010! 1 -0.0000 1 +0.00201 1 1 -0.0000 1 +0.0020/ 1 -0.0000 2.9970

1

1

3.0060

1

3.0060

1

1.2230

1

2.5060

1

2.5060

1 +0.0000/ 1

1 2.9910

-0.0020

6

Orifice Tube

2342113-1~

7

J

I

1

1.2180

1

1202-6

3

1

J

I

1

1.2180

1

2481030-2

4

1

J

I

1

1.2180

1

1 +0.00001 1 -0.0010 1 +0.0000/ 1 -0.0010 1 +0.0000/ 1

1 1.2160 1 1.2160

1 1.2160

-0.0010

1202-26A

5

1

J

I

1

12180

1

1 +0.0000/ 1

1 1.2160

-0.0010 2380032-30

6

J

I

1

1.2180

1

1 +0.0000/ 1

1 1.2160

-0.0010 7

Piston-2342104-1

1

K

I

Nose Gear Shock Strut

1

ALL

1

Allowable Wear and

Figure

IEFFECTIVITY:

2.4940

1

1 +0.0000/ 1 -0.0020

1 2.4950

Repair Data

(Sheet 2 of 3)

51-n-22

Page 2 slhw

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO. 1

Axle

2

Cylinder

3

Torque Block

4

Cam Follower

5

Upper Cam

6

Orifice Tube

2342117-1

2342102-1

2342100-2042-1 thru -12 2342101-1

i

2342106-1, -3

2342100-2043-1 thru -12

1

D

1

E

2

E

1

F

1 2

G G

1

H

7

J

12-02-6

3

J

2481030-2

4

J

1202-26A 2380032-30

5 6

J J

1

K

Piston

7

HOLE

CODES

2342103-1

2342103-1

2342104-2

REPAIR

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

EFFECTIVITIES

1

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

2

25-001 and Subsequent; 2&001 and Subsequent; 29-001 and Subsequent; 35-134 and Subsequent and Previous Aircraft Modified by SSK 973, "Replacement of Main Landing Gear Bushing and Pin"; 36-035 and Subsequent and Previous Aircraft Modified by AAK 90-02, "Replacement of Variable Au-

thority Nose Wheel Steering Component’ 3

23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051, 23-055, 23-060, 23-065, 23-087,

4

23-011, 23-012, 23-015, 23-019, 23-031, 23-043, 23-050, 23-051, 23-055, 23-060, 23-065, 23-087,

5

23-026 and

and 23-096 Unless Mod 2 Is Steel

Stamped On Name Plate

and 23-096 When Mod 2 Is Steel

Stamped On Name Plate Subsequent Except 23-031, 23-043, 23-050, 23-051, 23-055, 23-060, 23-065, 23-087; 24-001 and Subsequent 24-001 and Subsequent; 25-002 and Subsequent Except Aircraft Equipped With Variable Nose Wheel Steering 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29-001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent

6 7

NOTES:

At

bearing

surface of square

parts (not diameter)

Nose Gear Shock Strut

Allowable Wear and

Figure EFFECTIVITY:

ALL

Repair

Data

1 (Sheet 3 of 3)

51-71-22( Page 3

SRM-4

Jun 6/98

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL MAIN GEAR ACTUATOR

ALLOWABLE WEAR AND REPAIR DATA

A

A

I

I

B

I

K

u

\G I

F

Ij

3

/;6

D M

(TYPICAL)

B 14-90C-2

Main Gear Actuator

A63C-1 Awc

EFFECTIVITY:

Detail A Allowable Wear and

Figure ALL

1

Repair

Data

(Sheet 1 of 3)

51-71-23

Pagel SRM-I

Jun 6/98

1

Learjet e~Learjetl STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

NO.I 1

I

I

DESCRIPTION

Cylinder- 23271 01-1, -7,

HOLE

1

A

1

-11,-17

Inner Piston

MFD

HOLE

SHAFT

ID

OD

2.2450

I B

2

I

EFF.

MFD

I

1 C

3

2427110-1

2.4360

I

MFD

1 +0.0020/ 1

I

1 1.4870

1

ALLOWANCE OD

1 2.4330

-0.0000 1 +0.0030/ 1 -0.0000

1

ID

OD

ID

1 1

WEAR

ALLOWANCE

1

2.2520

1 +0.0020/ 1

1 1.4840

-0.0000 2

232711 0-1

1

C

I

1

1.4870

1

1 +0.0020/ 1

1 1.4840

-0.0000 3

1

Piston- 2327102-1, -2, -5

D

I

1

2.2430

1

1 +0.0000/

E

I

1

1.8730

1

1 +0.0000/

-0.0010 -0.0020 F

1.4910

1 +0.0020/ 1

1

0.0050

1

-0.0000 4

5

Ball Housing24271 04-1, -2

G

1

1

-003

H

1

Plunger- 2427105-1, -002,

J

6

Housing- 2327108-3,

-7

I

2.8110

I

1

2.4380

+0.0000/ -0.0020

1.8750

2.21 70

1

I

I

1

1 +0.0020/ 1

K

2.2260

1

L

2.8130

1

M

1.876

1

-0.0000 1 +0.0020/ 1 -0.0000 1 +0.0020 1 -0.0000 1 +0.0020 1 -0.0000

Allowable Wear and Figure 1 (Sheet 2 of 3)

Main Gear Actuator

1EFFECTIVITY:

ALL

+0.0020/ -0.0000 1 +0.0000/ 1 -0.0020

1 2.8070

1

2.4420

1

2.2350

1

2.8190

1

1.8850

Repair Data

51-71-23

Page2 SRM-4

Jun 6/98

Laarjet Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO.

Cylinder 2327101-1, -7, -11,

1 2

1

Inner Piston

-17

2427110-1

2327110-1 3

1

Piston-2327102-1,-2, -5

1

A, B

3

C

2

C

1

D E F

4

1

Bail

Housing- 24271 04-1,

1

-2

1

Plunger 2427105-1, -002, -003

5

1 Housing-232710&3,

CODES

1

-7

Replace worn part.

I

Replacewompart.~ Replace

worn

part.

I Replacewompart.~ Replace worn part. Replace worn part.

GIReplacewompart.~ H, J K

6

REPAIR

HOLE

L, M

Replace worn part. Replace worn part. Replace worn part.

EFFECTIVITIES 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent, 29-001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28001 and Subsequent, 29-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 31 -001 and Subsequent and Aircraft Equipped With 23271 01 -1 1 or 23271 01 -1 7 Cylinder Assembly

1 2

3

NOTES:

I~

16RMS. 32RMS. 63RMS. 125 RMS.

Main Gear Actuator

Allowable Wear and

Repair Data

Figure 1 (Sheet 3 of 3) EFFECTIVITY:

ALL

51-71-23

Page 3 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL MAIN DOOR UPLATCH MECHANISM

ALLOWABLE WEAR AND REPAIR DATA

r~´•

B~j A

/i 7 5

/s

t

Fi A

ii

10

Main Door

EFFECTIVITY:

ALL

’7

Uplatch Mechanism Allowable Wear and Repair Data Figure 1 (Sheet 1 of 3)

51-71-241 Pagel

SRM-I

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

I

I

MFD

MFD

HOLE

SHAFT

MFD

ALLOWANCE

EFF.

HOLE

ID

I

LH and RH Cam Bracket Assy- 2348042-1 and-2

1

A

0.2500

1

2

Bolt- AN24-36

1

A

3

LH and RH

1

A

0.2500

1

1

B

0.2500

1

1

C

0.4380

1

Bolt-AN24-17

1

A

I

1

0.248

1

1 +0.0000/

5

Bolt- AN24-36

1

B

I

i

0.248

1

1 +0.0000!

6

Bushing- NAS75-4-122

1

C

7

Bushing, Nylinder-

8

Spacer- 2348041-10

1

B

9

Roller- 231 7060-6

1

B

DESCRIPTION

NO.

1

OD

I

ID

OD

WEAR ID

ALLOWANCE OD

1 +0.00501 -0.0010

Assy-

I

1

0.2480

1 +0.0000/ -0.0020

i

Cam

Uplatch

2348041-1 and-2

i +0.00501 -0.0010 1 +0.0050/ -0.0010

1+0.00101 -0.0000

4

1

-0.0020 -0.0020

8L6F

1

1

0.3716

+0.00151 -0.0000

0.250

0.313

+0.0050/ -0.0010

0.385

0.562

+0.00001

0.250

I

+0.0000/ -0.0005

I ~0.0100

-0.0010

10 11

1 Spacer- 2317065-4 Bushing- 6L8D

Main Door

I

EFF~CTIVITY:

ALL

1

B

1

B

0.375

0.297

I

+0.0000/ -0.0410

+0.0000/ -0.0100

I

Uplatch Mechanism Allowable Wear and Repair Data Figure 1 (Sheet 2 of 3) 51-71-24

Page 2 SRM-I

Jun 6/98

Leariet ~Learjet STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM EFF.

DESCRIPTION

NO.

HOLE

REPAIR

LH and RH Cam Bracket

1

1

A

1

A

1

A

1

A

7

Assy 2348042-1 and -2 Bolt AN24-36 LH and RH Uplatch Cam Assy 2348041-1 and -2 Bolt AN24-17 Bolt AN24-36 Bushing NAS75-4-122 Bushing, Nylinder 6L6-F

8

Spacer

9

Roller

2

3 4 5

6

2348041-10

2317060-6

Spacer Bushing

10 11

CODES

2317065-4 6L8D

1

B

1

C

1

C

1

B

1

B

1

B

1

B

Replace Replace

worn worn

part. part.

Replace worn pact. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

EFFECTIVITIES 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

1

NOTES: Product of Industrial

Bearing

Main Door

EFFECTIVITY:

ALL

8

Transmission, 325 N. St. Francis, Wichita, KS 67202.

Uplatch Mechanism Allowable Wear and Repair Data Figure 1 (Sheet 3 of 3)

51-71-241 Page 3

SRM-4

Jun 6/98

Learjet i

STRUCTURAL REPAIR MANUAL ALLOWABLE WEAR AND REPAIR DATA

NOSE GEAR ACTUATOR

B\,

A

o

~4a

A

f CI~YPICAL)

1/

,3

Detail A 1

Detail E

a

t E

f A

ji~

1

Detail D

,_

Detail C Nose Gear Actuator

Allowable Wear and

Figure

EFFECTIVITY:

ALL

Detail B

1

(Sheet

1 of

Repair Data

3)

51-71-251 Pagel

SRM-I

Jun 6/98

Ledrjet I E~ Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

I

I

HOLE

MFD

MFD

WEAR

ALLOWANCE

ALLOWANCE

I SHAFT

ID

HOLE

EFF.

DESCRIPTION

NO.

I

OD

I

0.4358

1

ID

OD

ID

OD

Upper Attach Bolt

1

NAS464P7L53

1

I

I

1

1 +0.0009/ 1

1+0.43301

-0.0000

Lower Attach Bolt NAS464P7L20 2

1

1

i

1

0.4358

1

1 +0.000911

1+0.4330/

-0.0009

-0.0000

CylinderAssembly2

1202-202

3

231 7101-12 3

i

1

(Alt. 2317101-13) Plunger-1202-209

2

1

1

1.4360

1.6270

1

1

I

I

I

I

1

C

1.4360

1.6270

1 1.9900

+0.0000/

+0.0000/

-0.0020

-0.0020

+0.0000/ -0.0020

+0.0000/ -0.0020 1 +0.0000/ 1

1

1.4400

1.4400

1.4400

1.4400

1

1.9890

1

1.6330

1

1.9890

1

1.6330

1

1.4300

1

1.2200

-0.0020 D

I

1

1.6310

1

1 +0.0000/ 1 -0.0020

3

2317105-1, -002

C

I

1.9900

1

1 +0.0000/ 1

1

-0.0020 D

I

1

1.6310

1

1 +0.0000/ 1 -0.0020

4

2

Piston-1202-204

E

I

1

1.4340

1

i +0.0000/ i -0.0020

F

i

1

1.1240

1

1 +0.0000/ i -0.0020

G

2317102-1, -2, -5

3

i I

1 1

1.1240

E

1.4340

1 1

F

I

i

1.1220

1

1 +0.0000/ 1 1 +0.0000/ 1 -0.0020 1 +0.0020/ 1

1 1.2200 i 1.4300 i 1.2200

-0.0000

G

I

1

1.1240

1 +0.0000/ 1

1

1

1.2200

-0.0020 5

6

Downlock Ball

Housing

1202-207

2

A

1.1260

1

2317104-1

3

A

1.1260

1

2

B

1.9920

1

A

1.1270

1

B

1.9920

1

Housing-1202-211A

2317108-1, -3, -8

3

1 +0.0020/ -0.0000 1 +0.0020/ -0.0000 1 +0.0020/ -0.0000 1 +0.0000/ -0.0020 1 +0.0020/

1

1

1.1300

1

1

1.1300

1

1

1.9970

1

1

1.1310

1

1

1.9970

1 +0.0000/ i

i

1.1310

-0.0000 A

1.1270

1

-0.0020

Nose Gear Actuator

Allowable Wear and

Repair Data

Figure 1 (Sheet 2 of 3)

IEFFECTnrITY:

ALL

51-71-25

Page 2 SRM-4

Jun6/98

Learjet Learietl

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

EFF.

DESCRIPTION

NO.

Bolt

NAS464P7L53

1

NAS464P7L20

1

I I

I Replacewompart.~ I Replacewompart.l~

2

1

I

Cylinder Assembly

2

1202-202

3

2317101-12

(Alt. 2317101-13) Plunger 1202-209

3

C

1

D

2317105-1,-002

1

Piston -2317102-2

2

C D

1

4

E F

G E

3

2317102-1, -2, -5

F

G Downlock Ball Housing 2317104-1 Housing -1202-211A

5 6

REPAIR

Lower Attach Bolt

Upper Attach

1

HOLE

1202-207

2

A

3

A B

1

A B

1

231710&3

A

CODES

Replacewompart. Replace worn part. Replace worn part. Replace worn part. Replace worn part. I! Replace worn part. I! Replace worn part. Replace worn part. I! Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. I! Replace worn part. 1! Replace worn part. I! Replace worn part. I! Replace worn part. Replace worn part.

E

EFFECTIVITIES

2

23-001 thru 23-099; 24-001 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-010, 23-013, 23-014, 23-016, 23-017, 23-013, 23-020 thru 23-025 Except Aircraft

3

23-011, 23-012, 23-015, 23-019, 23-026 thru 23099 and Aircraft Modified per SSK 23-214; 24-100

1

Modified per SSK 23-214 and Subsequent; 25-001 and and Subsequent; 35-001 and

Subsequent; 2&001 and Subsequent; Subsequent; 36-001 and Subsequent

29-001 and

Subsequent;

31-001

NOTES: 32RMS 16RMS

Nose Gear Actuator

Allowable Wear and

Figure EFFECTIVITY:

ALL

1

Repair Data

(Sheet 3 of 3)

51-71-251 Page3

SRM-4

Jun 6/98

Learjet Learjet

STRUCTURAL REPAIR MANUAL NOSE GEAR UPLATCH

ACLOWABLE WEAR AND REPAIR DATA

00000

LA

~j

B~

(TYPICAL)

Detail A Nose Gear

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 1 of 5) 51-71-26

Page SXM-4

1

Jun 6/98

Leariet

STRUCTURAL REPAIR MANUAL NOSE GEAR UPLATCH

ALLOWABLE WEAR AND REPAIR DATA

00000

B

/13

6\

d Detail B ,1

I

EFFECTNITY:

Nose Gear

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 2 of 5) 51-n-26

Page2 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

NO.I

DESCRIPTION

1

Bolt- AN4-24

I

IEFF.

I HOLE I

MFD

MFD

HOLE

SHAFT

ID

OD

MFD I

ALLOWANCE

ID

OD

4

A

I

1

0.2490

1

1 +0.0000/

5

A

i

1

0.2490 1

1 +0.0000/

WEAR ID

ALLOWANCE OD

-0.0030

AN4-34

-0.0030 2

Spacer- 2317065-1

1

A

0.2970

0.3750

+0.0000/

+0.0000/

3

Roller- 231 7060-2

6

A

0.4445

0.5620

+0.0100

7

A

0.4445

0.5620

+0.00001 -0.0010 +0.00001 -0.0010

1

A

0.2570

0.5620

-0.01 00 +0.0100

8

A

0.2570 1

B

0.1930 1

C

0.2500 1

1 +0.0000/ -0.0090 1 +0.0050/ -0.0000 1 +0.0100

A

0.2570 1

1 +0.0000/

B

0.1930 1

1 +0.0050/

C

0.2500 1

1

-0.0410

231 7060-5 4

Spacer- 23170653

5

Support- 231 7063-1,

-4

-6,-8

(Slot)

+0.0060/ -0.0010

-0.0100

-0.0100 +0.0100

-0.0100

-0.0100

2442010-1,-7

9

(Slot)

-0.0090 -0.0000 +0.0100 -0.0100

6

Bolt- NAS464P4-37

1

71

NoseGearPistonAssy.

1

C, DI

1

0.2492

1

1 +0.0000/ -0.0009

81Screw-AN509-10Rll

1

D

0.2500 1

E

0.1900 1

B, El

1 +0.0010/ -0.0000 1 +0.0020/ -0.0000

1

0.1890 1

1 +0.0000/

1

0.3742 1

1 +0.0000/

-0.0030 9

Bolt- NAS464P6-8

1

F

I

-0.0009 10

1

Bearing-MS21233-6

1

F

0.3750

11

I

RodEnd-MS21243604K

1

G

0.2500 1

12

1

Bolt-NAS464P4-8

1

G

I

0.81 25

1

+0.0000/ -0.0005 1 +0.0000/ -0.0005

0.2492

1

+0.0000/ -0.0005

1 +0.0000/ -0.0009

Nose Gear

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 3 of 5) 51-71-26

Page3 SRM-4

Jun 6/98

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

MFD ITEM I

DESCRIPTION

NO. 13

I

I

MFD

HOLE

SHAFT OD

EFF.

HOLE

ID

1

H

0.7491

1

H

0.3125

MFD

ALLOWANCE

ID

1

1

OD

WEAR ID

ALLOWANCE OD

1 +0.0010/

i

-17,-23

15

I

1 Torque Tube Assy, Nose Gear Uplatch 231 7029-1, -11,-16,

14

I

Bearing- LHBV-5 (Alt. KSBG-5N) (Alt. LHBRQ) (Alt. MS21233-5) Pivot-2317058-2

-0.0000

I

1

J

0.7500

I

I

I

1

1

0.3110

1

+0.0000/

+0.0000/

-0.0005

-0.0005

1 +0.0010/ -0.0000

Nose Gear

I

EFFECTIVITY:

ALL

Uplatch Allowable Wear and Repair Data Figure 1 (Sheet 4 of 5) 51-71-26

Page 4 SRM-I

Jun 6/98

Learjet Leariet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

HOLE

2

A

3

A A A A A

Bolt AN4-24 AN4-34

1

Spacer

1

2317065-1 Roller 2317060-2 23170606 Spacer 2317065-3

2

3 4

4

5 1

1

8

Bolt NAS464P4-37 Nose Gear Piston Assy. Screw AN509-10R11

1

A, B, C A, B, C C, D D, E B, E

9

Bolt

1

F

1

F

Support 2317063-1, -4, -6, Support 2442010-1, -7

5 6 7

-8

6 7 1

NAS464P6-8 Bearing- MS21233-6

10

REPAIR

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Install

new

bearing with

Loctite. MS21243S04K NAS464P4-8 Torque Tube Assy., Nose Gear Uplatch

11

12

13

G G

Replace worn part. Replace worn part.

1

H H

Replace worn part. Replace worn part. Install new bearing with wet primer, exterior surface only.

1

J

Replace worn part.

Rod End

1

Bolt

1

1

2317029-23 14

1 Bearing- LHBV-5 (Alt. KSBG-5N) (Alt. LHBR-5)

15

1

(Alt. MS21233-5)

CODES 1 2

Pivot -231705&2

EFFECTIVITIES 23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 2&001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35001 and Subsequent; 36-001 and Subsequent 23-001 thru 23-059 Except Aircraft Modified by SK 23-129, "lnstallation of Nose Gear Uplatch Safe-

ty Cam" 3

23-060 and

Subsequent

and Aircraft Modified

by SK 23-129, "lnstallation of Nose Gear Uplatch

Safety Cam" 4

23-003 thru 23-010, 23-013, 23-014, 23-016 thru 23-018, 23-020 thru 23-030, 23-032 thru 23-038, 23-040 thru 23-042, 23-044 thru 23-049, 23-050a, 23-052 thru 23-054, 23-056 thru 23-059, 23-061

thru 23-064, 23-065a thru 23-086, 23-088 thru 23-095, 23-097 and fied per ECR392 5

Subsequent Except Aircraft

Modi-

23-011, 23-012, 23-015, 23-019, 23-031, 23-039, 23-043, 23-050, 23-051, 23-055, 23-060, 23-065, 23-087, 23-096 and Model 23 Series Aircraft Modified by ECR392; 24-100 and Subsequent; 25-001 and

Subsequent, 2&001 and Subsequent, 29-001 Subsequent; 36-001 and Subsequent

and

Subsequent;

31-001 and

Subsequent;

35-

001 and 6 7

23-001 thru 23-099; 24-100 thru 24-223; 25001 thru 25-059 24-224 and Subsequent; 25060 and Subsequent; 2&001 and

Subsequent;

29-001 and Subse-

quent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

Nose Gear

Uplatch

Allowable Wear and

Repair

Data

Figure 1 (Sheet 5 of 5) ALL

51-n-26

Page 5 SRM-4

Jun 6/98

Learjet Lenrjet

STRUCTURAL REPAIR MANUAL NOSE GEAR DOOR MECHANISM

O [I)

ALLOWABLE WEAR AND REPAIR DATA

000

P

A

3

5J /Y

1,

9

10

e

B 11

‘4

G 3 E 12 5

16

ij i

15/ 11

CA

10

16

(TYPICAL)

Detail A I-tlC

Nose Gear Door Mechanism

Figure EFFECTIVITY:

ALL

Allowable Wear and

Repair Data

1(Sheet lof4) 51-71-27

Pagel SRM-4

Jun 6/98

0

Learjet STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I

DESCRIPTION

NO.I 1

Pivot-231705&1

2

Channel

I

I

EFF.

HOLE

1

A

MFD

MFD

HOLE

SHAFT

ID

OD

I

1

0.3110

MFD

WEAR

ALLOWANCE

ID

1

OD

I

ID

ALLOWANCE OD

1 +0.0010/ -0.0000

Assy. B

0.2500

1

1 +0.0050/

C

0.4991

1

-0.0010 1 +0.00151

B

0.2500

1

1 +0.0000/

(Alt. MS21242S4)

B

0.2500

i

1 +0.0000/

(Alt. KBNE-4)

B

0.2500

1

1 +0.0000/

1

2317045-8, -9, -10

-0.0000

Rod End

3

MS21242-4

1

-0.0005 -0.0005 -0.0005 4

Bolt- AN24-32

1

B

I

1

0.2480

1

5

Bolt- AN24-15, -22

1

B

I

1

0.2480

1

6

Bolt- NAS464P8-33, -36,

C

I

1

0.4991

1

-0.0020 1 +0.0000/ -0.0020 1 +0.0000/

I

I

I

1 -0.0009

1

1 +0.0050/

1 1

-40

I

1 +0.0000/

Torque Tube Assy.

7

2317047-9,-11

D

1

E

0.2500

-0.0010

Bearing- LHBV-5 (Alt. RSST-5) (Alt. LHBR-5) (Alt. MS21233-5)

8

D

D D

(Alt. KSBGQN) TorqueTubeAssy.-

9

231 70481

D

1

0.3125

F

1

i

1 Bearing-LHBVd (Alt. KSBG-5N)

I

1

12

+0.0000/ -0.0005

0.7510

1 I

0.2500

1

I

1 +0.0050/ 1 -0.0000 1 +0.0050/ -0.0010

F F

(Alt. LHBR-5) (Alt. MS21233-5) 11

+0.0000/ -0.0005

D

G 10

0.7500

F F

0.3125

0.7500

+0.0000/ -0.0005

+0.0000/ -0.0005

Rod End -2317046-9 Bolt- AN24-22

1

E

1

E

I

1

0.2480

1

1 +0.000/

Bolt-AN24-15

1

E

I

1

0.2480

1

1 +0.0000/

-0.0020

13

1

-0.0020

Nose Gear Door Mechanism

Figure

I

EFFECTIVITY:

ALL

Allowable Wear and 1

(Sheet

2 of

Repair

Data

4)

51-71-27

Page 2 SRM-4

Jun 6/98

Learjet

STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I NO. 14

1

i DESCRIPTION Rod End-HMV4

I

I

EFF.

HOLE

1

15

Bolt- AN24-15

1

G G G G G

16

Bracket- 2310620-14

1

H

Rod End-HMV4 (Alt. HMV V4)

1

H

(Alt. HMV-V4) (Alt. REM-4T) (Alt. TRE-4T)

MFD

MFD

HOLE

SHAFT

ID

OD

I

0.2480

1

I

1

MFD

ALLOWANCE

ID

OD

WEAR I

ID

ALLOWANCE OD

1 +0.0000/ -0.0020

0.2500

1

1 +0.0050/ -0.0010

17

1

H

(Alt. REM-4T) (Alt. TRE-4T) 18

1

H H

Bolt- NAS464P4-12

1

H

1

0.2492

1

1 +0.0000/ -0.0009

Nose Gear Door Mechanism

Figure EFFECTIVITY:

ALL

Allowable Wear and

Repair Data

1 (Sheet 3 of 4)

51-71-27

Page 3 SRM-I

Jun 6/98

Learjet Learjet/

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

1

Pivot

2

Channel Assy. 2317045-8, -9, -10 Rod End MS21242-4

3

2317058-1

1

A

1

B, C

1

B B

(Alt. MS21242S04) (Alt. KBNE-4)

B

AN24-32

1

B

AN24-15, -22 NAS464P8-33, -36, -40

1

B

1

C

6

Bolt Bolt Bolt

7

Torque Tube Assy. 2317047-9, -11

1

D, E

8

Bearing LHBV-5 (Alt. RSST-5) (Alt. LHBRd) (Alt. MS21233-5) (Alt. KSBG-SN) Torque Tube Assy.

1

D

4 5

9

D D

D D

2317048-1 10

1 Bearing-

LHBV-5

(Alt. LHBR-5)

1

F, G

1

F

I

I

Rod End -2317046-9 Bolt AN24-22 Bolt AN24-15 Rod End HMV4

12 13 14

F 1

E

1

E

1

E

1

1

G G G G G H

1

H

(Alt. HMV-V4) (Alt. REM-4T) (Alt. TRE-4T) Bolt AN24-15 Bracket 2310620-14 Rod End HMV4

15

16 17

1

H

(Alt. HMV-V4) (Alt. REM-4T) (Alt. TRE-4T) Bolt

18

CODES 1

NAS464P1-12

H H H

1

part. part. part. part. part. part. part. part.

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

part. part. part. part. part. part.

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

23-001 thru 23-099; 24-100 and Subsequent; 25-001 and Subsequent; 28-001 and Subsequent; 29001 and Subsequent; 31-001 and Subsequent; 35-001 and Subsequent; 36-001 and Subsequent

Figure EFFECTIVITY:

Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn Replace worn

EFFECTIVITIES

Nose Gear Door Mechanism

I

F

F

(Alt. MS21233-5) (Alt. KSBG-5N) 11

REPAIR

HOLE

EFF.

DESCRIPTION

NO.

ALL

Allowable Wear and

Repair

Data

1 (Sheet 4 of 4)

51-71-27

Page4 sRM-4

Jun 6/98

~3 Learjet I STRUCTURAL REPAIR MANUAL FLAP PRESELECT ASSEMBLY

ALLOWABLE WEAR AND REPAIR DATA

A

C/ 4

’6~‘b x

B

6

F

Detail A M31-8151A

EFFECTIVITY:

Flap Preselect Assembly Allowable Wear and Repair Figure 1 (Sheet 1 of 3) 31-001 AND

SUBSEQUENT;

36-054 AND SUBSEQUENT SRM-4

35-509 AND

SUBSEQUENT;

Data

51-71-28

Page

1

Jun 6/98

Learjet ~1 STRUCTURAL REPAIR MANUAL WEAR ALLOWANCES

ITEM I

I EFF.

DESCRIPTION

NO.

1

Handle-2615269-5

1

I

I HOLE I

MFD

MFD

HOLE

SHAFT

ID

OD

A

0.3750

1

B

0.1250

1

0.1 890

MFD

WEAR

ALLOWANCE

ID

OD

I

ID

ALLOWANCE OD

1 +0.00201 -0.0000 1 +0.00201 -0.0000

2

Frame- 2615269-16

1

C

3

Screw- NAS1203-110

1

D

I

1

0.1895

4

Bushing-261526&3

1

A

I

0.3735

5

Link- 261 5269-32

1

E

0.1250

1 1

F

0.1250

1

1

1 +0.0000/ -0.0010

1 +0.0020/ -0.0000

1 +0.00201 -0.0000

6

1

Pin- MS20392-1C13

1

E

I

1

0.1240

1

1 +0.00001

Pin-MS20392-1 C7

1

F

I

1

0.1240

1

1 +0.00001

-0.0020 7

-0.0020

Flap Preselect Assembly Allowable Wear and Repair Data Figure 1 (Sheet 2 of 3)

I

EFFECTIVITY:

31-001

ANDSUBSEQUENT; 35-509ANDSUBSEQ~TENT; SUBSEQUENT

36-054 AND SRM-I

51-n-28

Page 2 Jun 6/98

Leariet ~Learjet

STRUCTURAL REPAIR MANUAL REPAIR DATA

ITEM

DESCRIPTION

NO.

EFF.

Handle 2615269-5 Frame 2615269-16 Screw NAS1203-110 Bushing 261526&3 Link 2615269-32 Pin MS20392-1C13 Pin MS20392-1C7

1 2

3 4

5

6 7

CODES 1

REPAIR

IHOLE

1

A, B

1

C D

1

A

1

E,

1

1

E

1

F

F

Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part. Replace worn part.

EFFECTIVITIES 31-001 and

Subsequent;

35509 and

Flap Preselect Assembly

Subsequent;

36-054 and

Allowable Wear and

Subsequent

Repair Data

Figure 1 (Sheet 3 of 3) EFFECTIVITY:

SRM-4

31-001 AND

SUBSEQUENT; 35-509 AND SUBSEQUENT;

36-054 AND

SUBSEQUENT

51-71-28

Page 3 Jun 6/98

CHAPTER

DOORS

Learjet Leariet

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject DOORS-STRUCTURAL IDENTIFICATION

Description

Page

....52-00-00 1

......................,.....................................................................................................52-00-00

PASSENGER/CREW UPPER DOOR (24-Inch Door) STRUCTURAL IDENTImCATION..............................................................................52-10-00

Description Passenger/Crew Upper (24-Inch) Door Structure Repair Index

.52-10-00

1 1

....................................52-10-00

PASSENGER/CREW UPPER DOOR (36-Inch Door)STRUCTURAL IDENTIFICATION..............................................................................52-10-00

Description Passenger/Crew Upper (36-Inch) Door Structure Repair Index

7

............................................................................................................................52-10-00

7

....................................52-10-00

PASSENGER/CREW UPPER DOOR ALLOWABLE DAMAGE.....................................52-10-00 Allowable

Damage Limits

101

....................................................................................................52-10-00

PASSENGER/CREW UPPER DOOR REPAIR

52-10-00 52-10-00

Approved Repairs

201

PASSENGER/CREW LOWER DOOR (24-Inch Door)STRUCTURAL IDENTIFICATION

52-10-10

Description Passenger/Crew Lower (24-Inch) Door Structure Repair Index

1

........................................................................,...................................................52-10-10

1

....................................52-10-10

PASSENGER/CREW LOWER DOOR (36-Inch Door)STRUCTURAL IDENTJFICATION..............................................................................52-10-10 5

Description Passenger/Crew Lower (36-Inch) ............................................................................................................................52-10-10

Door Structure Repair Index PASSENGER/CREW LOWER DOOR ALLOWABLE DAMAGE Allowable Damage Limits PASSENGER/CREW LOWER DOOR REPAIR..................................................................52-10-10

5

....................................52-10-00

...................................52-10-10

101

....................................................................................................52-10-10

Approved Repairs

201

..................................................................................................................52-10-10

EMERGENCY EXIT DOOR

STRUCTURAL IDENTImCATION.....................................

52-20-00 1

Description Emergency Exit Door Structure Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .52-20-0O ....................................................................................................52-20-00

EMERGENCY EXIT DOOR ALLOWABLE DAMAGE Allowable Damage Limits

1 .....................................................52-20-0O

101

....................................................................................................52-20-00

EMERGENCY EXIT DOOR

REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52-20-00 52-20-00

Approved Repairs SERVICE DOORS -STRUCTURAL IDENTIFICATION

Description

1

............................................................................................................................52-40-00

STRUCTURAL IDENTlmCATION................................... TaiIcone Access Door Structure Repair Index.. TAILCONE ACCESS DOOR ALLOWABLE DAMAGE TAJLCONE ACCESS DOOR

Allowable

Damage Limits

TAILCONE ACCESS DOOR

201

.....................................................52-40-0O

52-40-01

52-40-01

1

.52-40-01 101

....................................................................................................52-40-01

REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5240-01

Approved Repairs

................................................................52-40-01

NOSE COMPARTMENT ACCESS DOORS STRUCTURAL IDENTIFICATION .........52-40-05 Nose Compartment Access Doors Structure Repair Zndex..............................................52-40-05

NOSE COMPARTMENT ACCESS DOORS Allowable Damage Limits ....................................................................................................52-40-05

201 1

ALLOWABLE DAMAGE..........................52-40-05 101

52- Contents

SRM´•I

Page 1 May 15/92

~3 Learjet STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject REPAIR

NOSE COMPARTMENT ACCESS DOORS

Approved Repairs

.................;......................................52-40-05

201

.......................................................................................................~..........52-40-05

STRUCTURAL IDENTIFICATION

OIL FILLER ACCESS DOOR

..................................52-40-10

Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52-40-10 ALLOWABLE DAMAGE

1

Oil Filler Access Door Structure OIL FILLER ACCESS DOOR

Allowable

Damage Limits

52-40-10 101

....................................................................................................52-40-10

REPAIR

OIL FILLER ACCESS DOOR

.................................................................................52-40-10

52-40-10

Approved Repairs OXYGEN BOTTLE ACCESS DOOR

STRUCTURAL IDENTIFICATION

Oxygen Bottle (Nose Compartment) Access Door Structure Repair Index. Oxygen Bottle (Dorsal Fin) Access Door Structure Repair Index Damage Limits

201

52-40-15

52-40-15

1 2

...................................52-40-15

OXYGEN BOTTLE ACCESS DOOR

Allowable

Page

ALLOWABLE DAMAGE.......................................52-40-15 101

....................................................................................................52-40-15

OXYGEN BOTTLE ACCESS DOOR

REPAIR

.....................................................................52-40-15

......52-40-15

Approved Repairs.........

201

SINGLE-POINT PRESSURE REFUELING DOOR STRUCTURAL IDENTIFICATION..............................................................................52-40-20

Single-Point Pressure Refueling Door Structure Repair Index........................................52-40-20 SINGLE-POINT PRESSURE REFUELING DOOR

ALLOWABLE DAMAGE

Allowable Damage Limits SINGLE-POINT PRESSURE REFUELING DOOR

REPAIR..............................................52-40-20

1

52-40-20 101

....................................................................................................52-40-20

Approved Repairs Description

201

..............................................~...................................................................52-40-20

MAIN LANDING GEAR DOORS

STRUCTURAL IDENTIFICATZON..........................

52-80-00 1

..........~.................................................................................................................52-80-00

MAIN LANDING GEAR INBOARD DOOR

STRUCTURAL IDENTIFICATION .......52-80-10 Main Landing Gear Inboard Door Structure Repair Index..............................................52-80-10 MAIN LANDING GEAR INBOARD DOOR ALLOWABLE DAMAGE 52-80-10 Allowable

Damage Limits

1

101

....................................................................................................52-80-10

MAIN LANDING GEAR INBOARD DOOR

REPAIR.......................................................52-80-10

52-80-10 STRUCTURAL IDENTIFICATION ...52-80-20 Main Landing Gear Outboard Door Structure Repair Index .52-80-20 MAIN LANDING GEAR OUTBOARD DOOR ALLOWABLE DAMAGE

Approved Repairs.......

201

MAIN LANDING GEAR OUTBOARD DOOR

..........................................52-80-20

Allowable

Damage

Limits

101

....................................................................................................52-80-20

MAIN LANDING GEAR OUTBOARD DOOR

Approved Repairs

REPAIR...................................................52-80-20

201

..................................................................................................................52-80-20

NOSE LANDING GEAR DOOR STRUCTURAL IDENTIFICATION Nose Landing Gear Door Structure Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52-81-00 NOSE LANDING GEAR DOOR ALLOWABLE DAMAGE.............................................52-81-00 Allowable Damage Limits NOSE LANDING GEAR DOOR

Approved Repairs............

1

REPAIR

............................52-81-00

1

52-81-00

101

.52-81-00

201

...........................................................................52-81-00

52- Contents

Page 2 SRM-d

May 15/92

Leariet

STRUCTURAL REPAIR MANUAL Chapter

Chapter

Section

Section Date

Subject

Page 101

1

Jun 1/95

1

2

52-40-00

1

52-Contents 52-0000

2

52-00-00 52-00-00

3

52-40-01 *52-40-01 *52-40-01 52-40-01 52-40-01 52-40-01

1

52-00-00

May 15/92 May 15/92 May 25/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92

201

52-Contents

52-20-00 52-20-00 52-20-00

Page

Subject 52-TITLE 52-List of Eff.

Pgs.

1

4

52-10-00

1

52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 *52-10-10 52-10-10

2

3 4

5 6 7

8 9 10 11

101

102 201 202 1

Jun 1/95

2

May 15/92 Jun 1/95 Jun 1/95

*52-10-10

3

*52-10-10

4

*52-10-10 *52-10-10 *52-10-10 *52-10-10 *52-10-10 *52-10-10 ’52-10-10 *52-10-10 52-10-10 52-10-10 52-10-10 52-10-10 52-20-00 52-20-00

5

6 7

8 9

10 11 12

101 102 201

202 1

2

3

52-20-00 52-20-00 52-20-00 52-20-00

4

5 6

Insert Latest Revised

The

portion of the

text affected

or

3 101 102 201

52-40-05 52-40-05 52-40-05 52-40-05

1

*52-40-10 52-40-10 52-40-10

1 102

52-40-10

201

52-40-15

1

52-40-15

2

101 102

201 101

101

or

102

201 202 1

52-40-20

101

52-40-20

102

52-40-20

201

52-80-00 52-80-10 52-80-10 52-80-10

1

May 15/92 May 15/92 May 15/92 May 15/92 jun 1/95 Jun 1/95 Jun 1/95 May 15/92 May 15/92

May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 Jun 1/95 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 Jun 1/95

May 15/92 May 15/92

May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 Jun 1/95 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92

1 2

103 ~02

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May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92

Asterisk indicates pages revised, added

2

52-40-15 52-40-15 52-40-15 52-40-15 *52-40-20

Jun 1/95 Jun lj95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 May 15/92

Pages; Destroy Superseded

102

Date

201 1 2

101

102 201 1 2

102

102

52-81-00 52-81-00

201

Deleted

deleted

Pages. by current revision.

by the current revision is indicated by a

vertical line in the outer

margin of the

page. 52

Pages Pagel

List of Effective

Jun 1/95 SRM-4

e~ Learjet STRUCTURAL REPAIR MANUAL DOORS- STRUCTURAL IDENTIFICATION i.

DESCRIPTION NOTE:

The the

following structural data covers the basic non-modified aircraft. When applicable, refer to appropriate kit drawing for additions, modifications and changes to the structural compo-

nents and assemblies.

A.

This

Chapter

covers

structural components, allowable

damage limits,

skin gap tolerances, and

repair

of aircraft doors. B.

C. D.

repair index (Figure 1) is incorporated to aid in location of specific component repair indexes throughout this chapter. Allowable damage limits for each door are given in each respective section. Skin gap tolerances for each door are given in each respective section. A door master

Chapter Section

Description

Item

Passenger/Crew Upper Door Passenger/Crew Lower Door

52-10-00

2 3

Emergency Exit Door

52-20-00

4

Tailcone Access Door

52-40-00

5

Nose

6

Oil Filler Access Door

52-40-10

7

Oxygen Bottle Access Door (Nose Cylinder Oxygen System) Oxygen Bottle Access Door (Dorsal Cylinder Oxygen System) Single-Point Pressure Refueling Door Main Landing Gear Doors Nose Landing Gear Doors

52-40-15

1

8

9 10 11

Compartment Access Doors

Master Door

Figure

EFFECTIVITY: SRM~

ALL

Subject

52-10-10

52-40-05

52-40-15

52-40-20 52-80-00

52-81-00

Repair Index

1 (Sheet 1 of 4)

52-00-00

Pagel May 15/92

Learjet Learie~l STRUCTURAL REPAIR MANUAL DOORS- STRUCTURAL IDENTIFICATION

\O

d’

(MODEL 23 SERIES

It

TYPICAL)

(3

QOO

is (MODEL 24 SERIES Master Door

Figure EFFECTIVITY: SRM-4

NOTED

1

TYPICAL)

Repair Index

(Sheet 2 of 4)

52-00-00

Page 2 May 15/92

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL DOORS- STRUCTURAL IDENTTFICATION

000

(MODEL 25 SERIES

TYPICAL)

0000

(MODEL’28/29 SERIES-TYPICAL) Master Door

Figure EFFECTIVITY: srzM-4

NOTED

Repair Index

1 (Sheet 3 of 4)

52-00-00

Page 3 May 15/92

Learjet STRUCTURAL REPAIR MANUAL DOORS- STRUCTURAL IDENTIFICATION

6) (8) (8 1)

(3

00000

2)

~10)

(MODEL 31 SERIES

(4

TYPICAL)

6) 7)

(8

(3

0000

116

(MODEL 35/36 SERIES Master Door

Figure EFFECTIVITY: SRM4

NOTED

TYPICAL)

Repair Index

1 (Sheet 4 of 4)

52-00-00

Page 4 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

i.

STRUCTURAL IDENTIFICATION

DESCRIPTION A.

passenger/crew door is located on the left side of the fuselage in the forward passenger compartment. The passenger/crew door can be either a 24-inch executive door or a 36-inch cargo door. The door consists of an upper door assembly that forms a canopy when open, and a lower door assembly with integral entrance steps.

The

a~

(5)

o

(1

O

8cz o~be

6dd

2-2cne

Em~CTTVITY: SRM4

FWD)

Passenger/Crew Upper (24 Inch) Door Structure Repair Index Figure 1 (Sheet 1 of 6) AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-00

Page 1 May 15/92

~Learieil STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

STRUCTURAL IDENTIFICATION

C777>

44

Is

C> o

O

o

~BG;I

I_

FWDI)

O

2-202C

EFFECTNITY:

Passenger/Crew Upper (24 Inch) Door Structure Repair Index Figure 1 (Sheet 2 of 6) AIRCRAFT EQUIPPED WITH 24

PASSENGER/CREW DOOR SRM~

INCH

52-10-00

Page 2 May 15/92

Learjet

STRUCTURAL REPAIR WIANUAL ITEM

I

NO.

DWG. I NO. I

I DESCRIPTION

Passenger/Crew Upper (24 Inch) Door Assembly

2411495

I

I

EFF.I

MATERIAL

IFINISH

REPAIR

I GAGE I CODE

FIG. NO.

1

1

2411496

Channel

1

2024-T42 Clad

0.050

2

2411496

1

2024-T42 Clad

0.050

1

3

2411496

Angle Angle

2411496 1

Plate

1

2024-T42 Clad 2024-T3 Clad

0.050

4 5

2411496 1

Plate

1

2024-T3 Clad

0.100

1 1 1 1 1

6

2411496 1

Plate

1

2024-T3 Clad

0.100

1

I

Replace Replace Replace Replace Replace Replace

7

2411496 1

Skin

1

2024-T3 Clad

0.040

1

1

51-70-02

8

2411496 1 241 1496 1

Door Jamb, Aft Door Jamb, Fwd

1

S-552

1

S-552

10

2411496

Spacer

2

2024-T3 Clad

0.050

1

I

Replace

11

2411496

9

1

Frame

Assy.

0.063

I I I I I

1

2411496

Frame

1

2024-T42 Clad

0.050

1

1

51-70-03

2411496

Doubler

1

4130

SteelI~

0.050

1

1

51-70-03

1

2024-T42Clad

0.050

1

I

1

2024-T42 Clad

0.050

Replace Replace

2411496

´•´•Clip

2411496

Stiffener

1

12

2411496

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

13

2411496

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

14

2411496

ChannelAssy.

1

2411496

Stiffener

1

2024-T42 Clad

0.040

1

1

51-70-03

2411496

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

15

2411496

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

16

2411496 1

Frame

1

2024-T42 Clad

0.050

1

1

51-70-03

17

2411496 1

Frame

1

2024-T42 Clad

0.050

1

1

51-70-03

18

2411496 1

Frame

1

2024-T42 Clad

0.050

1

19

2411496 1

Frame

1

2024-T42 Clad

0.050

1

20

2411496

ChannelAssy.

1

2024-T42 Clad

0.050

2024-T42 Clad

0.071

Channel

2411496 21

1

2411496

1

2411496 22

2411496

1

1

Support Assy. Bracket(2ea.) Support Assy.

51-70-03

1

51-70-03

Replace

1 1

1

I

Replace

1

2411496 1

Bracket

1

2024-T42 Clad

0.050

1

I

2411496 1

Plate

1

2024-T3 Clad

0.190

1

I

1 1

I I

I I I

Replace Replace Replace Replace Replace Replace Replace

I

Replace

23

2411496

24

2311495

25

2311495

Angle Angle Angle

2411496

Angle Angle

2411496

2411496

27

2411496 1

2024-T42 Clad

0.050

2024-T42 Clad

0.050

4

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

0.050 0.050

1 1 1

2024-T3 Clad

0.063

1

3 4

I´•Shim, Laminated

26

2 3

Plate

0.050

4 4

Passenger/Crew Upper (24 Inch) Door Structure Repair Index Figure 1 (Sheet 3 of 6) EFFECTIVITY:

AIRCRAFT

EQUIPPED WITH 24 INCH

PASSENGER/CREW DOOR SRM~

52-10-00

Page 3 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO. 28 29

DWG. NO.

I I

I DESCRIPTION

EFF.

MATERIAL

I IFINISH CODE I GAGE

REPAIR

FIG. NO.

2311495 1

Striker Plate

3

4130 Steel

0.080

2411496 1

Striker Plate

4

4130 Steel

0.180

1 1

I I

Replace Replace

2411496

Support Assy. Bracket(2 ea.)

1

2024-T42 Clad

0.071

1

I

1

2024-T42 Clad

0.050

2024-T42 Clad

0.050

1 1

I I

Replace Replace Replace

3

2024-T3 Clad

0.190

3

2024-142 Clad

0.080

1 1

I I

Replace Replace

I

I

1

I

Replace Replace 51-70-03

1

2411496

I

1

30

2411496 1

31

2411496 1

Plate

1

32

2411496

CoverAssy. Bearing

3

2411496 2411496 1 2411496

Plate

Cover

CoverAssy. Bearing

2411496

4

4

AL Bronze

L~

I

2411496

Cover

4

2024-T42 Clad

0.080

33

2411496

Channel

1

2024-T42 Clad

0.050

1

1

34

2411496

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

35

2411496 1

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

36

2411496 1

Channel

1

2024-T42 Clad

0.050

1

1

51-70-03

37

2411498

Frame

Stiffener

5

2024-T42 Clad

0.040

1

I

Replace

Doubler

5

4130 Steel~

0.050

1

1

51-70-04

1

6 6

2024-T42 Clad

0.050

2411496 1 2411496

Doubler

6

4130 Steel~

0.050

1

1

51-70-04

2024-T42 Clad

0.050

1

I

Replace

2024-T3511

0.250

1

I

Replace

1 1

I

Replace Replace

Support Assy. Bracket

Support Assy. ´•´•Plate

Replace

5 5

6

6

Support Assy.

2411496

1

2411496

Bracket

1

2024-T42 Clad

0.050

2411496

Plate

1

2024-T3 Clad

0.080

1

2024-T42 Clad

0.071

1

2024-T3 Clad

0.100

1

I I

Replace Replace

2024-T42 Clad 2024-T3 Clad

0.071

1

I

Replace

0.100

Replace

2024-T42 Clad

0.071

Replace

2024-T42 Clad 2024-T3 Clad

0.071

2411496

1

2411496 2411496 1

1 2411496 2411496

42

2411496

43

2411496

Plate

Plate

2411496 2411496

Plate

1

Bracket

1

1 1

1

Support Assy. Bracket(2ea.) Support Assy. Bracket(2ea.)

2411496

2411496

Support Assy. Bracket(2ea.)

SupportAssy. Bracket(2ea.)

2411496

44

Assy.

Frame

2411496

41

Frame

2411496

2411496

40

5

2411496

2411496 1

39

1

2411496 1 2411496

38

Assy.

1 1

1 1 1

Assy.

0.100

1 1

I I

Replace Replace Replace Replace

1

2411496

Zee

1

4130 Steel

0.050

1

I

2411496

Plate

1

4130 Steel~

0.050

1

I

Passenger/Crew Upper (24 Inch) DoorStructure Repair Index Figure 1 (Sheet 4 of 6) EFFECTTVITY: sRM-a

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-00

Page 4 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO. 45

DWG. NO.

I

2411496

1

I DESCRIPTION Bracket

I

I

EFF.I

Assy.

MATERIAL

IFINISH GAGE

REPAIR FIG. NO.

CODE

1

2411496

Zee

i

4130 Steel~

0.050

2411496

Plate

i

4130 Steel~

0. 050

1

I

1 1 1 1

I I I I

1

I

46

2411491

Center Pin Guide

1

4139 Steel

0.100

47

2411494 1

Pin Guide

1

4139 Steel

0.100

48

2411494 1

Pin Guide

1

4139 Steel

0.100

49

2311502 1

Clevis

1

2024-T3 Clad

0.040

50

2311502

Guide

1

2024-T3 Clad

0.040

51

2311502

i

2024-T3 Clad

0.040

52

2311495

1

2024-T42 Clad

0. 050

53

2311495

1

Phenolic

0.312

54

2311278

Clip Splice Plate Spacer Hinge Arm

1

4130 Steel~

0.250

55

2411497

Guide

1

4130

Steell~

0.880

56

2411497

Guide

1

4130 Steel~

0.880

1

57

2411496

1

I

1

1

Doubler

Assy.

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

2411496

Bracket(2ea.)

i

2024-T42 Clad

0.050

2411496 1

Doubler

1

2024-T42 Clad

0.050

Spacer

1

2024-T3 Clad

0.063

58

2411493

Guide

1

4130 Steel~

0.190

59

2411493

Guide

1

4130

Steel~

0.190

1

I

Replace Replace Replace Replace Replace

60

2411496

5

2024-T42 Clad

0.080

1

I

Replace

2024-T42 Clad

0.080

2024-T42 Clad

0.080

1

I

Replace

2024-T42 Clad

0.080

1

I

Replace

2024-T42 Clad

0.080

1

I

Replace

2024-T42 Clad

0.080

1

I

Replace

2024-T42 Clad

0.080

1

I

Replace

2411472

Support Assy. Bracket(2ea.) Support Assy. Bracket(2 ea.) Support Assy. Bracket(eea.) Support Assy. Bracket(2ea.) Support Assy. Bracket(2 ea.) Support Assy. Bracket(2ea.) Support Assy. Bracket(2ea.) Support Assy. Bracket(2ea.)

6

2024-T42 Clad

0.080

1

I

Replace

2411499 1

Inner Skin

i

2024-T3 Clad

0.032

1

1

51-70-02

2411496

1

1

2411496 2411472 2411472 61

1 2411496 1 2411496 2411472 2411472

62

2411496

2411496 2411472

1 1 1

2411472 63

2411496 2411496

2411472 64

Passenger/Crew Upper (24 Figure EFFECTIVITY: SRM~

5 6 6

Replace

5 5

6 6 5 5

6 6 5 5

6

Inch) Door Structure Repair Index 1 (Sheet 5 of 6)

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-00

Page

5

May 15/92

Learjet STRUCTURAL REPAIR MANUAL ’EFFECTIVITIES

CODES

24-272, 24-295 THRU 24-357; 25-134, 25-168 THRU 25-373; 28-003 THRU 28-005; 29-001 THRU 29-004; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-304 THRU 24-357; 25-187 THRU 25-373; 28-0’03 THRU 28-005; 29-001 THRU 29-004; 35-017 AND SUBSEQUENT; 36-007, 36-009 AND SUBSEQUENT 24-272, 24-295 THRU 24-303; 24-309 THRU 24-314; 25-134, 25-168 THRU 25-186; 35-002 THRU 35-016; 36-001 THRU 36-006 AND 36-008 24-304 THRU 24357; 25-187 THRU 25-373; 28-003 THRU 28-005; 29-001 THRU 29-004; 35-017 AND SUBSEQUENT; 36-007, 36-009 AND SUBSEQUENT 24-272, 24-295 THRU 24-334; 25-134, 25-168 THRU 25-208; 35-002 THRU 35-084; 36-001 THRU

1 2 3 4 5

36-021 24-335 THRU

6

AND

24-357; 25-209 THRU 25-373; 28-003 THRU 28-005; SUBSEQUENT; 36-022 AND SUBSEQUENT

29-001 THRU 29-004; 35-085

NOTES Shims may be used between stiffeners and door skin and between bracket flanges and door skin, improve door skin contour. Refer to Approved Repairs for fabrication and usage of shims.

as

required,

to

Laminated shim stock, 0.002 num sheet.

or

0.003 lamination per MlL-S-22499

Heat Treat to 125,000

140,000 psi.

Heat Treat to 125,000

145,000 psi.

Heat Treat to 180,000

200,000

Type

1 Class 1

or

Class 2 1145-H19 alumi-

psi.

Aluminum bronze per AMS4640.

Condition Annealed

Type

FBG per MIL-P-15035.

Passenger/Crew Upper (24 Figure

EFFECTIVITY: SRM-4

Inch) Door Structure 1

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

Repair Index

(Sheet 6´•of 6)

INCH

52-10-00

Page 6 May 15/92

Learjet 1

STRUCTU RAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

STRUCTURAL IDENTIFICATION

33~

’13

22)

(10

n)

O

2-141B2

EFFECTIVITY: SRMII

~2

Passenger/Crew Upper (36 Inch) Door Structure Repair Index Figure 2 (Sheet 1 of 5) AIRCRAFT EQUIPPED WITH 36 PASSENGER/CREW DOOR

INCH

52-10-00

Page 7 May 15/92

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR

O

00

STRUCTURAL IDENTIFICATION

00

O

oO 00

OO

(3~ O

O

oC)o

oo

FWDI)

2-141B1

Passenger/Crew Upper (36

Inch) Door Structure

Repair Index

Figure 2 (Sheet 2 of 5) EFFECTIVITY: SRM4

AIRCRAFT EQUIPPED WITH 36 INCH PASSENGER/CREW DOOR

52-10-00

Page 8 May 15/92

Leariet Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

I

DWG. NO.

I

I

EFF.

Passenger/Crew Upper (36 Inch) Door Assy.

2311495 1

I DESCRIPTION

IFINISH

I GAGE

MATERIAL

REPAIR FIG. NO.

CODE

1

2311495 1

Skin

2

2024-T42 Clad

0.040

1

1

51-70-02

2311495

Skin

3

2024-T42 Clad

0.040

2

2311495 1

Frame

1

2024-T42 Clad

0.050

1 1

1 1

51-70-03

3

2311495 1

Frame

1

2024 Clad

0.050

1

1

51-70-03

4

2311495

1

4

4130

0.050

1

I

Replace

2311495

1

1 1

I I

2311495

Plate

Splice Splice Plate Assy. SplicePlate Angle Splice Plate

Steell~

51-70-02

5 5

4130 Steel

5

4130

Steell~

0.050

0.050

5

2311495

1

2024-T42 Clad

6

2311495 I´•Stiffener

3

S-554

I

I

Replace Replace Replace Replace

2311495 1

Channel

5

2024-T3 Clad

0.040

1

1

51-70-03

7

2311495 1

Stiffener

1

2024-T42 Clad

0.050

1

1

51-70-03

8

2311495 I´•Stiffener

1

S-554

2311495 I´•Stiffener

1

S-554

10

2311495

1

S-554

1 1 1

51-70-04

9

I I I

11

2311495

2311495

Stiffener

1

2311495

Bracket

Assy. Bracket(2ea.)

0.050

1

1 1 1

1 1

2024-T42 Clad

0.050

1

I

Replace

1

2024-T42 Clad

0.050

1

1

51-70-03

1

51-70-04

I I I I

Replace Replace Replace Replace Replace

12

2311495 1

13

2311495 I´•Stiffener

1

3-554

1

I

14

2311495

Channel

3

S-554

1

I

2311495

Channel

5

2024-T3 Clad

0.040

Gusset

1

1

2024-T3 Clad 2024-T3 Clad

0.050

Rocker Arm

6

2024-T3 Clad

0.080

1 1 1

2024-T3 Clad 2024-T42 Clad

0.100

1

I

1

0.050

1

Phenolic

0.375

1

I

15

2311495

16

2311495 2311495

17

2311495

1 1 1

Support Rocker Arm Support Support Assy.

2311495

Disc Bracket

2311495 18

Frame

2311495

BearingPlate CoverAssy.

1 2311495

51-70-04 51-70-04

0.050

1 1

I

Replace Replace Replace

1

2311495

Cover

1

2024-T42 Clad

0.080

2311495

Disc

1

2024-T3 Clad

0.190

1 1

I I

Clip

7

2024-T3 Clad

0.050

1

I

Replace Replace Replace

Exterior Handle Instl.

8

1 1 1 1

I I I

Replace Replace Replace Replace

1

19

2311495

20

2311678 1

2311678 I´•Pan

2311678 2311678 1

8

6061-T6

0.050

End Pan (2 ea.) Doubler

8

6061-T6

0.050

8

2024-T3 Clad

0.063

1

2024-T3 Clad

0.050

1

0.050

0.050

1 1

1 1

51-70-03

1

2024-T42 Clad 2024-T42 Clad

1

2024-T42 Clad

0.050

1

1

51-70-03

21

2311495

22

2311495 1

23

2311495

Rocker Arm Support Frame Channel

24

2311495 1

Frame

1

51-70-03

Passenger/Crew Upper (36 Inch) Door Structure Repair Index Figure 2 (Sheet 3 of 5) EFFECTIVITY: srzh~-a

AIRCRAFT EQUIPPED WITH 3~ INCH PASSENGER/CREW DOOR

52-10-00

Page 9 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ITEM NO.

DWG. NO.

25

2311495

I

Splice Plate SpliceAngle Assy. SpliceAngle Angle Guide Pin Assy.

2311495 2311495 2311495 26

27

I DESCRIPTION

2311271

I

I

EFF.

MATERIAL

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

Steell~

0.050

1

5

4130 Steel~

0.050

5

4130 Steel~

0.050

1 1

3

4130

Replace

5

I

1

2311271

Cover

1

2024-T42 Clad

0.080

2311271

Disc

1

2024-T3 Clad

0.190

2311495 1

Bracket

1

2024-T3 Clad

0.050

2311495

Stiffener

1

2024-T3 Clad

0.050

2311271

Plate, Fwd 6 Aft Upper

1

4130 Steel~

0.100

1 1 1 1 1

I I I I

2311495 1

Bracket

1

2024-T3 Clad

0.050

1

I

28

2311495 1

Frame

1

2024-T3 Clad

0.050

29

2311495 1

Lower Channel

3

2024-T42 Clad

0.050

1 1

I I

I

I I I I

30

2311495 1

Forward Door Jamb

1

S-552

2311495

Aft DoorJamb

1

S-552

Lower

1

2024-T3 Clad 2024-T3 Clad

0.100

1

1

Edge

1

31

2311495

32

2311495

Bracket

33

2311495 1

Bracket

1

2024-Tr12 Clad

0.050

1 1

34

2311495 1

Doubler

9

301 Stainless

0.040

1

I

35

2311502

ClevisPin BracketAssy.

10

2024-T3 Clad

0.063

Clip

10

0.040

I I

2311502

Clevis

10

Guide

10

I I

I

2311502

2024-T3 Clad 4130 Steel 4130 Steel

1 1

2311502

Plate

Replace Replace

0.063

I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

36

2311499 1

Inner Skin

1

2024-T42 Clad

0.032

1

1

51-70-02

37

2311499

Stiffener

1

2024-T42 Clad

0.040

1

I

38

2311499

Cover

1

2024-T3 Clad

0.032

Replace Replace

Passenger/Crew Upper (36 Inch) Door Structure Repair Index Figure 2 (Sheet 4 of 5) EFFECTIVITY: sRM-a

AIRCRAFT EQUIPPED WITH 36 PASSENGER/CREW DOOR

INCH

52-10-00

Page 10 May 15/92

Learjet STRUCTURAL REPAIR MANUAL EFFECTIVITIES

CODES

23-002 THRU 23-099; 24-100 THRU

1

24-357; 25-002 THRU 25-373; 35-002 AND SUBSEQUENT;

36-001 AND SUBSEQUENT

23-003 THRU 23-008 23-009 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 23-002 THRU 23-090; 24-100 THRU 24-169; 25-002 THRU 25-010 24-170 THRU 24-357; 25-011 THRU 25-061, 25-067 THRU 25-373; 35-002 AND SUBSEQUENT;

2

3 4 5

36-001 AND SUBSEQUENT

24-344 THRU 24-357; 25-219 THRU 25373; 35-101 AND

6

SUBSEQUENT;

36-030 AND SUBSE-

SUBSEQUENT;

36-018 AND SUBSE-

QUENT 24-327 THRU 24-357; 25-002 THRU 25-373; 35-059 AND

7

QUENT 23-014 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25373; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 23-060 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-100 THRU 24-357; 25-002 THRU 25-373; 35-002 AND SUBSEQUENT; 36-001 AND SUBSE-

8 9

10

QUENT

NOTES: Condition Annealed.

I~

Heat Treat to 125,000

Type

145,000 psi.

FBG per MIL-P-15035.

Condition 1/2 Hard.

Passenger/Crew Upper (36 Inch) Door Structure Repair Index Figure 2 (Sheet 5 of 5) EFFECTIVITY:

AIRCRA~ EQUIPPED WITH 36 PASSENGER/CREW DOOR

INCH

52-10-00

Page 11 May 15/92

Learjet ~Learjet STRUCTURAL REPAIR MANUAL PASSENGERICREW UPPER DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGELIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose or failed rivet can cause increased stress concentra-

progressive joint failure. A careful inspection must be performed to ensure that joint failure has not spread from the area of the loose or failed rivet. (Refer to Chapter 51 for definition of rivet failure.) tions

the

on

(2) Loose

or

remaining

failed

rivets and lead to

screws are

not allowed. A loose or failed screw can cause increased stress concen-

surrounding screws and lead to progressive joint failure. A careful inspection must be performed to ensure that the joint failure has not spread from the area of the loose or failed screw. trations

B.

on

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, and refinished in accordance C. D.

re-

Chapter 51.

Deformation

(1) Deformation of the primary door assembly structure or door hinges is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

with

more

than

specified.

Dents

(1) Dents

are

permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch depth, do not exceed 10% of total surface area in one (1) square foot, and are not

(2.54 mm) in

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to a rivet or structural area. Such dents shall be repaired or the component reF.

G.

H.

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) Structural (2) components must be replaced or repaired if nicks reduce the original material thickthan ness more specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY: SRM-4

ALL

52-10-00

Page 101 May 15/92

STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0,100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY: SRM4

ALL

101

52-10-00

Page 102 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW UPPER DOOR i.

APPROVED REPAIRS

NOTE:

All dimensions

Refer to

B.

Refer to the basic for door

C.

are

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the passenger/crew upper door structure. Learjet Maintenance Manual, Chapter 52, for repairs and maintenance procedures

A.

bar

components

such

as

door seals, door latch mechanism, door hook

mechanism, and

torsion

assembly.

Skin gap tolerance between the passenger/crew door skin and fuselage skin is 0.030-inch (0.762 mm) minimum to 0.0B0-inch (1.524 mm) maximum around perimeter of door (see Figure 201).

(TWICAL FOR 24

EFFECTIVIIY:

INCH OR 36

0.030

Inch Minimum

0.060

Inch Maximum

INCH DOOR)

Door Skin

Gap Tolerances Figure 201

2-146A

SRM~I

REPAIR

ALL

52-10-00

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL CONDITION

Out-of-Contour condition

1.

can

exists when door skin is secured in

place and

door is dented.

LIMITATIONS 1.

Out-of-Contour

2.

Maximum thickness of shim may not exceed 0.063 inch (1.6 mm). Dents may or may not cause deformation of the door substructure which affects the structural

area

may not exceed 12.0 inches (304 mm) in

length by 0.080

inch (2.03 mm) in

depth. integri-

ty of the door. REPAIR

6.

length and depth of area to be shimed. a shim of proper length, thickness and taper, from 2024-T3 aluminum sheet. Apply one (1) coat epoxy primer to shim. Apply faying´• surface seal to both sides of shim. (Refer to Chapter 51.) Slid~ shim into place. Drill proper size holes from skin side through shim.

7.

InstallMS20426AD fasteners.

8.

Paintaffected

i.

Determine

2.

Fabricate

3. 4.

5.

areas.

Door Stiffeners

(Ref)

Door Frame

U

(Ref)

Door Skin

(Ref)

,i,

Outside Door Skin Contour Door Frame

(Normal)

(ReO

Detail A 2-153A

EFFECTTVITY: SRM-4

Upper Door Skin Repair Figure 202

Out-of-Contour

ALL

52-10-00

Page 202 May 15/92

Learjet ~LBarjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

1.

STRUCTURAL IDENTIFICATION

DESCRIPTION A.

passenger/crew door is located on the left side of the fuselage in the forward passenger compartment. The passenger/crew door can be either a 24-inch executive door or a 36-inch cargo door. The door consists of an upper assembly that forms a canopy when open, and a lower door assembly with integral entrance steps. The

b

2

’1 o

20r

-1) ~!II

I"

A’

’ol~d

32r

2-2000

EFFECTIVITY: SRM-4

Passenger/Crew Lower (24 Inch) Door Structure Repair Index Figure 1 (Sheet 1 of 4) AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW MX)R

INCH

52-10-10

Page 1 Jun 1/95

Inarpt ~Learjetl STRUCTURAL REPAIR MANUAL PASS~ENGER/CREW LOWER DOOR

STRUCTURAL IDENTIFICATION

~7 cl II

I

a

0/

(25

(AF]T E~D

LOOKING AFT)

(FWD END

~s

Detail A

LOOKING FWD)

DetailB

,o

I’

,e

a

21

(VIEW LOOKING AFT)

(VIEW LOOKING FWD)

DetailC

DetailD

2aOOC

Passenger/Crew Lower (24

Inch) Door Structure

Repair Index

Figure 1 (Sheet 2 of 4) EFFECTIVITY: SRM~

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-10

Page 2 May 15/92

Lsarjet i ~I Leariet

STRUCTURAL REPAIR MANUAL ITEMI NO.

DWG.

I

I

NO.

Passenger/Crew Lower (24 Inch) Door Assy.

2411250

I

I MATERIAL

EFF.

DESCRIPTION

GAGE

IFINISHI REPAIR CODE FIG. NO.

1 1

2024-T42 Clad

0.040

1

2024-T3 Clad

0.080

F4-6

2511271

Skin, Outer Skin, Inner Shim, Laminated (Max. 0.032) Angle(3 ea.)

1

2024-T42 Clad

0.050

F4-6

F4-6

1

2411250

2

2411250

2411250

51-70-02

1

2511271

Clip

1

2024-T42 Clad

0.050

3

2511271

1

2024-T3 Clad

0.063

4

2511271

Cover (2 ea.) Bracket

1

4130 Steel

0.063

1

5

2511271

Doubler

1

12024-T3Clad

0.050

1

6

2511271

Cover

1

2024-13 Clad

0.032

2511271

CoverAssy.

1

7

2511271

Cover

1

2024-T3 Clad

8

2511271

Stiffener

1

S654

9

2511271

Stiffener

10

2511271

Stiffener

11

2511271

12

13

F4-6

F4-6

0.032

1

I F4-6

F4-6

1

S-554

1

I

F4-6

S-554

1

I

F4-6

Stiffener

1

5654

1

I

F4-6

2511271

Stiffener

1

S-554

1

I

F4-6

2511271

Strap

1

2024-T42 Clad

0.063

F4-6

14

2511271

1

2024-T42 Clad

2311216

0.050 0.063

F4-6

15

Seal Retainer Doubler

o.loo

F4a

I

0.050

F4-6

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

0.050

F4-6

51-70-04

2311216

I´•Spacer

1

2024-T3 Clad 12024-T3Clad

16

2311216

Bracket

1

2024-T3 Clad

0.032

17

2311273

Latch Arm

1

4130 Steel

0.125

18

2311666

1

2024-T42 Clad

0.063

F4-6

19

2411276

Angle(2ea.) Angle(2ea.) Clip(2 ea.) Spring Hinge Fitting

1

2024-T42 Clad

0.050

F4-6

1

2024-T42 Clad

0.050

F4-6

1

Music wire

0.042

2411276 20

2411276

21

2511297

22

2511297

23

2411276

1

1

I

1

MS35821-2A

2

4130 Steel

Plate

2

4130 Steel

Cover

1

2024-T3 Clad

24

2511271

Frame

1

2024-T42 Clad

25

2511271

Stiffener

1

S-554

26

2511271

Frame

3

2024-T42 Clad

2411232

Frame

4

2511271

3

2411230

Support Support

4

27 28 29

Replace Replace Replace Replace Replace Replace Replace

Replace Replace Replace

F4-6

I

1

2411276

51-70-02

I

F4-6 F4-6

1

I

I

I F4-6

Replace

0.050

F4-6

51-70-04

2024-T42 Clad

0.050

F4-6

51-70-04

2024-T42 Clad

0.050

F4-6

2024-T42 Clad

0.050

F4-6

Replace Replace

1

2511271

Frame

3

2024-T42 Clad

0.050

F4-6

51-70-04

2411231

Frame

4

2024-T42 Clad

0.050

F4-6

51-70-04

2511271

Support Support Angle (2ea.)

3

2024-T42 Clad

0.050

F4-6

4

2024-T42 Clad

0.050

F4-6

4

2024-T3 Clad

0.063

F4-6

Replace Replace Replace

2411230

2411233

1

Passenger/Crew Lower (24 Inch) Door Structure Repair Index Figure 1 (Sheet 3 of 4) EFFECTIVITY: SRM-I

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-10

Page 3 Jun 1/95

Learjet ~Learjetl

STRUCTURAL REPAIR MANLIAL ITEM NO.

FINISH

DWG. NO.

DESCRIPTION

EFF.

MATERIAL

30

2511271

Doubler

1

2024-T3 Clad

31

2511271

DoorJamb

1

S-552

2511271

Bracket Assy. Bracket

1

2511271

32

Plate

2511211 33 34

0.050

CODE F4-6

F4-6

REPAIR FIG. NO.

Replace Replace

1

2024-T42 Clad

0.063

F4-6

1

2024-T3 Clad

0.100

F4-6

Replace Replace

2511271

Frame

3

2024-T42 Clad

0.050

F4-6

51-70-04

2511271

Frame

4

2024-T42 Clad

0.050

F4-6

51-70-04

2511271

DoorJamb

1

S-552

F4-6

2511271

Filler

1

2024-T42 Clad

0.100

F4-6

Filler

5

2024T3 Clad

0.160

F4-6

Replace Replace Replace Replace Replace Replace

2511271

2511282

35

GAGE

25~1282 2511282

CODES

HingeAssy., LowerDoor Hinge(2 ea.) Hinge Pin

1 1

F176

i

EFFECTIVITIES 24-272, 24-295 THRU 24-357; 25-134, 25-168 THRU 25-373; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-272, 24-295 THRU 24-314; 25-134, 25-168 THRU 25-189; 35-002 THRU 35-020; 36-001 THRU

1

2

36-013 3

24-272, 24-295 THRU 24-357; 25-134, 25-168 THRU 25336; 35002 THRU 35-392; 36-001 THRU

4

25-337 AND

5

24-350 THRU 24-357; 25-227 THRU 25-373; 35-1 17 AND SUBSEQU ENT; 36-033 AND SUBSE-

36-047

SUBSEQUENT; 35-393 AND SUBSEQUENT; 36-048 AND SUBSEQUENT

QUENT

NOTES:

F4-Glnterior, F4Exterior. Laminated shim stock, 0.902 sheet.

or

0.003 lamination per MlL-S-22499

Type

1 Class 1 or Class 2 1145-H19 alumi-

num

Condition Annealed. HeatTreatto 150,000 -180,000

psi.

HeatTreatto 125,000 -150,000

psi.

HeatTreatto125,000- 145,000psi. MadefromA151321 or347.

Madefrom

MS202536pin.

Passenger/Crew Lower (24 Inch) Door Structure Repair Index Figure 1 (Sheet 4 of 4) EFFECTIVITY: SRM-4

AIRCRAFT EQUIPPED WITH 24 PASSENGER/CREW DOOR

INCH

52-10-10

Page 4 Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

1.

STRUCTURAL IDENTIFICATION

DESCRIPTION A.

passenger/crew door is located on the left side of the fuselage in the forward passenger compartpassenger/crew door can be either a 2Pinch executive door or a 36-inch cargo door. The door consists of an upper assembly that forms a canopy when open, and a lower door assembly with integral entrance steps. The

ment. The

B

~dS:

A:

D

2-198C

Passenger/Crew Lower (36 Inch) Door Structure Repair Index Figure 2 (Sheet 1 of 8)

EFFECTIVITY:

AIRCRAE~ 23-002 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU INCH PASSENGER/CREW DOOR

25-060 EQUIPPED WITH 36 SRM-4

52-10-10

Page 5 Tun 1/95

Learjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

5)

I1

O

STRUCTURAL IDENTIFICATION

~19

oS

~i o~ (AFT END

P~ d

LOOKING FWD)

Detail B (FWD END

LOOKING APT)

Detail A ~Y

r;´• 9)

@i\

Q

o

o/

I

uy

v

0)

(VIEW LOOKING EUID)

(VIEW LOOKING APT)

(VIEW LOOKING AFT)

DetailC

DetailD

DetailE

2-19ec

EFFECTnrITY:

Passenger/Crew Lower (36 Inch) Door Structure Repair Index Figure 2 (Sheet 2 of 8) AIRCRAFT 23-002 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU 25-060 EQUIPPED WITH 36

SRM-4

(10

INCH PASSENGER/CREW DOOR

52-10-10

Page 6 Jun 1/95

Leariet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

I

Passenger/Crew Lower (36 Inch) Door Assy

2311270

I EFF.

DESCRIPTION

I MATERIAL

IFINISH

1 1

2024-T42 Clad

1

S-552

1

S-552

2311275

Skin, Outer DoorJamb, Fwd DoorJamb, Aft Filler (2 ea.)

1

2024-T3 Clad

0.100

2311275

Filler

1

2024-T3 Clad

0.160

6

2311275

Stiffener(2 ea.)

1

S-554

7

2311275

Stiffener

1

S654

8

2311271

Guide,

1

4130 Steel

2311271

Plate

1

4130 Steel

0.100

1 1

1

2311275

2

2311275

3

2311275

4

5

REPAIR FIG. NO.

CODE

I GAGE

Pin

0.040

1 1

1

1~

1

1

51-70-02

I I

I I

1 1

I

I I

Replace Replace Replace Replace Replace Replace Replace Replace

I 0.100

9

2311275

2024-T42 Clad

0.050

1

1

51-70-04

2311275

Support, Fwd Support, Aft

1

10

1

2024-T42 Clad

0.050

1

1

51-70-04

11

2311275

End Frame, Fwd

1

2024-T42 Clad

0.050

1

1

51-70´•04

12

2311275

Frame(2 ea.)

1

2024-T42 Clad

0.050

2311275

Plate

1

2024-T3 Clad

0.050

1 1

I

1

/2024-T3Clad

0.050

1

I

I

I

I´•Clip

231 1275

I

1

13

2311275

Stiffener

1

S-554

14

2311275

Cover

1

2024-T3 Clad

0.032

1

I

2311275

Plate

1

2024-T3 Clad

0.125

15

2311275

Skin, Inner

1

2024-T3 Clad

0.080

1 1

I I

16

2311275

Doubler

1

2024-T3 Clad

0.050

2311275 1

Plate

1

2024-T3 Clad

0.025

1 1

I I

1

2024-T42 Clad

0.080

1

1

0.032

2311275 17

18

19

20

I

Pan, SeatRail

1 2311275

Cover

2311275

Angle

1

2311275

Frame

2

2024-T3 Clad 2024-T42 Clad 2024-T42 Clad

2311275

Seat Rail

3

S-537

2311275

Switch Bracket

1

2311275

Gusset (2ea.)

1

2311275

2311275

Clip Clip

2311275

2311275 2311275 2311275

I i

0.050

1

I

0.050

1 I

I I

2024-T42 Clad

0.050

1

I

2024-T3 Clad

0.063

1

I

1

2024-T42 Clad

0.050

1

I

1

2024-T42 Clad

0.050

I

Cover

1

2024-T3 Clad

0.063

1 1

CoverAssy.

1

2024-T3 Clad

0.032

Cover

1

Shim, Laminated (Max. 0.032)

4~

2311275

Plate

1

2024-T3 Clad

21

2311275

Stiffener(2 ea.)

1

S-554

22

2311275

Channel

1

2024-T3 Clad

I

0.080

1 0.080

1 I 1

I I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Passenger/Crew Lower (36 Inch) Door Structure Repair Index Figure 2 (Sheet 3 of 8) EFFECTIVITY:

AIRCRAFT 23-002 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU

25-060 SRM-I

EQUIPPED

WITH 36

INCH PASSENGER/CREW DOOR

52-10-10

Page 7 Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL FINISH CODE

REPAIR FIG. NO.

ITEM

DWG.

NO.

NO.

23

2311661

Bracket

1

2024-T42 Clad

0.063

Replace

2311663

Pulley Support

1

2024-T42 Clad

0.050

2311664

1

2024-T42 Clad

0.063

2311666

Clip Angle(4ea.)

1

2024-T3 Clad

0.063

2311673

Doubler

1

2024-T3 Clad

0.063

2311663

Pulley Support

1

2024-T42 Clad

0.050

2311275

Frame

1

2024-T42 Clad

0.050

2311275

Plate

1

2024-T3 Clad

0.063

2311275

Angle(2ea.)

5

2024-T42 Clad

0.050

2311501

End Frame, Aft

1

2024-T42 Clad

0.050

Replace Replace Replace Replace Replace Replace Replace Replace Replace

2311275

Hinge

1

MS35821-2A

2311275

Spring

1

Music Wire

0.042

Cover

1

2024-T3 Clad

0.063

24 25

26

DESCRIPTION

27

2311275

28

2411282

2411282 2411282

CODES

HingeAssy., LowerDoor Hinge(2 ea.) Hinge Pin

EFF.

MATERIAL

1

3

F17-6

1

4

F176

3

23-002 THRU 23-008

4

23-009 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU 25-060 23-003 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU 25-060 24-140 THRU 24-229; 25-002 THRU 25-060

6

Replace Replace

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU 25-060 23035 THRU 231)39

5

Replace Replace Replace Replace

1

2

1

GAGE

NOTES:

Laminated shim stock, 0.002 sheet.

or

0.003 lamination per MlL-S-22499

Type

1 Class 1

or

Class 2 1145-H19 alumi-

num

Heat Treat to 125,000

I

I~

145,000 psi.

MadefromA151321 or347. Madefrom

MS20253-5pin.

Passenger/Crew Lower (36 Inch) Door Structure Repair Index Figure 2 (Sheet 4 of 8) EFFECTIVITY:

AIRCRAFT 23-002 THRU 23-099; 24-100 THRU 24-229; 25-002 THRU INCH PASSENGER/CREW DOOR

25-060 EQUIPPED WITH 36 SRM-4

52-10-10

Page 8 Jun 1/95

Learjet ~jLearjet STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

STRUCTURAL IDENTIFICATION

B

~an\ 26

g*~B (Airmaft 24-320 thru 24-357: 25-261 th~u 25373; 28-002 thru 28-005: 29-001 thru 29-004: 31-002 and Subseauent: 35-002 and Subseauent: 36-001 and Subseauent. eaainned with 36 Inch PassenperlCrew Door)

2-197C

EFFECTIVITY:

Passenger/Crew Lower (36 Inch) Door Structure Repair Index Figure 2 (Sheet 5 of 8) NOTED

52-10-10

Page9 SRM-I

Jun 1/95

Learjet

STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR

I

O

STRUCTURAL IDENTIFICATION

~B

1"1

"o

6)

j/

O

O ’1, LI

(FWD END

(3

LOOKING AFT)

(AFT END

Detail A

LOOKING FWD)

DetailB

(VIEW LOOKING FWD)

Detail C (Aircrafl´• 24320 thru 24-357: 25-261 thru 25-373: 2&001 thvu 28-005: 29-002 thru 29-004.: 31-002 and Subseauent: 35-002 and Subseauent: 36-001 and Subseauent. eauirttled wifh 36 Inch PassenaerlCrew Door) 2-197(3

Passenger/Crew Lower (36

Inch) Door Structure Repair Index

Figure 2 (Sheet 6 of 8)

EFFECTIVITY:

NOTED

52-10-10

Page SRM-4

10

Jun 1/95

~j Learjet STRUCTURAL REPAIR NIANUAL ITEM( DWG. NO.

I EFF.

DESCRIPTION

NO,

PassengerlCrew

2411234

MATERIAL

(FINISH( REPAIR

Lower

1

2411234

2

2411234

(36 Inch) Door Assy. Skin, Outer Skin, Inner

3

2311216

4

2311216

1 1

2024-T42 Clad

0.040

1

1

51-70-02

1

2024-T3 Clad

0.080

1

1

51-70-02

Doubler

1

2024-T3 Clad

0.063

Bracket

2

4130 Stainless

2024-T3 Clad 2024-T3 Clad

1

0.032

I I

Replace Replace Replace Replace

I I I

Replace Replace Replace

1

51-70-04

5

2311216

Spacer

1

6

2311216

Bracket

1

2311661

BracketAssy.

1

0.100

Bracket

1

2024-T42 Clad

0.063

2024-T3 Clad

0.063

2311666

Angle (2ea.) Angle(2ea.)

1 1

2024-T3 Clad

0.063

1 1 1

2411273

Frame, Aft

1

2024-T42 Clad

0.050

1

2411274

Actuator

2024-T3 Clad 2024-T42 Clad

0.063

7

2311661

8

2311666

9

10

Support Assy.

1

Gusset(2ea.)

11

2411274

12

2411277

1 1

13

2411276

Frame, Fwd Stiffener(2 ea.)

1

S-554

14

2411276

Stiffener

1

S-554

15

2411276

Stiffener(2 ea.)

1

2411276

1

0.050

1 1

16

2411276

Seal Retainer Filler

1

S-554 2024-T42 Clad 2024-T42 Clad

17

2411276

Angle(2 ea.)

1

2024-T42 Clad

0.050

18

2411276

Filler(2 ea.)

1

0.100

19

2411276

Doubler

1

2024-T3 Clad 2024-T3 Clad

20

2411276

Cover

1

2024-T3 Clad

21

2411276

Cover

1

2411276

Cover

1

2411276

CoverAssy.

1

22

2411276

2411276 2411276 2411276 2411276

I 1 1

I I I

Replace Replace Replace Replace Replace Replace Replace

I

2024-T3 Clad

0.063

1

I

Replace

2024-T3 Clad

0.032

1

I

Replace

0.032

1

I I I I

Replace Replace Replace Replace

Replace Replace Replace Replace Replace Replace Replace

0.050

2024-T3 Clad 6061-T6

Clip, Fwd Clipi Aft Hinge Assy. Hinge Spring

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

0.042

I 1 1

I I I I

1 1

I I

1

MS35821-2A

1

Music Wire

Plate

1

2024-T3 Clad

Angle Clip (2 ea.)

1

S-606

Support Clip(2 ea.)

1

Replace Replace

1

2411276

2411276

I

0.063

2411276

1

I

I I I

24

2411276

51-70-04

1 1 1

23

2411276

0.050

Replace

1

1

´•´•RecessHandle

2411276

0.050

I 1

1

Cover

2411276

25

CODE I FIG. NO.

I GAGE

I

I 0.063

I

1

2024-T3 Clad

0.050

1

2024-T42 Clad

0.080

1

2024-T3 Clad

0.050

(Aircraft 24-320 thru 24357: 25-261 thru 25-373: 28-001 thre 28-005: 29-001 thru 29-004.: 31-002 and Subsewith 36 Inch PassenperlCrao Door) auent: 35-002 and Subseauent: 36-001 and Subseauent.

Passenger/Crew Lower (36 Inch)

Door Structure

Repair Index

Figure 2 (Sheet 7 of 8) EFFECTIVITY:

NOTED

52-10-10

Page 11 SRM-4

Jun 1/95

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

26

2411276

Frame

1

2024-T3 Clad

0.050

27

2411276

Cover

1

2024-T3 Clad

0.050

28

2411276

Stiffener

1

S-554

29

2411276

1

S-552

30

2411276

Door Jamb, Fwd Door Jamb, Aft

1

S-552

31

2411276

Frame

1

2024-T42 Clad

0.050

32

2411276

Frame

1

2024-T42 Clad

0.050

33

2411276

Support(2 ea.)

1

2024-T42 Clad

0.050

34

2411276

Cover

1

2024-T3 Clad

0.050

35

2411276

Filler(2ea.)

1

2024-T3 Clad

0.160

36

2411282 2411282 2411282

CODES

EFF.

DESCRIPTION

HingeAssy., LowerDoor Hinge Half (2 ea.) Hinge Pin

MATERIAL

GAGE

FINISH CODE

1

t

F17-6

1

F176

REPAIR FIG. NO.

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

EFFECTIVITIES 24-230 THRU 24-357; 25-061 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 31-030 AND SUBSEQUENT; 35-664 AND SUBSEQUENT; 36-064 AND SUBSEQUENT

1 2

NOTES:

Condition Annealed.

I

MadefromA151321 or347. Madefrom

MS20253-5pin.

(Airmaft 24-320 thre 24357: 25-261 thru 25-373: 28-001 thru 28-005: 29-001 thtrr 29-004: 31-002 and Subseauettt: 35-002 and Subseauent: 36-001 and Subseauent, eauitlt~ed with 36 Inch PassenaerlCrew Door)

Passenger/Crew Lower (36 Inch) Figure

EFFECTIVITY:

sRM-a

NOTED

2

Door Structure

Repair Index

(Sheet 8 of 8)

52-10-10

Page 12 Tun1/95

Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE DAMAGE

PASSENGER/CREW LOWER DOOR

i.

ALLOWABLE DAMAGELIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose or failed rivets

are

not allowed. A loose

or

failed rivet

can cause

increased stress concentra-

progressive joint failure. A careful inspection must be remaining has failure not that to ensure spread from the area of the loose or failed rivet. (Rejoint performed fer to Chapter 51 for definition of rivet failure.)

tions

(2) Loose

rivets and lead to

the

on

or

failed

screws are

not allowed. A loose

or

failed

screw can cause

increased stress

concen-

progressive joint failure. A careful inspection must be failure has the not spread from the area of the loose or failed screw. that to ensure joint performed trations B.

on

surrounding

screws

and lead to

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired,

and refinished in accordance with

re-

Chapter 51.

C.

Deformation

D.

(1) Deformation of the primary door assembly structure or door hinges is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness more than specified.

E.

Dents

(1) Dents

are

permissible,

(2.54 mm) in

depth,

if smooth and without

abrupt changes in contour, do

do not exceed 10% of total surface

area

in

one

not exceed 0.100 inch

(1) square foot, and

are

not

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. F.

Scratches(See Figure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to

Chapter 51

must be

than

specified.

thickness by G.

procedures.) replaced or repaired

for protective treatment

(2) Structural components more

if scratches reduce the

original

material

Nicks (See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to

protective treatment procedures.) must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings andForgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired. Chapter 51

for

(2) Structural components H.

EFFECTIVITY: SRM~

ALL

52-10-10

page 101 May 15/92

Learjet

STRU%TURAL REPAIR MANUAL

Minimum Thickness

Nominal Thickness

(Inch)

(Inch)

0.016

0.0135 0.0175

0.020 0.025

1

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure

EFFECTIVITY: SRM~

ALL

101

52-10-10

Page 102 May 15/92

Learjet Learjetl STRUCTURAL REPAIR MANUAL PASSENGER/CREW LOWER DOOR i.

APPROVED REPAIRS

NOTE:

All dimensions

are

in inches unless otherwise

Refer to

B.

Refer to the basic

for door components such C.

specified.

Chapter 51 for typical repairs for the passenger/crew lower door structure. Leajet Maintenance Manual, Chapter 52, for repairs and maintenance procedures

A.

bar

as

door seals, door latch mechanism, door hook mechanism, and torsion

assembly.

Skin gap tolerance between the passenger/crew door skin and fuselage skin is 0.030-inch (0.762 mm) minimum to 0.060-inch (1.524 mm) maximum around perimeter of door (see Figure 201).

(TYPICAL FOR 24

EFFECTIVITY:

INCH OR 36

0.030

Inch Minimum

0.060

Inch Maximum

INCH DOOR)

Door Skin

Gap Tolerance Figure 201

2-146A

SRM~

REPAIR

ALL

52-10-10

Page 201 May 15/92

Learjet Learjefl STRUCTURAL REPAIR MANUAL CONDITION

Out-of-Contour condition

1.

can

exists when door skin is secured in

place and

door is dented.

LIMITATIONS area may not exceed 12.0 inches (304 mm) in length Maximum thickness of shim may not exceed 0.063 inch (1.6 mm).

1.

Out-of-Contour

2.

Dents may or may not ty of the door.

cause

by 0.080

depth.

inch (2.03 mm) in

deformation of the door substructure which affects the structural

integri-

REPAIR

6.

length and depth of area to be shimmed. shim of proper length, thickness and taper, from 2024-T3 aluminum sheet. Apply one (1) coat epoxy primer to shim. Apply faying surface seal to both sides of shim. (Refer to Chapter 51.) Slide shim into place. Drill proper size holes from skin side through shim.

7.

InstallMS20426AD fasteners.

8.

Paint affected

1.

Determine

2.

Fabricate

3. 4.

5.

a

areas.

Door Stiffeners

(Ref)

Door Frame

U

(Ref)

I

Door Skin

’Ref)

Shim

Outside Door Skin

Contour DoorFrame--Y

(Normal)

(ReO

Detail A 2-153A

EFFECTTVITY: SRMII

Upper Door Skin Repair Figure 202

Out-of-Contour

ALL

52-10-10

Page 202 May 15/92

Learjet ~Learjet STRUCTU RAL REPAIR MANUAL STRUCTURAL IDENTIFICATION

EMERGENCY EXIT DOOR i.

DESCRIPTION

B.

The emergency exit door is located on the fuselage left side in the the aft passenger compartment. The door contains an acrylic window and can be opened from inside or outside of the aircraft. Refer to the basic Learjet Maintenance Manual, Chapter 52, for repairs and maintenance procedures

C.

Refer to the basic

A.

for door

components such as door seals and door latch mechanism. Learjet Maintenance Manual, Chapter 56, for repairs and

maintenance

procedures

for the emergency exit door window. FS 194.09

205.51

(Ref)

(Ref)

J,FS 182.65

~FS171.26

(Ref)

(Ref)

FS 157.28

(Ref) 1

ii

~I

i:t

Y

B

i

I

~I

lo

r

I

j ii

A

FWD~ i: (VIEWED FROM RIGHT SIDE LOOKING INBOARD)

O (VIEW LOOKING FWD)

(VIEW LOOKING AFT)

Detail A

DetailB

2-203(3

EFFECTIVITY: SRM~

Emergency Exit Door Structure Repair Index Figure 1 (Sheet 1 of 6) 23-002 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218

52-20-00

Page 1 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

I DESCRIPTION

I EFF.

MATERIAL

2388195

Emergency Emergency

1

2311320

Gusset

3

2024-T4 Clad

0.040

2

2311320 1

Bulkhead

3

2024-T4 Clad

0.040

2311320 1

Retainer

4

2024-T3 Clad

0.190

2311320

Catch, Lower

3

2014-T6

0.375

2311320

Doubler

3

2024-T3 Clad

0.080

2311320

Retainer

4

2024-T3 Clad

0.050 0.040

2311320

3 4

5

6

Exit

DoorAssy. DoorAssy.

REPAIR

CODE

FIG. NO.

1

2

1 1

I I

Replace Replace

I I I I I I I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Gusset

3

2024-T42 Clad

2311320

Retainer

5

2024-T4 Clad

0.250

2311320 1

Plate

5

2024-T3 Clad

0.080

2311320

1

2024-T42 Clad

0.250

2388195

Spacer Spacer

1 1 1 1 1 1 1 1

2

2024-T42 Clad

0.250

1

2311320

1 2311320 1

Frame, Window Outer Retainer, Window Inner

6

2024-T3 Clad

0.090

6

2024-T3 Clad

0.090

1

I I I

2311320

7

2024-T42 Clad

0.040

3

2024-T42 Clad

0.040

1 1

I I

3

2024-T42 Clad

0.040

2311320

Channel(2ea.) Channel(2ea.) Channel(2ea.) Gang Channel

2311320

Retainer

1 2311320

7

2311320

8

2311320

9

Exit

IFINISH GAGE

2311320 I´•Retainer 10

2311320

Frame

11

2311320

12

2311320

Ring, Ring,

1

9

2014-T6

0.375

1

I

10

2014-T6

0.250

1

I

Replace Replace Replace Replace Replace Replace

8

3

6061-T6

0.040

1

1

51-70-04

Aft

3

2024-T3 Clad

0.080

1

I

Fwd

3

2024-T3 Clad

0.080

2024-T3 Clad

0.125

1

I

Replace Replace Replace Replace

321 Stainless 2024T4 Clad

0.125

2

0.830

1 1

I I

2

5-578

2311320

Shim, Laminated (Max. 0.125)

10

2311320

Retainer

10

Pin

2

2388195 2388195 2388195 2311321

1

Assy.

´•´•Link

2

Pin

Angle (2 ea.)

1

Replace Replace Replace

Emergency Exit Door Structure Repair Index Figure 1 (Sheet 2 of 6) EFFECTIVITY: SRM-4

23-002 THRU 23-099; 24-100 THRU 24-229 EXCEPT 24-218

52-20-00

Page 2 May 15/92

Learjet Learjet

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-002 THRU 23-099

2

24-100 THRU 24-229

3

23-002 THRU

4

23-002 THRU 23-012

5

23-005 THRU

6

23-004 THRU 23-099; 24-100 THRU 24-229 23-012 AND 23-013

7

23-099; 24-100 THRU

24-229

23-099; 24-100 THRU 24-229

23-022 THRU 23-099; 24-100 THRU 24-229 23-022 THRU 23-099; 24-100 THRU 24-140

8 9

24-141 THRU 24-229

10

NOTES:

Made from G1000-3-10-5,

Kaynar Mfg.

Laminated shim stock, 0.002 num sheet.

or

0.003 lamination per MIL-S-22499

Type

1 Class 1

or

Class 2 1145-H19 alumi-

Emergency Exit Door Structure Repair Index Figure 1 (Sheet 3 of 6) EFFECTIVITY: SRM-4

23-002 THRU 23-099; 24-100 THRU 24-229 EXCEPT 24-218

52-20-00

Page 3 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL EMERGENCY EMT DOOR

91

STRUCTURAL IDENTIFICATION

~s

6

~jj´•

ii ´I

Nli´• :I %I‘" B´•

´•I

I\´•

o

o

1)

(4 a

~u"d (TYPICAL) 2-48

EFFECTIVITY: SRM~

Emergency Exit Door Structure Repair Index Figure 1 (Sheet 4 of 6) 24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

52-20-00

Page 4 May 15/92

Learjet ~Hrietl STRUCTURAL REPAIR MANUAL ITEM NO.

DWG. NO.

I

2511320

2411320

3

4

FIG. NO.

1 2

2024-T42 Clad

0.040

1

I

0.040

1

I

0.063

1 1 1 1

I I I I

1 1

I I I

I

I I I

2511323 2511323

1

Spacer, Spacer,

2511324

l´•Spacer,

Internal

i

2024-T42 Clad 2024-T3 Clad

Internal

2

2024-T3 Clad

0.063

Pan

3

2024-T42 Clad

0.063

Filler

3

2024-T3 Clad

0.063

Inner

3

2024-T42 Clad

0.125

Outer

i

2024-T42 Clad

0.125

Outer

2

2024-T351 Clad

0.250

2411322

Catch

1

2024-T351 Clad

2411320

Catch, Lower

2

2014-T6 Clad

2411322

Spacer Support

3

2024-T3 Clad

0.063

1

2024-T351

1.600

1 1

1

2411322

Tee

Arm, Fwd Arm, Aft

2411322

2411322

Strap Clip Support

0.375

I

1

2024-T351

2.000

1

2024-T351

0.438

1

1

0.250

I

1

2024-T3 Clad 2024-T3 Clad

0.040

1

I

2411322 I´•Pin

1

2024-T4

0.438

1

I

24113211´• Pin

2

2024-T4

0.438

1

2024-T4 Clad

0.375

1 1

I I

2

2014-T6 Clad

0.250

2411322

2411323

1

2411320

1

2411320

I´•Shim, Laminated (Max. 0.125) 1 Fairing Pin Assy.

2388195

2388195 2388195

10

REPAIR

CODE

1

2511327 1

6

9

IFINISH

I GAGE

2

2511322 1

2411322

8

I MATERIAL

External

2411325

5

7

I EFF.

External

Skin, Skin, Skin, Skin,

1 2511325 1 2511320

2

DESCRIPTION

Emergency Exit DoorAssy. Emergency Exit DoorAssy.

2411320 1

I

I

2388195

Retainer(2 ea.) Retainer(2 ea.)

´•´•Link

Pin

2411323 1

Retainer

2311320

Gang

Channel

2~ 2

1

2024T3 Clad

0.750

1

j

2

321 Stainless

0.125

1

I

2

2024T4 Clad

0.830

1

I

2

2024-T4 Clad

0.375

1

I

0.080

1

I

I

I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

2

Replace Replace Replace

2

2311320 1

Plate

2

2024-T3 Clad

2311321

Angle (2 ea.)

2

S-578

1

Replace Replace

Emergency Exi~ Door Structure Repair Index Figure 1 (Sheet 5 of 6) EFFECTIVITY: SRM-4

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

52-20-00

Page 5 May 15/92

Learjet Learjet

STRUCTURAL REPAIR NIANUAL CODES

EFFECTIVITIES

1

24-218, 24-230 THRU 24- 357; 25-061, 25-070 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU

2 3

29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT;

36-001 AND SUBSEQUENT

25-002 THRU 25-066, EXCEPT 25-061 24-218, 24-230 THRU 24-357; 25-002 THRU

28-005; 29-001 THRU 29-004;

31-002 AND

SUBSEQUENT;

35-002 AND

25-373;

28-001 THRU

SUBSEQUENT;

36-001 AND SUBSEQUENT

NOTES:

Made from

G1000-3-10-5, Kaynar Mfg.

Laminated shim stock, 0.002 num sheet.

or

0.003 lamination per MIL-S-22499

Type

1 Class 1

or

Class 2 1145-H19 alumi-

Emergency Exit Door Structure Repair Index Figure 1 (Sheet 6 of 6) EFFECTIVITY: SRM-4

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND 36-001 AND SUBSEQUENT

SUBSEQUENT;

52-20-00

Page 6 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL EMERGENCY EXIT DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGE LIMITS All dimensions

NOTE: A.

specified.

Fasteners

(1) Loose tions

or

failed rivets the

on

performed fer to Chapter 51 (2) Loose

or

trations

ensure

failed

on

performed

not allowed. A loose

are

remaining

to

B.

in inches unless otherwise

are

rivets and lead to

that

joint

or

failed rivet

can cause

increased stress concentra-

inspection must be progressive joint of the loose from the or failed rivet. (Rearea spread failure. A careful

failure has not

for definition of rivet failure.)

screws are not

surrounding

allowed. A loose

to ensure that the

or

failed

screw can cause

increased stress

failure. A careful

and lead to

progressive joint joint failure has not spread from the area

screws

concen-

inspection must be

of the loose

or

failed

screw.

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, C. D.

and refinished in accordance with

Deformation

(1) Deformation of the emergency exit door assembly or structure is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

Chapter

re-

51.

more

than

specified.

Dents

(1) Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

G.

H.

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY:

ALL

52-20-00

Page sRM-a

re-

101

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016 0.020

0.0135

1

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0;063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY: SRM´•I

ALL

101

52-20-00

Page 102 May 15/92

Learjet STRUCTURAL REPAIR MANUAL EMERGENCY EXIT DOOR i.

REPAIR

APPROVED REPAIRS

NOTE:

All dimensions

are

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the emergency exit door structure. Learjet Maintenance Manual, Chapter 52, for repairs and

A.

Refer to

B.

Refer to the basic

C.

for emergency exit door components such as door seals and door latch mechanism. Skin gap tolerance between the emergency exit door skin and fuselage skin is 0.040-inch (1.016 mm) minimum to 0.080-inch (2.032 mm) maximum around

maintenance

procedures

perimeter of door (see Figure 201).

0.040

Inch Minimum

0.080

Inch Maximum

(TYPICAL)

Emergency Exit Door Skin Gap Tolerance Figure 201

2-145A

EFFECTIVITY: SRM~

ALL

52-20-00

Page 201 May 15/92

Learjet STRUCTURAL REPAIR MANUAL STRUCTURAL IDENTIFICATION

SERVICE DOORS 1.

DESCRIPTION A.

Service doors covered in this section

the tailcone

are

access

door,

nose

compartment

access

doors, oil

filler doors, oxygen bottle access door and single-point pressure refueling door. (1) The tailcone access door is located on the bottom side of the fuselage, in the aft section of the aircraft. Refer to Tailcone Access Door Structure Repair Index (52-40-01) for structural components.

applicable kit and/or kit drawing for additions, modifications and changes to structural components and assemblies.

On Aircraft eauim7ed with drag chute, refer to the

NOTE:

(2) The

nose

compartment

access

windshield. Refer to Nose

doors

are

Compartment

located

on

the

top side

Access Door Structure

of the

Repair

fuselage

forward of the

Index (52-40-05) for struc-

tural components.

(3) The oil filler

access

doors

are

located

(4) On Aircraft eaui~med with hand side of the

inder. cess

an access

nose

nose

Door Structure

the upper cowl

assembly of each engine

nacelle. Refer to

Repair Index (52-40-10)

compartment

door is located

on

for structural components. comt7artment oxwaen~culinder, an access door is located

Oil Filler Access Doors Structure

on

aft of frame 2. On Aircraft eauitwed with

the

right

a

on

dorsal fin

hand side of the dorsal fin. Refer to

the

right

oxvaerr

Oxygen

clA~-

Bottle Ac-

Repair Index (52-40-15) for structural components.

(5) On Aircraft eauim?ed with sinale-~oint

tlressure

refue2ina, an

access

door is located

on

the

right

hand

fuselage just above and aft of the wing trailing edge. Refer to Single-Point Pressure ReAccess Door Structure Repair Index (52-40-20) for structural components.

side of the

fueling B.

for service door

EFFECTIVITY: SRM-4

Learjet Maintenance Manual, Chapter 52, for repairs components such as seals, and door latch mechanism.

Refer to the basic

ALL

and maintenance

procedures

52-40-00

Page 1 May 15/92

Leariet I~j´•ti STRUCTURAL REPAIR MANUAL TAILCONE ACCESS DOOR

STRUCTURAL IDENTIFICATION

(23-002 thru 23-099: 24-100 thru 24-357)

3

(25-002 thru 25-357. 28-001 thtle 28-005; 29-001 thtu 29-004: 31-002 thnr 31-089: 35-002 th~ 35-676: 36-001 thfic 36-063)

(31-089 and Subseauent: 35-677 and Subseauent: 36-064 and Subseauent) 3-68

Tailcone Access Door Structure Repair Index

3-5C

3-528

EFFECTIVITY:

Figure 1 (Sheet 1 of 2) NOTED

52-40-01

Page sRM-a

1

Jun 1/95

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO. 2312015

1

2024-T3 Clad

S-557

2312015

Stringer Spacer(2ea.)

1 1

2024-T3 Clad

0.040

2312015

Doubler

1

2024-T3 Clad

0.040

2

2024-T3 Clad

0.040

2512049

TailconeAccess Door Instl.

2512049

TailconeAccess Door Instl.

2512051

I Replace

1

j Replace

Replace

3

Replace

2

51-70-02

Inner Pan

2

2024-T42 Clad

0.032

F4-1

Doubler

2

2024-T3 Clad

0.040

F4-1

´•´•Shim, Laminated (Max. 0.040) TailconeAccess DoorAssy.

2 3

1

I

I

3

2024-T42 Clad

0.040

2588061

Skin, Inner Skin, Gutter

3

2024-T3 Clad

0.050

2588061

Doubler

3

2024-T3 Clad

0.071

2024-T3 Bar

0.500

2588061 4

2488716

5

2512042 2512042

2512042 2512015 2512015 2512015 2488715 2488700

3 2

8 RH

Angle, LH 8 RH Hinge Arm, LW RH ´•´•HingeAssy.(2ea.)

1

1

2

S-608

2

2024-T351 Clad

I

j

I

i 0.250

2

3 3

Channel

0.500

4130 Steel Bar

1

I

I

2024-T42 Clad

0.040

2588061

´•´•Shim, Laminated (Max. 0.094)

3

2512047

Clip,LH&RH CIIp,LH&RH CIIRLH&RH Clip,LH&RH ´•´•HingeSpacer(2ea.)

4

2024-T42 Clad

0.100

4

2024-T42 Clad

0.100

4

2024-T42 Clad

0.100

4

2024-T42 Clad

0.100

4

2024-T351 Clad

0.050

4

2024-T42 Clad

0.063

2512046 2512045 2512044 2512043

Intercostal, LH 8 RH (3 ea.j

2512015 2512015

2512015

´•´•Angle(2ea.) ´•´•Stiffener(2ea.)

51-70-02

2

3

0.063

4 4

S-681

I

I

2512049

Doubler

4

2024-T42 Clad

0.090

2512049

Filler(Gea.)

4

2024-T3 Clad

0.032

Replace Replace Replace I Replace Replace

F4-1

2

´•´•´•HingeHalf(L~ea.) Hinge Pin (2 ea.) Hinge, LH 8 RH ´•´•ChannelAssy.

2488700

F4-1

3

´•´•Shim, Laminated (Max. 0.040)

Hinge, LH 8 RH Hinge Assy., LH

51-70-02

1

2312051 3112052

FIG. NO.

2

Tailcone Access Door Assy. Skin

2588061

7

F4-1

0.040

2312051 251 2051

6

CODE

1

DoorAssy

1

2312051

3

TailconeAccess

(FINISHI REPAIR GAGE

MATERIAL

EFF.

Door

2312015 2312015

2

I DESCRIPTION

Replace Replace F-l Replace I Replace F4-6 Replace F4-6 Replace Replace F4-1 Replace F4-1 Replace F8 Replace I Replace F4-1 Replace Replace F4-1 Replace F4-1 Replace F4-1 Replace F4-1 Replace F4-1 Replace F4-1 Replace F8-1 Replace F4-1 Replace F4-4 Replace F4-1 Replace

Repair Index Figure 1 (Sheet 2 of 2)

Tailcone Access Door Structure

EFFECTIVITY:

ALL

52-40-01

Page 2 SRM-4

Jun 1/95

Learjet ~tl

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357 25-002 THRU 25-373; 28-001 THRU 2&005; 24001 THRU 29-004; 31-002 THRU 31-088; 35-002 THRU 35676; 36-001 THRU 36-063 31-089 AND SUBSEQUENT; 35-677 AND SUBSEQUENT; 36-064 AND SUBSEQUENT 25-002 THRU 25-373; 28-001 THRU 28005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

1 2

3 4

NOTES: Finish F14-1 interior, F-l exterior.

L~

Laminated shim stock, 0.002 sheet.

or

0.003 lamination per MlL-S-22499

Type 1, Class

1

or

Class 2, 1145´•H19 alumi-

num

I~

Madefrom MS20001-4.

Madefrom MS20252P2.

4130 Steel, Condition Normalized.

EFFECTIVITY:

ALL

52-40-01

Page 3 SRM-4

Jun 1/95

Learjet STRUCTURAL REPAIR MANUAL TAILCONE ACCESS DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGE LIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose

or

failed rivet

can cause

increased stress concentrainspection must be

failure. A careful

tions on progressive joint remaining performed to ensure that joint failure has not spread from the area of the loose or failed rivet. fer to Chapter 51 for definition of rivet failure.) rivets and lead to

the

(2) Loose

or

trations

failed

on

performed B.

screws are

surrounding to

ensure

not allowed. A loose

failed

screw can cause

increased stress

concen-

must be

failure. A careful

inspection progressive joint joint failure has not spread from the area of the loose or failed screw.

screws

that the

or

(Re-

and lead to

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, C.

and refinished in accordance with

Chapter

re-

51.

Deformation

(1) Deformation of the tailcone access door, structure assembly or door hinges is not allowed. D. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) Structural (2) components must be repaired or replaced if corrosion repair reduces the original material thickness E.

more

than

specified.

Dents

(1) Dents

are

permissible,

~2.54 mm) in

depth,

if smooth and without

abrupt changes in

do not exceed 10% of total surface

area

in

contour, do not exceed 0.100 inch one (1) square foot, and are not

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. F.

Scratches(See Figure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Re-

protective treatment procedures,) must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(SeeFigure 301.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired. fer to

Chapter 51

for

(2) Structural components

G.

H.

EFFECTTVITY:

ALL

52-40-01

Page SRM~

101

May 15/92

Leariet ~tl STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040 0.050

0.037

1

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY:

ALL

101

52-40-01

Page SI~M-4

May

102

15/92

Learjet I

STRUCTURAL REPAIR MANUAL TAILCONE ACCESS DOOR i.

REPAIR

APPROVED REPAIRS

NOTE: A. B.

C.

All dimensions

are

in inches unless othenuise

specified.

Chapter 51 for typical repairs for the tailcone access door structure. See Figure 201 for tailcone access door skin gap tolerances. Refer to the basic Learjet Maintenance Manual, Chapter 52, for repairs and Refer to

for tailcone

access

door

components

such

as

maintenance

procedures

seals, and door latch mechanism.

Tailcone Access Door

CFWD

a.050

Inch Maximum

(VIEW LOOKING UP)

Tailcone Access Door Skin

2-146C

Figure EFFECTIVITY: SRM4

ALL

Gap Tolerance

201

52-40-01

Page 201 May 15/92

Learjet ~rj´•rl STRUCTURAL REPAIR MANUAL NOSE COMPARTMENT ACCESS DOORS

STRUCTURAL IDENTIFICATION

‘I

i

‘I

j

~FWO (VIEW LOOKING DOWN) (LH SHOWN, RH TYPICAL)

ITEM NO.

I

DWG. NO.

I DESCRIPTION

2311450

NoseCompartmentAccess Assy, LH RH

I EFF.

I MATERIAL

IFINISH GAGE

REPAIR FIG. NO.

CODE

Door 1

i

2311450

Door

1

2024-T42 Clad

0.032

1

1

51-70-02

2

2311450

Pan

1

2024-T42 Clad

0.025

1

1

51-70-02

CODES 1

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-001 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

Nose

1-188

Compartment

Access Doors Structure

Figure EFFECTIVITY:

ALL

Repair Index

1

52-40-05

Page SRM~

1

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL NOSE COMPARTMENT ACCESS DOORS i.

ALLOWABLE DAMAGE

ALLOWABLE DAMACELIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose or failed rivet

can cause

increased stress concentrainspection must be

failure. A careful

tions on the remaining rivets and lead to progressive joint performed to ensure that joint failure has not spread from the area of the loose or failed fer to Chapter 51 for definition of rivet failure.)

(2) Loose

or

failed

screws are

not allowed. A loose

or

failed

screw can cause

rivet. (Re-

increased stress

concen-

failure. A careful

inspection must be progressive joint of the loose from the or failed screw. area performed to ensure that the joint failure has not spread trations B.

on

surrounding

screws

and lead to

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, and C. D.

refinished in accordance with

Deformation

(1) Deformation of the nose compartment access doors or structure assembly is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

re-

Chapter 51.

more

than

specified.

Dents

(1) Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to a rivet or structural area. Such dents shall be repaired or the component reF.

G.

I-I.

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings andForgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY: SRM-4

ALL

52-40-05

Page 101 May 15/92

STRUCTURAL REPAIR MANUAL

Minimum Thickness

Nominal Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.073

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure

EFFECTIVITY: SRM4

ALL

101

52-40-05

Page 102 May 15/92

Learjet LBarjet STRUCTURAL REPAIR MANUAL NOSE COMPARTMENT ACCESS DOORS i.

REPAIR

APPROVED REPAIRS

NOTE:

All dimensions

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the nose compartment access door structure. Learjet Maintenance Manual, Chapter 52, for repairs and maintenance procedures for door components such as door seals and door latch mechanism. See Figure 201 for nose compartment access door skin gap tolerances.

A.

Refer to

B.

Refer to the basic

C.

are

CFWO

Nose

2-146(3

EFFECTIVITY: SRM~

ALL

0.050

Inch Minimum

0.070

Inch Maximum

Compartment Access Doors Skin Gap Tolerances Figure 201 52-40-05

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL STRUCTURAL IDENTIFICATION

OIL FILLER ACCESS DOOR

I

r I I

jI I

O

I

iI I

Ii i I

_I I

I:

O

i I I I

ii

I I

Z--

(5)

(3)

(TYPICAL)

ITEM

DWO.

NO.

NO.

j

I

I

2452004 2652023

1

OilFillerDoorAssy., LH&RH

1

LH B RH

2

Oil Filler Door

2452004 2652023

1

126520231´•

2

2652023/´•

3

12652023/

4

I EFF.

DESCRIPTION

Assy.,

Skin, Outer Skin, Outer Pan,lnner Filler

1

2024-T42 Clad

0.063

i

1

51-70-02

0.025 0.025

1

1

51-70-02 51-70-02

2

2024-T42 Clad i 2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

2

i

2 i

GAGE

2 2

Filler

IFINISHI REPAIR CODE FIG. NO.

I MATERIAL

Replace

0.080 0.080

j

I

Replace

MSeOO~i

5

1P4-700

I Hinge Assy.

j

~4085-4 jHingePin

CODES 1

I

2

I I

I

Replace Replace

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 2&005; 29-001 THRU 29-004

2

31-002 AND

1C195A

SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

Oil Filler Access Door Structure

Figure EFFECTIVITY:

SRLI-´•I

ALL

Repair Index

1

52-40-10

Page 1 Jun1/95

Learjet

B

STRUCTURAL REPAIR MANUAL OIL FILLER ACCESS DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGELIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose or

failed rivet

can cause

increased stress concentra-

progressive joint failure. A careful inspection must be remaining has that failure not to ensure spread from the area of the loose or failed rivet. (Rejoint performed fer to Chapter 51 for definition of rivet failure.) tions

(2) Loose

rivets and lead to

the

on

or

failed

screws are

not allowed. A loose

or

failed

screw can cause

increased stress

concen-

progressive joint failure. A careful inspection must be performed to ensure that the joint failure has not spread from the area of the loose or failed screw. trations B.

on

surrounding

screws

and lead to

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

re-

paired, and refinished in accordance with Chapter 51. C. D.

Deformation

(1) Deformation of the oil filler access door, structure assembly or door hinges is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

more

than

specified.

Dents

(1) Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to a rivet or structural area. Such dents shall be repaired or the component reF.

G.

H.

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(SeeFigure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY:

ALL

52-40-10

Page 101 May 15/92

Learjet STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTTVITY: SRM-4

ALL

201

52-40-10

Page 102 May 15/92

Leariet

STRUCTURAL REPAIR MANUAL OIL FILLER ACCESS DOOR i.

REPAIR

APPROVED REPAIRS

NOTE: A. B.

C.

All dimensions

are

in inches unless otherwise

specified

Chapter 51 for typical repairs for the oil filler access door structure. Refer to the basic Leajet Maintenance Manual, Chapter 52, for repairs and for door components such as door seals and door latch mechanism. See Figure 201 for oil filler access door skin gap tolerances. Refer to

0.020

maintenance

procedures

Inch Maximum

010

0.050 (f0.020)- Inch Maximum

(TYPICAL) Oil Filler Access Door Skin

2-146C

Gap Tolerances

Figure 201 EFFECTIVITY:

ALL

52-40-10

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL OXYGEN BOTTLE ACCESS DOOR

STRUCTURAL IDENTIFICATION

r

li.-_

FWOI)

ii

(VIEW FROM RIGHT SIDE, LOOKING INBOARD)

I

DWG.

ITEM

DESCRIPTION

NO.

NO.

Oxygen Bottle Nose Compartment Access Door Assy.

2319055 1

I

Door

1

2024-T42 Clad

0.040

Spacer Hinge

1

2024-T42 Clad

0.032

1

MS35821-5A

1

2-2048

REPAIR

CODE

FIG. NO.

1

2319055

CODES

IFINISH GAGE

MATERIAL

2319055 1

2319055

2

I EFF.

I

1 1

I I

I

I

Replace Replace Replace

EFFECTIVITIES 24-110 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT 36-001 AND SUBSEQUENT

Oxygen Bottle (Nose Compartment) Access Door Stntcture Repair Index Figure 1

EFFECTIVITY:

AIRCRAFT 24-110 THRU 24-357; 25-002 THRU 25-373; 28-001

SRM-4

THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

52-40-15

Page 1 May 15/92

Learjet ~Learietl STRUCTURAL REPAIR MANUAL OXYGEN BOTTLE ACCESS DOOR

STRUCTURAL IDENTIFICATION

i

1!

tiia

-7

i 17~

FWDI)

ITEM

DWG.

NO.

NO.

DESCRIPTION

2512021 2512052

Oxygen Battle Access Door Assy. Oxygen Bottle Access DoorAssy.

EFF.

2512021

Door

1 2

2

Door Stiffener

2512052

Stiffener

2

Spacer Spacer Hinge Hinge

1

2512052

2512021 2512052

4

CODES

FINISH

REPAIR

CODE

FIG. NO.

1

2512052 2512021

1 2512021

GAGE

2

1

3

MATERIAL

1

2

1 2

2024-T42 Clad 2024-T3 Clad 2024-T42 Clad 2024-T3 Clad

2024-T3 Clad 2024-T3 Clad MS35821-5A MS35821-10A

0.040 0.040

0.025 0.025

0.032 0.032

Replace Replace Replace Replace Replace Replace Replace Replace

EFFECTIVITIES

1

25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 35-002 THRU 35-491;36-001 THRU 36-034

2

31-002 AND

SUBSEQUENT; 35-492 AND SUBSEQUENT; 36-035 AND SUBSEQUENT

Oxygen Bottle (Dorsal Fin) Access Door Structure Repair Index Figure 2 EFFECTIVITY:

ALL

52-40-15

Page 2 SRM-4

May 15/92

Learjet ~Learjet

STRUCTURAL REPAIR MANUAL OXYGEN BOTTLE ACCESS DOOR

ALLOWABLE DAMAGE

ALLOWABLE DAMAGELIMITS

i.

All dimensions

NOTE: A.

in inches unless otherwise

are

Fasteners

(1) Loose tions

failed rivets

or

the

on

are

remaining

performed fer to Chapter 51 (2) Loose

or

trations

failed

on

performed

not allowed. A loose or failed rivet can

rivets and lead to

to ensure that

B.

specified.

joint

cause

increased stress concentra-

failure. A careful

progressive joint inspection must be from of the the loose area or failed rivet. (Respread

failure has not

for definition of rivet failure.)

screws are

surrounding

not

allowed. A loose

to ensure that the

or

failed

screw can cause

increased stress

failure. A careful

and lead to

concen-

must be

progressive joint inspection joint failure has not spread from the area of the loose or failed

screws

screw.

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired,

and refinished in accordance with

C.

Deformation

D.

Corrosion

(1) Deformation of the oxygen bottle

access

Chapter

door,

re-

51.

structure

assembly or door hinges is not allowed.

(SeeFigurelOl.) damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness more than specified.

(1) Corrosion

(2) E.

Dents

(1) Dents

are

permissible,

(2.54 mm) in

depth,

if smooth and without

abrupt changes in contour, do

do not exceed 10% of total surface

area

in

one

not exceed 0.100 inch

(1) square foot, and

are

not

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

G.

H.

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFlFECTIVITY: SRM-4

a

ALL

52-40-15

Page 101 May 15/92

Learjet E~ Learietl STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure 101 EFFECTIVITY:

ALL

52-40-15

Page 102 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL OXYGEN BO~LE ACCESS DOOR i.

REPAIR

APPROVED REPAIRS

All dimensions

NOTE:

Refer to

Refer to the basic

C.

See

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the oxygen bottle access door structure. Learjet Maintenance Manual for repairs and maintenance procedures

A. B.

bottle

are

door

access

Figure 201

for oxygen bottle

access

door skin gap tolerances.

0.030

I

for oxygen

components such as door seals and door latch mechanism.

Inch Minimum

z

_

_

r

I

-_J

FWDI) i~------

I I

I

0.120

Inch

Maximum1

(Aircraft eauitl~ed with Nose Com27artmen~ Oxvaen Bottle A_ccess Door)

(VIEW FROM RIGHT SIDE, LOOKING INBOARD)

Oxygen Bottle Access Door Skin Gap Tolerances Figure 201 (Sheet 1 of 2)

2-2048

EFFECTIVITY: SRM-4

NOTED

52-40-15

Page 201 May 15/92

Learjet I STRUCTURAL REPAIR MANUAL OXYGEN BOTTLE ACCESS DOOR

_C0.050 jr

I

REPAIR

Inch Minimum

FWD

I)

Ir;--T---tt

1

111

1

I I

‘:-------_1I~LL 0.060

Inch

MaximumJ

(Airmaft eauitltled wifh Dorsal Fin OxuPen Bottle Access Doorl

(VIEW FROM RIGHT SIDE, LOOKING INBOARD) 2-2048

Oxygen

Bottle Access Door Skin

Figure EFFECTIVITY: SRM-4

NOTED

Gap Tolerances

201 (Sheet 2 of 2)

52-40-15

Page 202 May 15/92

STRUCTURAL REPAIR MANUAL SINGLE-POINT PRESSURE REFUELING DOOR

STRUCTURAL IDENTIFICATION

;f:

slp~b ITEM

DWG.

NO.

NO.

I

I DESCRIPTION

3112015

Single-Point

Pressure

Refueling

I

I

EFF.

IFINISH GAGE

MATERIAL

REPAIR FIG. NO.

CODE

1

Door 1

3112015

Door

1

2024-T42

3112015

Bracket

1

j2024-T42

HingeAssy.

1

13112013

2

CODES

0.050

1

1

0.050

D

I

I

Replace Replace Replace

EFFECTIVITIES 31-001 AND SUBSEQUENT

1

NOTES: Made from MS35822-10C Butt

12-818

EFFECTIVITY:

Hinge.

Single-Point Pressure Re~fueling Door Structure Repair Index Figure 1 AIRCRAFT

EQUIPPED WTTH SINGLE-POINT

PRESSURE REFUELING 5RM-4

52-40-20

Page

1

Jun1/95

Learjet Learjet

STRUCTURAL REPAIR WIANUAL SINGLE-POINT PRESSURE REFUELING DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE All dimensions

NOTE:

A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose or failed rivet

can cause

increased stress concentra-

progressive joint failure. A careful inspection must be remaining failure has that not to ensure spread from the area of the loose or failed rivet. (Rejoint performed fer to Chapter 51 for definition of rivet failure.) tions

(2) Loose

or

trations

failed

on

performed B.

rivets and lead to

the

on

screws are

surrounding

not allowed. A loose

screws

to ensure that the

and lead to

joint

increased stress

failure. A careful

concen-

progressive joint inspection spread from the area of the loose or failed

must

be

screw.

not allowed. Cracked

forgings with Chapter 51.

fittings

in accordance

and

fittings or forgings must be replaced. considered allowable if properly

are

re-

Deformation

(1) Deformation of single-point pressure refueling door, structure or door hinges is not allowed. Corrosion(SeeFigure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

screw can cause

Cracks

paired, and refinished

D.

failed

failure has not

(1) Cracks in any fitting or forging are (2) Cracks in components other than C.

or

more

than

specified.

Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50

(1) Dents

inch (12.7 mm) to

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. F.

Scratches(See Figure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Re-

protective treatment procedures.) must be replaced or repaired thickness by more than specified. fer to

Chapter 51

for

(2) Structural components G.

H.

original

material

Nicks(SeeFigure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY:

AIRCRAFT WITH SINGLE-POINT PRESSURE REFUELING

SRM-4

if scratches reduce the

52-40-20

Page 101 May 15/92

Learjet ~tl STRUCIURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

fInch) 0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.030

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure 101

EFFECTIVITY:

AIRCRAFT WITH SINGLE-POINT PRESSURE REFUELING

SRM-4

52-40-20

Page 102 May 15/92

Learjet Leari~t

STRUCTURAL REPAIR MANUAL SINGLE-POINT PRESSURE REFUELING DOOR i.

REPAIR

APPROVED REPAIRS

All dimensions

NOTE:

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the single-point pressure refueling door structure. Learjet Maintenance Manual, Chapter 28, for repairs and maintenance procedures single-point pressure refueling door components such as door seals and door latch mecha-

A.

Refer to

B.

Refer to the basic for the

are

nism.

C.

See

Figure 201

for

single-point pressure refueling door skin gap tolerances.

0.020

Inch Maximum

I

C

O

Fwn~ 0.020

Inch Maximum

f (VIEW FROM RIGHT SIDE, LOOKING INBOARD)

2-201B

EFFECTIVITY:

Single-Point Pressure Refueling Door Skin Gap Tolerances Figure 201 AIRCRAFT EQUIPPED WITH SINGLE-POINT PRESSURE REFUELING

52-40-20

Page 201 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR DOORS

i.

STRUCTURAL IDENTIFICATION

DESCRIPTION A. B.

C.

landing gear doors and outboard landing gear doors are covered in this See Figure 1, 52-80-10, for main landing gear inboard door structure repair index. See Figure 1, 52-80-20, for main landing gear outboard door structure repair index. Both inboard

EFFECTIVITY:

ALL

section.

52-80-00

Page SRM-4

1

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR INBOARD DOOR

STRUCTURAL IDENTIFICATION

$$t~

$’LI

1

6-6C

EFFECTIVITY:

Main

ALL

(6

Landing Gear Inboard Door Structure Repair Index Figure 1 (Sheet 1 of 2) 52-80-10

Page SRM-4

2

May 15/92

Learjet STRUCTURAL REPAIR MANUAL DWG. NO.

ITEM

NO.

DESCRIPTION Main Landing Gear Inboard Instl. Main Landing Gear Inboard

2311620 2496200 2311620

8 RH

Door

Assy., LH

Main

Landing Gear Inboard Assy., LH 8 RH

Door

EFF.

MATERIAL

GAGE

3

Door

1

2024-T42 Clad

0.040

2

2311620

DoorPan

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

4130 Steel~

0.071

2

S-627

2311620

4

2327020

DoorPanSupport SupportAngle ´•´•Fitting ´•´•Fitting

3

2024-T351

Doubler

1

2024-T3 Clad

0.032

2311620

´•´•Stopper

1

Nylon

0.189

2311620

´•´•Filler

3

2024-T3

0.100

2311628

Lever

1

2311628

´•´•Plate

1

321 Stainless

0.080

2311628

´•´•Lug ´•´•StopPlate

1

321 Stainless

0.080

1

321 Stainless

0.080

3127010 2311620

5

2311628

7

Hook

2348040

1

4130

Steel~

0.125

2348040

Hook

1

4130 Steel~

0.250

231 i 630

Bracket

2311630

Tee

1

S-592

2311630

Bracket

1

2024-T42 Clad

0.100

Gusset

1

2024-T42 Clad S-646

0.063

1

2311630 2311630

Assy.

´•´•Channel

Replace Replace Replace Replace Replace

i

2327021

Plate

1

2024-T3 Clad

0.120

2311628

Bushing

i

4130 Steel

0.250

CODES

Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

Assy. MountingPlate

2348040

6

Assy.

FIG. NO.

2

2311620 2311620

REPAIR

CODE

1

1

3

FINISH

Replace Replace Replace Replace Replace Replace

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSE-

1

2

QUENT 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

3

31-002 AND SUBSEQUENT

NOTES: Condition Normalized. Condition Annealed.

Main

EFFECTIVITY: SRM4

ALL

Landing Gear Inboard Door Structure Repair Index Figure 1 (Sheet 2 of 2) 52-80-10

Page 2 May 15/92

Learjet Learjet STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR INBOARD DOOR 1.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGELIMITS All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose

or

failed rivet

can cause

increased stress concentra-

progressive joint failure. A careful inspection must be performed to ensure that joint failure has not spread from the area of the loose or failed rivet. (Refer to Chapter 51 for definition of rivet failure.) tions

the

on

(2) Loose

or

remaining

failed

rivets and lead to

screws are not

allowed. A loose

or

failed

screw can cause

increased stress

concen-

progressive joint failure. A careful inspection must be performed to ensure that the joint failure has not spread from the area of the loose or failed screw. trations B.

on

surrounding

screws

and lead to

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, and refinished C.

in accordance with

re-

Chapter 51.

Deformation

(1) Deformation of the main landing gear inboard door,

structure

assembly

or

door

hinges

is not al-

lowed. D.

Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original mate-

E.

Dents

rial thickness

more

than

specified.

(1) Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

G.

H.

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 301.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.)

EFFECTIVITY: SRM-4

a

ALL

52-80-10

Page 101 May 15/92

STRUCTURAL REPAIR MANUAL

Minimum Thickness

Nominal Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.0~6

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure

EFFECTIVITY: SRMII

ALL

101

52-80-10

Page 102 May 15/92

Learjet Learjet

STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR INBOARD DOOR i.

REPAIR

APPROVED REPAIRS NOTE:

All dimensions

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the main landing gear inboard door structure. Learjet Maintenance Manual, Chapter 32, for repairs and maintenance procedures for main landing gear inboard door components such as door seals and door latch mechanism. See Figure 201 for main landing gear inboard door skin gap tolerances.

A.

Refer to

B.

Refer to the basic

C.

are

Main

Landing Gear

Outboard Door 0.040 (f0.020)- Inch Maximum

0.020-Inch h~aximum

FWD

Main

Landing Gear

Inboard Door

~t

(VIEW LOOKING UP) (RH SHOWN, LH TYPICAL) Main

EFFECTIVITY: SRM-4

ALL

Landing Gear Inboard Door Skin Gap Tolerances Figure 201 52-80-10

Page 201 May 15/92

STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR OUTBOARD DOOR

STRUCTURAL IDENTIFICATION

a

,P

66C

EFFECTNITY: SRM-4

Main

ALL

Landing Gear Outboard Door Structure Repair Index Figure 1 (Sheet 1 of 2) 52-80-20

Page Z May 15/92

~Learjetl STRUCTURAL REPAIR MANUAL DWG.

ITEM NO.

EFF.

DESCRIPTION

NO. 2422520

Landing Gear Outboard Assy., LH 8 RH

Main

MATERIAL

GAGE

1

2024-T42 Clad

0.040

1

2024-0 Clad

0.050

Fitting Support Angle

1

2522521

Doubler

1

2522521

Filler

1

5

2522521

1

6

2522521

7

2522521

Support Hinge Assy. Hinge Half (2 ea.) Hinge Pin

3 4

2522521

CODES 1

FIG. NO.

1

Door Pan

2

2422520 2422520 2322522 2522521

REPAIR

CODE

Door

Panel

1

FINISH

495 2024-T42 Clad 2024-T3 Clad

0.100

2024-T3 Clad S520

0.190

0.040

1 1

MS35823-4C

1

MS20253P-1092

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-001 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

~e

EFFECTIVITY:

Main

ALL

Landing Gear Outboard Door Structure Repair Index Figure 1 (Sheet 2 of 2) 52-80-20

Rage 2 SRM-4

Jun 1/95

I

~j Learjet STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR OUTBOARD DOOR i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGE LIMITS All dimensions

NOTE: A.

are

in inches unless otherwise

Fasteners

(1) Loose tions

failed rivets

or

the

on

are

remaining

performed fer to Chapter 51 (2) Loose

or

trations

failed

on

performed

not allowed. A loose

rivets and lead to

to ensure that

B.

specified.

joint

or

failed rivet

can cause

increased stress concentra-

failure. A careful

progressive joint inspection must be the from of loose the area or failed rivet. (Respread

failure has not

for definition of rivet failure.)

screws are not

surrounding

allowed. A loose

screws

to ensure that the

increased stress concenA careful failure. progressive joint inspection must be failure has not spread from the area of the loose or failed screw. or

failed

screw can cause

and lead to

joint

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, C.

and refinished in accordance with

Chapter

re-

51.

Deformation

(1) Deformation of the main landing gear outboard door,

structure

assembly or door hinges is

not al-

lowed. D.

Corrosion(See FigurelOl.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original mate-

E.

Dents

rial thickness

more

than

specified.

(1) Dents are permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch (2.54 mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to

Chapter 51

for

protective

procedures.) replaced or repaired

treatment

if scratches reduce the original material by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings andForgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.)

(2) Structural components

must be

thickness

G.

H.

EFFECTIVITY: SRM-4

ALL

52-80-20

Page 101 May 15/92

STRUCTURAL REPAIR MANUAL

Nominal Thickness

Minimum Thickness

(Inch)

(Inch)

0.016

0.0135

0.020 0.025

0.0175

1

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY: SRM~

ALL

101

52-80-20

Page 102 May 15/92

Learjet ~g Learjet]

STRUCTURAL REPAIR MANUAL MAIN LANDING GEAR OUTBOARD DOOR i.

REPAIR

APPROVED REPAIRS NOTE:

All dimensions

A.

Refer to

B.

Refer to the basic

C.

are

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the main landing gear outboard door structure. Learjet Maintenance Manual, Chapter 32, for repairs and maintenance procedures for main landing gear outboard door components such as door seals and door latch mechanism. See Figure 201 for main landing gear outboard door skin gap tolerances.

Main

Landing Gear

Outbcard Door

0.040 (fO.0U0)- Inch Maximum

0.020-Inch

Maximum

Main

FWD

Landing Gear

Inboard Door

(VIEW LOOKING UP)

(RH SHOWN, LH TMJICAL) 4-57B

Main

Landing Gear

Outboard Door Skin

Figure EFFECTIVITY:

ALL

Gap Tolerances

201

52-80-20

Page 201 May 15/92

Leariet Learlet

STRUCTU RAL REPAIR MANUAL NOSE LANDING GEAR DOORS

STRUCTURAL IDENTIFICATION

i/

IdD

EFFECTIVITY: sRM-4

Nose

ALL

Landing Gear Door Structure Repair Index Figure 1 (Sheet 1 of 2) 52-81-00

Page 1 May 15/92

Learjet Learjet/ STRUCTURAL REPAIR MANUAL DWG. NO.

ITEM

NO.

DESCRIPTION

2391062

EFF.

MATERIAL

GAGE

LH

RH

Door

1

2024-T42 Clad

0. 040

2

2310620

Door Pan

1

2024-T42 Clad

0.050

3

2310620

Door Actuator

1

2024-T42 Clad

0.080

2310620

Door Panel

1

2024-T42 Clad

0.040

2310620 2310620

Support Support

Hinge Assy. Hinge ´•´•Pin

1 1

MS20001Y4-4000

1

MS20001 Y4-3900

5

2310620

Retainer

1

2024-T42 Clad

0.032

6

2310620

Deflector

1

2024-T42 Clad

0.032

CODES 1

FIG. NO.

1

2310620

1 2310620

REPAIR

CODE

Noseianding GearDoorAssy,

1

4

FINISH

Replace Replace Replace Replace Replace Replace Replace Replace Replace

EFFECTIVITIES 23-002 THRU 23-099; 24-100 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-001 AND SUBSEQUENT; 35-002 AND SUBSEQUENT; 36-001 AND SUBSE-

QUENT

Nose

EFFECTIVITY:

ALL

Landing Gear Door Structure Repair Index Figure 1 (Sheet 2 of 2) 52-81-00

Page SRM~

2

May 15/92

Learjet

STRUCTURAL REPAIR MANUAL ALLOWABLE DAMAGE

NOSE LANDING GEAR DOOR i.

ALLOWABLE DAMAGELIMITS

All dimensions

NOTE: A.

are

in inches unless otherwise

specified.

Fasteners

(1) Loose tions

failed rivets

or

on

the

are

not allowed. A loose

or

failed rivet

can cause

increased stress concentra-

rivets and lead to

progressive joint failure. A careful inspection must be that joint failure has not spread from the area of the loose or failed rivet. (Re-

remaining

performed to ensure fer to Chapter 51 for definition of rivet failure.) (2) Loose

or

failed

screws are not

allowed. A loose

or

failed

screw can cause

increased stress

concen-

trations on surrounding screws and lead to progressive joint failure. A careful inspection must be performed to ensure that the joint failure has not spread from the area of the loose or failed screw. B.

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, and refinished C. D.

re-

Chapter 51.

Deformation

(1) Deformation of the nose landing gear door, structure assembly or door hinges is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

in accordance with

more

than

specified.

Dents

(1) Dents

are

permissible, if smooth and without abrupt changes in contour, do not exceed

(2.54 mm) in

depth,

do not exceed 10% of total surface

area

in

one

0.100 inch

(1) square foot, and

are

not

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

G.

H.

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if scratches reduce the original material thickness by more than specified. Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) (2) Structural components must be replaced or repaired if nicks reduce the original material thickness more than specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired.

EFFECTIVITY: sras~

a

ALL

52-81-00

Page 101 May 15/92

STRUCTURAL REPAIR WIANUAL

Minimum Thickness

Nominal Thickness

(Inch)

(Inch) 0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY:

ALL

101

52-81-00

Page sRM-4

102

May 15/92

Learjet STRUCTURAL REPAIR MANUAL NOSE LANDING GEAR i.

DOR

REPAIR

APPROVED REPAIRS

NOTE:

All dimensions

in inches unless otherwise

specified.

Chapter 51 for typical repairs for the nose landing gear door structure. Leajet Maintenance Manual, Chapter 32, for repairs and maintenance procedures for nose landing gear door components such as door seals and door latch mechanism. See Figure 201 for nose landing gear door skin gap tolerances.

A.

Refer to

B.

Refer to the basic

C.

are

0.030

0.030

Inch Maximum

Inch Maximum

0.040

Inch Minimum

0.060

Inch Maximum

(VIEW LOOKING DOWN) M6B

EFFECTIVITY: SRM-4

Nose

ALL

Landing Gear Door Skin Gap Tolerances Figure 201 52-81-00

Page 201 May 15/92

CHAPTER

F USE LAG E

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject FUSELAGE- STRUCTURAL IDENTIFICATION

Description RepairIndex

................................................................53-00-00

1

............................................................................................................................53-00-00

2

...........................................................................................................................53-00-00

NOSE ASSEMBLY

STRUCTURAL IDENTIFICATION

....................................................53-10-00

1

Description Nose Assembly Repair Index ............................................................................................................................53-10-00

(Model 23 Aircraft and Earlu Model 24 Series Aircraft) Nose

Page

2

..................................................53-10-00

Assembly Repair Index

(Late Model 24 Aircraft and Model 25/28/29/31/35/36 Series Aircraft) NOSE ASSEMBLY ALLOWABLE DAMAGE Allowable

Damage Limits

NOSE ASSEMBLY

101

...................................................................................................53-10-00

Approved Repairs STRUCTURAL IDENTIFICATION ALLOWABLE DAMAGE

Allowable Damage Limits FUSELAGE ASSEMBLY REPAIR

53-10-00

201

53-20-00

1

..........................................53-20-00

Description FUSELAGE ASSEMBLY

53-10-00

....................................................................................................53-10-00

REPAIR

FUSELAGE ASSEMBLY

9

..........................53-10-00

...........53-20-00 101

....................................................................................................53-20-00

Approved Repairs

201

..................................................................................................................53-20-00

FUSELAGE FRAMES

Description

.........................................................................................53-20-00

STRUCTURAL IDENTIFICATION

...............................................53-21-00

1

............................................................................................................................53-21-00

FUSELAGE FRAMES ALLOWABLE DAMAGE... Allowable Damage Limits

...............................................53-21-00

53-21-00

FUSELAGE FRAMES- REPAIR

53-21-00

Approved Repairs FUSELAGE STRINGERS -STRUCTURAL IDENTIFICATION

Description

1

ALLOWABLE DAMAGE..........................................................53-22-05

Allowable Damage Limits FUSELAGE STRINGERS -REPAIR

101

....................................................................................................53-22-05

........................................................................................53-22-05

53-22-05

Approved Repairs WINDSHIELD STRUCTURE

Description

Repair

Damage Limits

201

53-24-00 1

WINDSHIELD STRUCTURE Allowable

STRUCTURAL IDENTIFICATION....

............................................................................................................................53-24-00

Windshield Structure

201

.........................................53-22-05

............................................................................................................................53-22-05

FUSELAGE STRINGERS

101

53-21-00

Index

1

.....................................................................................53-24-00

ALLOWABLE DAMAGE

53-24-00 101

....................................................................................................53-24-00

WINDSHIELD STRUCTURE

REPAIR

.................................................................................53-24-00

Approved Repairs

53-24-00

201

FUSELAGE INSTRUMENT PANEL SUPPORT STRUCTURE STRUCTURAL IDENTIFICATION...,.,........................................................................53-25-00

Description

............................................................................................................................53-25-00

I

1

53-Contents

Pagel sRM-4

Jan 15/93

~-j´•tl STRU~TURAL REPAIR MANUAL Chapter Section

Subject

Subject

Page

FUSELAGE INSTRUMENT PANEL SUPPORT STRUCTURE ALLOWABLE DAMAGE

Allowable

Damage Limits

..............................................................................................53-25-00

101

....................................................................................................53-25-00

FUSELAGE INSTRUMENT PANEL SUPPORT STRUCTURE

REPAIR

........................53-25-00

Approved Repairs....

.........53-25-00

201

FUSELAGE CIRCUIT BREAKER PANEL SUPPORT STRUCTURE STRUCTURAL IDENTIFICATION .....................................................................................53-26-00

Description

1

............................................................................................................................53-26-00

FUSELAGE CIRCUIT BREAKER PANEL SUPPORT STRUCTURE ALLOWABLE DAMAGE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .53-26-00 Allowable Damage Limits FUSELAGE CIRCUIT BREAKER PANEL SUPPORT STRUCTURE

101

....................................................................................................53-26-00

REPAIR ...............53-26-00

Approved Repairs FUSELAGE SKINS

.........53-26-00

201

STRUCTURAL IDENTIFICATION....................................................53-28-00

Fuselage Skins Repair Index (Model 23/24 Series Aircraft)

Fuselage

Skins

Repair

(Model 25/28/29 Series Aircraft with 24-1nch PassenaerlCrao Door).

Fuselage

Skins

Repair

53-28-00

1

.53-28-00

4

Index Index

(Model 25128/29 Series Aircraft with 36-inch PassenaerlCrao Door).............................53-28-00

6

Fuselage Skins Repair Index (Model 31/35/36 Series Aircraft) FUSELAGE SKINS Allowable

Damage

FUSELAGE SKINS

Approved Repairs

9

.......................................................................................53-28-00

ALLOWABLE DAMAGE

....................................................................53-28-00

Limits

53-28-00

REPAIR....

101

53-28-00 201

..................................................................................................................53-28-00

FUSELAGE SEAT AND BAGGAGE FLOOR STRUCTURE

STRUCTURAL IDENTIFICATION...,,.........................................................................53-29-00

Description

1

............................................................................................................................53-29-00

FUSELAGE SEAT AND BAGGAGE FLOOR STRUCTURE ALLOWABLE DAMAGE ..............................................................................................53-29-00

Allowable

Damage

Limits

FUSELAGE SEAT AND BAGGAGE FLOOR STRUCTURE

Approved Repairs

Damage

.........,53-30-00 1

ALLOWABLE DAMAGE...........................................................53-30-00

Limits

....................................................................................................53-30-00

TAILCONE ASSEMBLY- REPAIR

Approved Repairs

53-29-00 201

STRUCTURAL IDENTIFICATION

............................................................................................................................53-30-00

TAILCONE ASSEMBLY

Allowable

REPAIR

..................................................................................................................53-29-00

TAILCONE ASSEMBLY

Description

101

....................................................................................................53-29-00

..................................................................................................................53-30-00

101

.........................................................................................53-30-00

201

53-Contents

Page snM-4

2

Tan 15/93

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject

TAILCONE BULKHEAD (FRAME)- STRUCTURAL IDENTIFICATION Tailcone Bulkhead (Frame) Repair Index

......................53-31-00

1

...........................................................................53-31-00

TAILCONE BULKHEAD (FRAME)- ALLOWABLE DAMAGE Allowable Damage Limits

.......................................53-31-00

.........53-31-00

TAILCONE BULKHEAD (FRAME)- REPAIR

Tailcone

53-31-00

STRUCTURAL IDENTIFICATION

Allowable

1

ALLOWABLE DAMAGE..........................................................53-32-00

Damage Limits

101

....................................................................................................53-32-00

TAILCONE STRINGERS- REPAIR

Approved Repairs

201

53-32-00

Stringer Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .,.,. . 53-32-00

TAILCONE STRINGERS

101

53-31-00

Approved Repairs............ TAILCONE STRINGERS

Page

........................................................................................53-32-00

201

..................................................................................................................53-32-00

TAILCONE VENTRAL FIN AND STRINGER

STRUCTURAL IDENTIFICATION ....53-33-00 Tailcone Ventral Fin and Stinger Repair Index (Model 35/3 6 Series Aircraft) 53-33-00 53-33-00 Stinger Repair Index -(Model 31 Series Aircraft). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAILCONE VENTRAL FIN AND STRINGER ALLOWABLE DAMAGE Allowable Damage Limits TAILCONE VENTRAL FIN AND STRINGER REPAIR 53-33-00

1

5

.....................53-33-00

....................................................................................................53-33-00

Approved Repairs Tailcone Dorsal

STRUCTURAL IDENTIFICATION

....53-34-00

Assembly Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-34-00

TAILCONE DORSAL ASSEMBLY Allowable

201

..................................................................................................................53-33-00

TAILCONE DORSAL ASSEMBLY

Damage Limits

Approved Repairs

1

ALLOWABLE DAMAGE

.........................................53-34-00

101

....................................................................................................53-34-00

TAILCONE DORSAL ASSEMBLY

101

REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-34-00 201

..................................................................................................................53-34-00

TAILCONE SKINS

STRUCTURAL IDENTIFICATION Tailcone Skins Repair Index TAILCONE SKINS ALLOWABLE DAMAGE

...................................................53-35-00

..................53-35-00

1

....................................................................53-35-00

Allowable

Damage Limits

TAILCONE SKINS

101

....................................................................................................53-35-00

REPAIR

..................................................................................................53-35-00

Approved Repairs

.........53-35-00

DELTA FINS

STRUCTURAL IDENTIFICATION.......... Delta Fins Repair Index DELTA FINS ALLOWABLE DAMAGE Allowable Damage Limits DELTA FINS REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .53-36-00

1

.........................................................................................................53-36-00

.........53-36-00 101

....................................................................................................53-36-00

Approved Repairs

201

..................................................................................................................53-36-00

FUSELAGE FUEL CELL

STRUCTURAL IDENTIFICATION

..........................................53-40-00

Description

53-40-00

FUSELAGE FUEL CELL ALLOWABLE DAMAGE Allowable Damage Limits ....................................................................................................53-40-00

201

.........,53-36-00

1

..........................................................53-40-00

101

53-Contents

Page3 SRM-4

Tan 15/93

STRUCTURAL REPAIR MANUAL Chapter Section

Subject

Subject FUSELAGE FUEL CELL

Approved Repairs

REPAIR

.........................................................................................53-40-00

201

..................................................................................................................53-40-00

FUSELAGE FUEL CELL STRUCTURE STRUCTURAL IDENTIFICATION .................53-40-05 53-40-05 Fuselage Fuel Cell Structure Repair Index FUSELAGE FUEL CELL STRUCTURE ALLOWABLE DAMAGE..................................53-40-05 Allowable Damage Limits FUSELAGE FUEL CELL STRUCTURE

Approved Repairs Description

REPAIR

................................................................53-40-05

201

..................................................................................................................53-40-05

STRUCTURAL IDENTIFICATION

......................................53-50-00

1

............................................................................................................................53-50-00

ALLOWABLE DAMAGE

KEELBEAM ASSEMBLIES Allowable

Damage

Limits

....................................................,.53-50-00

101

....................................................................................................53-50-00

REPAIR

KEELBEAM ASSEMBLIES

Approved Repairs

.....................................................................................53-50-00

201

..................................................................................................................53-50-00

FORWARD KEELBEAM

STRUCTURAL IDENTIFICATION

......53-51-00 53-51-00

Forward Keelbeam Repair Index FORWARD KEELBEAM ALLOWABLE DAMAGE Allowable Damage Limits

FORWARD KEELBEAM

53-51-00 53-51-00

1 ....................................................53-53-00

101

Allowable Damage Limits UNDERWING KEELBEAM REPAIR

....................................................................................................53-53-00

Aft

Allowable

201

..................................................................................................................53-53-00

Limits

REPAIR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Approved Repairs

......................................................53-55-00

1

..................................................................................53-55-00

ALLOWABLE DAMAGE

Damage

AFT KEELBEAM

53-53-00

STRUCTURAL IDENTIFICATION

Fuselage Keelbeam Repair Index

AFT KEELBEAM

201

STRUCTURAL IDENTIFICATION....................................53-53-00

Underwing Keelbeam Repair Index.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .53-53-00 UNDERWING KEELBEAM ALLOWABLE DAMAGE

Approved Repairs

101

53-51-00

REPAIR

UNDERWING KEELBEAM

1

53-51-00

Approved Repairs

AFT KEELBEAM

1

101

....................................................................................................53-40-05

KEELBEAM ASSEMBLIES

Page

.......................................................................53-55-00

53-55-00

101

53-55-00 53-55-00

201

53-Contents

Page 4 SRM-´•I

Jan 15/93

Learjet Learjet/

STRUCTURAt REPAIR MANUAL Chapter

Chapter I

Section

Subject 53-TJTLE 53-List of Eff. 53-List of Eff. 53-List of Eff. 5S-Contents 53´•-Contents 53-Contents

Page

Pgs. Pgs. Pgs.

53-Contents

1

2

3 1

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8

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32

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May 15/92 May 15/92 May 15/92

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7 8 9 10 12

Pages; Destroy Superseded or Deleted Pages. Asterisk indicates pages revised, deleted, or added by current revision. The portion of the text affected by the current revision is indicated by a vertical lii~e in the outer Insert Latest Revised

margin of the

page. 53

sRM4

List of Effective

Pages Page 1

Jun 1/95

Learjet ~Learjet STRUCTURAL REPAIR MANUAL Chapter

Chapter I

Section

Subject

Page

53-22-05

13

53-22-05

14

53-22-05

15

53-22-05

101

53-22-05

102

53-22-05

201

53-24-00

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53-24-00

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1

Jan 15/93 Jan 15/93 Jun 1/95 Jun 1/95 Jun 1/95 Jan 15/93 Jan 15/93 Jan 15/93

53-29-00 1 53-29-00 1 1*53-29-00 1"53-29-00 1*53-29-00 53-29-00 1

1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1

2

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1 1

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"53-34-00

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1 1

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53

sRM-4

Date

Jun 1/95 Tun 1/95 Jun 1/95 May 15/92 May 15/92 May 15/92

List of Effective

Pages Page 2

Jun 1/95

Learjet Learjet 1

STRUCTURAL REPAIR MANUAL Chapter

Chapter

Section

Section

Subject

Page

53-35-00 53-36-00 53-36-00 53-36-00 53-36-00 53-36-00 53-40-00 53-40-00

201 1

53-40-00 53-40-00 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-40-05 53-50-00 53-50-00 53-50-00 53-50-00 53-50-00 53-51-00 53-51-00 5331-00 53-51-00 5351-00 53-51-00 *53-53-00 ~53-53-00 *53-53-00 *5333-00 *53-53-00

102 201

*53-53-00

6

*53-53-00 53-53-00 53-53-00

7

53-53-00 53-55-00 53-55-00

2

101 102 201 1

101

1

2

3 4

5 6 7

8 9 10 11

101 102 201 1

101 102 201 202 1 2

3 101 102

201 1 2

3 4

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Date

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subject

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Jan 15/93 Tan 15/93 Jan 15/93 Tan 15/93 Jan 15/93 Jan 15/93 Jan 15/93 Jan 15/93 Jan 15/93 Jan 15/93 Jan 15/93 May 15/92 May 15J92 May 15/92 May 15/92 May 15/92 May 15/92

May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 May 15/92 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 Jun 1/95 May 15/92 May 15/92

May 15/92 May 15/92 May 15/92

53

List of Effective

Pages Page 3

Jun 1/95 SRM~

Learjet STRUCTURAL REPAIR MANUAL FUSELAGE- STRUCTURAL IDENTIFICATION i.

DESCRTPTION NOTE:

The the

following structural data covers the basic non-modified aircraft. When applicable, refer to appropriate kit drawing for additions, modifications and changes to the structural compo-

nents and assemblies.

A. B.

main frame is constructed of frames, stringers, keelbeams, longerons, a forward and aft and frames around openings. bulkhead pressure Located between frame 1 and frame 34 are transverse frames spaced approximately 3.5 to 17 inches apart. The tailcone contains canted frames for attachment of the vertical stabilizer. Cutouts are located around the perimeter of the frames for stringer clearance. Frames 2 and 4 terminate where they The

fuselage

wheel well. Frame 3 terminates where it meets the nose compartment access door nose wheel well. Frames 6 through 8 terminate where they meet the windshield. opening Frame 11, and frame 12 ton aircraft eauirtt?ed with 36" Ilassenaerlcrau door), terminate where they meet the passenger/crew door. Frames 16 through 21 terminate when the lower end meets a longeron meet the

nose

and the

wing passes through the fuselage. Longitudinal stringers are located around the perimeter of the frames, and are spaced approximately 5 inches apart. The stringers are aluminum extrusions cut to various lengths. The forward, underwing and aft keelbeam assemblies, located along the bottom side of the aircraft, provide a major structural component used to complete the fuselage structure when the wing assembly is installed. The keelbeams also provide housings for fuel and hydraulic lines and control cables. Fuselage frames are interrupted at the keel and are continued through the keel by webs. The floorboards are secured on top of the forward keelbeam and become a part of the aircraft structure. Access covers, located along the bottom side of the keelbeams, form a smooth aerodynamic surface on the bottom side of the aircraft. Refer to Chapter 51 for forward, underwing and aft keelbeam station locations. Refer to 53-50-00 for keelbeam Master Repair Indexes. A longeron extends longitudinally down each side of the fuselage at the point where the fuselage and wing intersect. where the

C. D.

E.

F.

an ah pressure bulkhead are installed in the aircraft. The forward pressure bulkhead is located at frame 5, the aft pressure bulkhead location will vary depending upon aircraft model and fuel system configuration. Refer to Chapter 51 for forward and aft pressure bulkhead locations.

A forward and

EEFECTIVITY: SRM-4

ALL

53-00-00

Page 1 May 15/91

Learjet Learjetl

STRUCTURAL REPAIR MANUAL

Chapter/ Section/ Item 1

n

Nose

53-10-00

4

Assembly Fuselage Assembly Tailcone Assembly Fuselage Fuel Tank Assembly

5

Keelbeam Assemblies

53-50-00

2

3

53-20-00 53-30-00

53-40-00

(TYPICAL)

Fuselage

Structure Master

Figure EFFECTNITY:

ALL

Repair Index

1

53-00-00

Page SRM~

2

May 15/91

Learjet I Learjet STRUCTURAL REPAIR MANUAL NOSE AS SEMBLY

i.

STRUCTURAL IDENTIFICATION

DESCRIPTION A.

The

nose

assembly

consists of the structure

structure consists of five

assembly

from frame

one

to and

including

frame 5. The

(5) major bulkhead assemblies, stringers, minor structural subassemblies,

and skins. B.

assembly provides mounting provisions for various avionics and radio equipment, various nose landing gear when retracted. Two nose access doors are inthe to aerodynamic configuration and protection of the equipment installed withcorporated provide in the nose assembly. Two nose wheel doors complete the aerodynamic configuration on the lower side of the nose assembly and also provides protection for the nose gear. (Refer to Chapter 52 for additional information pertaining to nose doors.)

The

nose

aircraft systems, and storage for the

EFFECTIVITY:

ALL

53-10-00

Page sRM-a

1

May 15/92

STRUCTURAL REPAIR MANUAL NOSE ASSEMBLY

STRUCTURAL IDENTIFICATION

(TYPICAL) 14-194C

EFFECTIVITY: SRM-b

Assembly Repair Index Figure 1 (Sheet 1 of 7)

Nose

23-002 THRU 23-099; 24-100 THRU

24-229, EXCEPT 24-218

53-10-00

Page 2 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

Nose

2311000 1

2311010

1

2311010 2311010 2311010

2311010 2311010

2311010 2311010 2311010 2311020

S151-1 3

2311030

I 1

2311030 1 2311030

2311030 2311030

1 1 1

2311030 4

2311030

1

2311040

1

2024T42 Clad

0.040

F4-1

2024T42 Clad

0.080

F4-1

Bracket

2

2024T42 Clad

2

S-549

1

2024T42 Clad

0.040

F4-1

0.040

F4-1

Bulkhead Instl., Frame No. 2

1

2024T42 Clad

2

S-633

3

S-633

3

S-591

I

0.040

1 1 1 1

I I I I

Replace Replace Replace Replace

0.040

1

1

51-70-04

2024-T42 Clad

0.040

1

I

Replace

5

2024-T3 Clad

0.040

1

I

6

2024-T3 Clad

0.040

1

I

Replace Replace

1

2024-T42 Clad

0.032

1

1

51-70-04

1

2024-T3 Clad

0.032

1

I

1

2024-T3 Clad

0.032

1

2024-T3 Clad

0.040

1 1

I I

Replace Replace Replace

2024-T3 Clad

0.040

1

2024-T3 Clad

0.040

Gusset

1

2024-T42 Clad

0.040

Bracket(2ea.) FrameWeb(eea.) Clip(4ea.)

4

2024-T42 Clad

1

2024-T42 Clad

1

Gusset(2 ea.) Frame Web (2 ea.) Clip Connecting Plate Angle Bulkhead Instl., Frame No. 4 Frame Web (2 ea.)

I

1 1

Bulkhead Instl., Frame No. 3 Gusset

F4-1

0.050

1

Replace Replace Replace Replace Replace Replace

1

1 1

2024-T42 Clad

0.040

1

1

51-70-04

Connecting Angle

1

2024-T42 Clad

0.063

8

2024-T3 Clad

0.032

I I

Replace

Bracket

1 1

Angle

5

2024-T42 Clad

0.040

2311030 1

Filler

7

2024-T3 Clad

0.040

2311030 1

Gusset

5

2024-T3 Clad

0.040

I I I

2311030

Gusset(2ea.)

6

2024-T3 Clad

0.040

1 1 1 1

2311040

SpliceAngle

1

2024-T42 Clad

0.040

1

I

Channel(2ea.)

1

2024-T42 Clad

0.040

1

I

Replace Replace Replace Replace Replace Replace

0.050

1 I

I I

2311040 231 1 040

1

2311040 1

2311030

1

2311040 5

1 2

2311020 2311020

REPAIR FIG. NO.

CODE

FlangeRing(eea.) ZeeClip

ReinforcementAngle (2ea.) Stiffener(2ea.)

2311020

IFINISH

I GAGE

Assembly, Fuselage

2311020

2311020

I MATERIAL

Bulkhead Instl., Frame No. 1

Brace

1

I EFF.

SupportAngle(2ea.) 1 Angle Channel (2 ea.) 1 Support (2 ea.) 1 I´•´•Support

2311010 2

I DESCRIPTION

2311050 2411050

1 1

2310525 2310525 2310525 2310526

2310526

1

Bulkhead Instl., Frame No. 5

11

Doubler(2 ea.) Supportlnstl.,LH&RH SupportWeb Angle Support Instl., LH 8 RH Support

1 1

2024-T3 Clad

1

I

1

2024-T42 Clad

0.032

2024-T42 Clad

0.032

1 1

I

1

2024-T42 Clad

0.032

1

I

Replace

Replace Replace Replace Replace

1 1

Replace

Assembly Repair Index Figure 1 (Sheet 2 of 7)

Nose

EFFECTIVITY: SRM~

23-002 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218

53-10-00

Page 3 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

I DESCRIPTION

2311574

Supportlnstl.,LH&RH Support(2ea.) Supportlnstl.,LH&RH Support 1 Support Instl., LH 8 RH SupportWebb Support Instl., LH 8 RH 1 SupportWeb I´•´•Segmentlnstl. Support Support ´•´•Anglelnstl.,LH&RH Supportlnstl.,LH&RH Support Supportlnstl.,LH&RH Support Suppartlnstl.,LH&RH Support(8 ea.) SafetyBand SupportAngle

2311581

Frame Piece Instl.

2310527 2310527 2310533 2310533 2310531 2310531 2310538 2310538

2311267 2311267 2511229 2310533 2311575 2311575 2311577 2311577

2311583 2311583 2311050

2311581 2311580

2310521 2310521 2310521 2310522 2310522 2310522

1

2310523

2310537 2310532

2310537

1

IFINISH MATERIAL

GAGE

REPAIR FIG. NO.

CODE

1

2024-T42 Clad

0.032

2024-T42 Clad

0.040

2024-T42 Clad

0.040

2024-T42 Clad

0.040

4

2024-T42 Clad

0.063

1

I

4

2024-T42 Clad

0.063

1

I

Replace Replace

2024-T42 Clad

0.040

1

I

Replace

2024-142 Clad

0.080

1

I

Replace

1

2024-T42 Clad

0.032

1

2024-T3 Clad

0.063

I

4

2024-T42 Clad

0.040

Replace Replace Replace

0.040

1

I

Replace

I

Replace Replace Replace

1

1

I

Replace

I

Replace

i

Replace

1 1 9 9

1

4 4

F4-1

Replace

4

1 1 1 1 1 1

F4-1

1 F4-1

1

Frame

2311584

I EFF.

1

2024-T42 Clad

Stiffener, LH RH Bearing Assy., LH 8 RH Support Instl., LH 8 RH

1

Casting

1

2024-T42

0.040

1

Support Angle Supportlnstl.,LH&RH Support Angle Washer(2 ea.) Support Instl., Nose Gear Support Instl., Nose Gear SupportAngle(3 ea.) SupportAngle(2 ea.)

1

2024-T42 Clad

0.071

1

I

1

2024-T42 Clad

0.063

1

I I

1

1 1

2024-T42 Clad

0.071

1

2024-T42 Clad

0.063

1

2024-T3 Clad

0.100

1 1 1

4

2024-T24 Clad

0.080

1

I

1

2024-T24 Clad

0.063

1

I I

I

Replace Replace Replace

4 9

2310532

Channel

1

2024-T24 Clad

0.063

1

2310532

Angle(2 ea.)

9

2024-T24 Clad

0.080

1

Web

1

2024-T24 Clad

0.080

1

I

Replace Replace Replace Replace Replace

1

Casting

I

1

51-71-00

2310532

2310537

2311579 2310509 2310509 2310510

´•´•Fitting, NoseWheelActuator Channellnstl.,LH&RH Channel

1 1

Channellnstl.,LH&RH

I

2024-T42 Clad

0.032

1

I

Replace

1 1

I I

Replace Replace

1

2310510

Channel

1

2024-T42 Clad

0.071

2310510

Angle

1

2024-T42 Clad

0.071

Assembly Repair Index Figure 1 (Sheet 3 of 7)

Nose

EEFECTIVITY: SRM-4

23-002 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218

53-10-00

Page 4 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

I DESCRIPTION

I EFF.

I MATERIAL

2310513 I´•´•HorizontalBeam Instl.

11

´•´•´•"I"Beam

11

S-642

11

2024-T42 Clad

0.071

11

2024-T42

0.063

2310513

Plate

2310513 231 0511

´•´•´•Clip

2310514

1

Doubler

Assy.,

LH 8 RH

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

1

I

F4-1 F4-1

1

I

13

2310514

Doubler

13

2024-T42 Clad

0.063

F4-1

2310514

Filler

13

2024-T3 Clad

0.050

F4-1

2310514

Channel

13

2024-T3 Clad

0.063

F4-1

2311583 I´•´•Beamlnstl.

1

2311583

1

4130 Steel

0.080

F8-1

1

4130 Steel

0.080

F8-1

1

4130 Steel

0.080

F8-1

1

S-566

Channel, Upper(2ea.) Channel, Lower (2 ea.)

2311583 2311583

Splice Plate ´•´•´•SupportTee(2ea.)

2311583

Bulkhead Beam Instl., LH 8 RH Beam Assy.

2311667

2311667 2311667 2311667

1

2311668 2311668 2311669

2311669 2310505 1 2310505

2310505 2310505 2310505

2310506 1 2310506 2310506

2310507

2310508

15

15

Bulkhead Beam Instl. Beam Assy., LH 8 RH

1

1

Bulkhead Beam Instl.

14

LH 8 RH

Replace

S-630

I

I

F4-1

Replace

I

I

I

2024-T42 Clad

0.080

F4-1

1

2024-T3 Clad

0.032

F4-1

1

2024-T42 Clad

0.040

F4-1

14

1

Assy., LH 8 (2 ea.) Splice Plate

I I I

1

I 2024-T42 Clad

0.032

F4-1

14

2024-T3 Clad

0.032

F4-1

RH

14

1

I

I

14

2024-T42 Clad

0.032

F4-1

14

2024-T3 Clad

0.032

F4-1

RH

14

1

I

I

14

2024-T42 Clad

0.032

F4-1

2024-T3 Clad

0.032

F4-1

9

6061-T6 Clad

0.063

F4-1

2311050

Web

1

2024-T3 Clad

0.032

F4-1

1

2024-T42 Clad

0.040

F4-1

1

2024-T3 Clad

0.125

F4-1

2311050

Plate

I

Replace Replace Replace

I

Replace Replace Replace

I

Replace Replace Replace Replace

14

14

Splice

Replace Replace Replace Replace

14

FramePiece

1

I

I

14

2311059 2311050

Replace Replace Replace

1

´•Channel(2ea.) ´•SplicePlate ´•Clip

Channel

2310508

F4-1

15

Beam

2310508

I

Bulkhead Beam Instl., LH 8 RH ´•´•´•Beam

BulkheadBeamlnstl.

2310508

I

15

Beam Assy., LH 8 ´•Channel(2ea.) Splice Plate

2310507

S-630

15

Bulkhead Beam Instl., LH 8 RH ´•´•´•Beam

BulkheadBeamlnstl.

2310507

S-571

I I I

´•´•´•´•Clip

Assy.,

Replace Replace Replace

I I I

S-630

´•SplicePlate

2310507

1

15 15

Channel

Replace Replace Replace

15

´•´•´•´•Bsam

Beam

2310506 1

Replace Replace Replace

(2 ea.)

Doubler

Replace Replace Replace

Nose

Assembly Repair Index Figure 1 (Sheet 4 of 7)

EFFECTIVITY:

23-002 THRU

23-099; 24-100 THRU 24-229, EXCEPT 24-218

53-10-00

Page 5 SRM-4

Tan 15/93

Learjet ~Learjefl STRU~TURAL REPAIR MANUAL ITEM NO.

DWG. NO.

I

I EFF.

2311050

´•´•DoublerAssy.

1

2311050

´•Doubler

1

MATERIAL

I IFINISH I GAGE CODE

2024-T42 Clad

0.050

F4-1

1

2024-T3 Clad

0.080

F4-1

20

2024-T3 Clad

0.050

F4-1

2311050

Angle SpliceAngle(2ea.) ´•´•Angle(4ea.)

10

S-545

2311050

Reinforcement

16

2024-T3 Clad

0.071

F4-1

2311050

Reinforcement

17

2024-T3 Clad

0.100

F4-1

2311050

Filler(2ea.) Filler(2ea.)

14

2024-T3 Clad

0.032

F4-1

2311050

15

2024-T3 Clad

0.050

F4-1

2311050 1

Plate

19

2024-T3 Clad

0.063

2311050 2311050

´•´•Shim,Laminated

2311050 6

I DESCRIPTION

2311250 1

18

Nose Wheel Box Instl.

2311250

Channel(2ea.) Angle(Gea.) Angle(2ea.) BulkheadSegment

2311250

SupportAngle(eea.)

2311250 2311250

2311250

REPAIR FIG. NO.

Replace Replace Replace

F4-1

0.062

1

I

1 1 1 1

I I I I

I

I

1 1

2024-T42 Clad

0.040

1

2024-T3 Clad

0.040

1

2024-T42 Clad

0.080

1

2024-T42 Clad

0.040

1

S-549

1

2024-T42 Clad

1

S-306

I

I

1

2024-T42 Clad

0.040

1

I

1

2024-T3 Clad

0.032

1

I

1

2024-T3 Clad

0.032

1

2024-T42 Clad

0.040

Reinforcement Plate

1

2024-T3 Clad

0.050

1

I

2311250

EndPlate

1

2024-T42 Clad

0.050

2311250

AftSidePlate,LH&RH

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1 1 1 i

I I I i

1

2024-T42 Clad

0.063

1

1

2024-T3 Clad

0.040

1

2024-T42 Clad

0.050

1

S-512

1

S-571

SealAngle 2311250 ´•´•Seal(Fwd) 2311250 ReinforcementAngle 2311250 TopPlate(Fwd) 2311250 1 Top Plate (Aft) 2311250 Pan,LH&RH(Bea.)

I

2311250

2311250 1

2311250

Support(2ea.) Clip ´•´•BracketAssy. Bracket(2ea.) Gusset(4ea.) Support ´•´•Angle(2ea.) ´•´•Angle(Sea.)

2311250

2311250 2311250 2311250

2311250 2311250 2311250

I 0.032

I

I I

I I

1

I I

I I

I I

Filler

1

2024-T3 Clad

0.040

1

I

2311250

SupportChannel(2ea.) Pan(eea.) Cover(Gea.) Clip

1

2024-T42 Clad

0.050

1

2024-T3 Clad

0.040

1 1

I I

1

2024-T42 Clad

0.032

1

I

1

2024-T42 Clad

0.050

Doubler

1

2024-T42 Clad

1 1

I I

1

MS20001 V4

I

I

1

2024-T42 Clad

0.040

1

2024-T42 Clad

0.032

1 1

I I

2311250 2311250 2311250

´•´•HingeHalf

2311250 2311250

1

2311250

1

Channel, LH 6 RH Aft Top Plate, RH

Nose

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

0.062

I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Assembly Repair Index

Figure EFFECTIVITY:

Replace Replace

1

2311250 2311250

Replace Replace Replace Replace Replace Replace

1 (Sheet 5 of 7)

23-002 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218

53-10-00

Page SRM-4

6

Jan 15/93

Learjet STRUCTURAL REPAIR MANUAL ITEM NO.

I

DWG.

1

2311250 2311250 2311250

2311250

1

2311250 1

2317031 1 2317031 2310612

1

2310612 2411001 2310720 2311450 2311450 2311450 2311450

1

2311450

FIG. NO.

2024-T42 Clad

0.032

1

I

2024-T42 Clad

0.032

1 I

I

Doubler

1

2024-T3 Clad

0.050

Angle

1

0.040

Shim

1

2024-T3 Clad 2024-T3 Clad

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

I

Angle Clip Doubler(2 ea.) Bracket Assy.

F4-1

Replace Replace

2024-T42 Clad

0.032

1

1

51-70-02

8 RH

12

2024-T42 Clad

0.032

1

1

51-70-02

2024-T42 Clad

0.040

1

I

Replace

0.050

1

I

I

I

Replace Replace

I I

Replace Replace Replace

1 1

Access Door Instl.

SplicePlate Lip, Lower (2 ea.)

I´•´•DoorAssy. (Refer to Chapter 52)

1

I F4-1

1

Equip. Splice, Plate (2 ea.)

Channel

1 1

11

Nose

2311000 1

0.040

Replace Replace Replace Replace Replace Replace

8 RH

HatSection

2311450

REPAIR

CODE

1

´•´•Stiffener

2311450

IFINISH

I GAGE

1

Bracket

1 1

I MATERIAL

SidePlate,LH

I´•Bradtetlnstl., RH

2310720

I EFF.

Side Plate (2 ea.)

Skin, LH Skin, LH

2311500

1 1

2024-T3 Clad

1

S-522

1

1

2024-T3 Clad

0.050

1

2024-T42 Clad

0.040

1

2024-T42 Clad

0.050

I 1 1

0.050

1

1 4

2024-T42 Clad

No. 19 LH 8 RH

1

S-554

No. 17 LH 8 RH

1

S-554

No. 16 LH 8 RH

1

S-554

No. 14 LH 8 RH

1

S-554

1

I

Replace

1

I

1

51-70-04

1

1

51-70-04

1 1

1 I

i 1

51-70-04

I I I I

1 1 1 1

51-70-04

2311000

1

Stringer, Stringer, Stringer, Stringer,

2311000

1

Stringer,

No. 13 LH 8 RH

1

S-522

Stringer, Stringer, Stringer, Stringer,

No. 12 LH 8 RH

1

S-554

No. 18 LH 8 RH

1

5-554

No. 11 LH 8 RH

1

S-566

1 1 1 1

No. 10 LH 8 RH

1

S-554

1

I

1

51-70-04

15 LH 8 RH

14

S-566

15

S-554

I I

1 1

51-70-04

15 LH 8 RH

1 1

7

2311000

8

2311000 2311000

9

I DESCRIPTION

NO.

2311000 2311000 10

2311000

11

2311000 2311000 2311000

Stringer, No. Stringer, No.

51-70-04 51-70-04 51-70-04 51-70-04

51-70-04

Assembly Repair Index Figure 1 (Sheet 6 of 7)

Nose

EFFECTIVITY:

23-002 THRU 23-099; 24-100 TKRU 24-229, EXCEPT 24-218

53-20-00

Page SRM~

7

May 15/92

Learjet STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

1

23-002 THRU

2

23-002 THRU

23-099; 24-100 THRU 24-229, EXCEPT 24-218 23-099; 24-146 THRU 24-229, EXECPT 24-218

3

23-002 THRU 23-014

4

24-100 THRU

5

23-002 THRU

8

24-229, EXCEPT 24-218 23-099; 24-100 THRU 24-145 24-146 THRU 24-229, EXCEPT 24-218 23-015 THRU 23-099; 24-100 THRU 24-124 24-122, 24-123, 24-140 THRU 24-229, EXCEPT 24-218

9

23-002 THRU 23-099

6

7

11

23-015 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218 23-002 THRU 23-099; 24-100 THRU 24-119

12

24-120 THRU

13

24-150 THRU

10

24-229, EXCEPT 24-218 24-229, EXCEPT 24-218

14

23-002 THRU 23-029

15 16

23-030 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218 23-002 THRU 23-009

17

23-01 0 TH RU

18

23-002 THRU 23-069

23-099; 24-1 00 TH RU 24-229, EXCEPT 24-21 8

19

23-070 THRU

20

24-100 THRU 24-129

23-099; 24-100 THRU 24-229, EXCEPT 24-218

NOTES:

Laminated shim stock, 0.002 sheet.

or

0.003 lamination per MIL-S-22499

Type

1 Class 1

or

Class 2 1145-H19 aiumi-

num

Nose

Assembly Repair Index Figure 1 (Sheet 7 of 7)

EFFECTIVITY:

23-002 THRU 23-099; 24-100 THRU 24-229, EXCEPT 24-218

53-10-00

Page 8 May 15/92

STRUCTURAL REPAIR MANUAL NOSE ASSEMBLY

STRUCTURAL IDENTIFICATION

(TYPICAL) 14-194C

EFFECTIVITY: srud~

Nose

Assembly Repair Index Figure 2 (Sheet 1 of 7)

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005;

53-10-00

29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

Page 9 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ITEM

NO.

I

DWG. NO.

2311010

1

FIG. NO.

Bulkhead Instl., Frame No. 1

FlangeRing(2ea.)

1

202´•4T42 Clad

0.040

F4-1

2

2024T42 Clad

0.080

F4-1 F4-1

2418119

Zee

3

2024T42 Clad

0.080

2311010

Bracket

2

2024T42 Clad

0.050

2418119

Support

3

2024T42 Clad

0.063

2311010

DoublerPlate

2

2024T3 Clad

0.050

2418119

Zee

3

2024T42 Clad

0.063

2311010

2

S-549

2311010

SupportAngle(2ea.) Angle(2ea.)

4

2024T42 Clad

0.040

F4-1

2311010

Channel

4

2024T42 Clad

0.040

F4-1

2311010 1

Frame

5

2024T42 Clad

0.040

F4-1

2311010

Flange Door

5

202´•4T42 Clad

0.040

F4-1

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

2311010

Support Angle

6

S-633

2311010

´•´•SupportAngle ´•´•SupportAngle

3

S-633

7

S691 0.063

F4-1

Replace

2311020

1

Seal

(2 ea.)

ChannelAssy.(2ea.) ChannelAssy.(2ea.) 1

Bulkhead Instl., Frame No. 2

2311020

ReinforcementAngle (2 ea.)

2311020

Stiffener

8

S-556

3

2024T42 Clad

1

F4-1

1

F4-1

F4-1 F4-1

I

I

1

I

1

2024-T3 Clad

0.040

1

2024-T3 Clad

0.040

1 1 1 1

I I I

Replace Replace Replace Replace

2311020 1

Stiffener

1

202´•4-T42 Clad

0.040

2311020

Gusset

1

2024-T42 Clad

0.040

2311020

FrameWeb(2ea.) Clip(G ea.)

1

2024-T42 Clad 2024-T42 Clad

0.040

1

1

51-70-04

0.040

1

I

Replace

S151-1

2311030 2311040

9

Bulkhead Instl., FrameNo. 3 Gusset

1 2311030 2311030

FrameWeb

1

1

1 1

Bulkhead Instl., Frame No. 4

2024-T3 Clad 2024-T42 Clad

0.040

1

I

Replace

0.032

1

1

51-70-04

1 1

2024-T42 Clad

0.040

1

1

51-70-04

2311040

FrameWeb(2ea.) ConnectingAngle

1

2024-T42 Clad

0.063

Bracket

i

2024-T3 Clad

0.032

2311030

Gusset

10

1 1 1

I

2311040 1

I I

Replace Replace Replace Replace Replace

2311040

5

REPAIR

CODE

Zee

2418120

4

IFINISH GAGE

2311010

2418120

3

I MATERIAL

2311010

2311010

2

I EFF.I

NoseAssembly, Fuselage

2511500 1

I DESCRIPTION

2311040

1

2311040

1

2311050

1 1

2411050 2411050 2310525

2310525 2310525

Splice Angle (2 ea.) Channel(2 ea.) Bulkhead Instl., Frame No. 5 Bulkhead Instl., Frame No. 5

Doubler(2ea.) Supportlnstl.,LH&RH SupportWeb Angle

2024-T3 Clad

0.040

1

2024-T42 Clad

0.040

1

2024-T42 Clad

0.040

1 1

0.040

1

I

I 1 1

I i

I

11

12

2024-T3 Clad

1 1

I

I

1

2024-T42 Clad

0.032

1

2024-T42 Clad

0.032

Replace Replace Replace Replace

Assembly Repair Index Figure 2 (Sheet 2 of 7)

Nose

EFFECTIVITY: SRM~

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

53-10-00

Page 10 May 15/92

Learjet ~Learjetl STRUCTWRAL REPAIR MANUAL ITEM NO.

I

DWG. NO.

I DESCRIPTION

2310526 2310526 2310527 2310527

I EFF.

Supportlnstl.,LH&RH Support Supportlnstl.,LH&RH Support(3 ea.)

1 1

MATERIAL

0.032

i

2024-T42 Clad

0.032

2024-T42 Clad

0.040

2024-T42 Clad

0.032

2024-T42 Clad 2024-T42 Clad

0.063

1

2024-T42 Clad

0.040

2024-T42 Clad

0.080

RH

1

2310533

1

2311575

Support Supportlnstl.,LH&RH SupportWeb I´•´•Segmentlnstl. Support Support Supportlnstl.,LH&RH Support

2411577

Supportlnstl.,LH&RH

1

2411577

Support Support Instl., LH 8 RH Support(8 ea.) Support Plate (2 ea.) Angle (2 ea.) SafetyBand Support Angle

1

1

2024-T42 Clad

0.032

1

2024-T3 Clad

0.040

1

2024-T42 Clad

0.050

1

2024-T3 Clad

0.063

i

2024-T42 Clad

Frame Center Piece Instl.

1

2310538 2311267 2311267 2511229 2311575

1

2411583 2311583

1

2411052 2411052 2411058

1

2411574 2411581 2411584 2311580

1

2488296

1 13 14

1

2310522

Replace

1

I

Replace

i

I

Replace Replace

1

I

Replace

1

I

Replace

0.063

F4-1

1

I

0.040

1 1

I I

Replace Replace Replace Replace Replace

0.040

1

I

Replace

2024-T42 Clad

1

Casting

Bearing Assy.

1

2024-T42 Clad

0.040

1

2024-T42 Clad

0.040

1 1

I

Doubler

Replace Replace

1

2024-T42 Clad

0.063

1

I

1

2024-T42 Clad

0.080

1

I

Replace Replace

1

2024-T42 Clad

0.071

1

2024-T42 Clad

0.063

1 1

I I

Replace Replace

1

2024-T42 Clad

0.071

1

2024-T42 Clad

0.063

1 1

I I

1

2024-T3 Clad

0.100

1

I

Replace Replace Replace

1

2024-T24 Clad

0.080

1

I

1

2024-T24 Clad

0.063

1

I

1 1

I I

12

2310522

I

1

11

2310521

1

1

Bulkhead

2310521

Replace

1

Bulkhead

2310521

I

1

2411050 2411050

Replace

1

2311050

1 1 2411050 1

I

1

Stiffener, LH 8 RH

Frame

2411521

FIG. NO.

2024-T42 Clad

1

2310538

REPAIR

CODE

1

2310533

Support Instl., LH

IFINISH GAGE

Assy, Frame 5 Assy, Frame 5 Bulkhead Frame Support SupportAngle Support Instl., LH 8 RH Support Angle

Supportinstl.,LH&RH Support

Angle 2310523 1 Washer(2 ea.) 2310537 ´•´•Supportlnstl., NoseGear 2310537 SupportAngle(Sea.) 2310532 SupportAngle(2 ea.) 2310522

1

1

1

2310532

Channel

1

2024-T24 Clad

0.063

2310537

Web

1

2024-T24 Clad

0.080

Replace Replace Replace Replace

Assembly Repair Index Figure 2 (Sheet 3 of 7)

Nose

EFFECTIVITY: SRMII

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

53-10-00

Page 11 May 15/92

Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

I DESCRIPTION

EFF.

´•´•Fitting, NoseWheelActuator ChannelSupport

1

2410514 2410509

Channellnstl.,LH&RH

1

2411243

2410509 2410510

1

Channel

1

Channellnstl.,LH&RH

I MATERIAL

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

0.063

I 1

1 I

51-71-00

2024-T42 Clad

I

2024-T42 Clad

0.032

1

I

Replace

Replace

1

2410510

Channel

1

2024-T42 Clad

0.071

1

I

2410510

Angle

1

2024-T42 Clad

0.071

1

I

Replace Replace

I

Replace Replace Replace Replace

2410513

HorizontalBeamlnstl.

1

2410513 I´•´•."I"Beam

I

1

I

1

S-642

2410513

Plate

1

241 0511

´•´•´•Clip SupportPan Doubler Assy.,

i

2024-T42 Clad 2024-T42

0.063

1

2024-T42 Clad

0.063

2024-T42 Clad 2024-T3 Clad 2024-T3 Clad

0.050

1

I

0.050

i

i

0.100

1

I

Replace Replace Replace

2024-T3 Clad

0.040

1

I

Replace

2410514 2411051

LH 8 RH

Doubler

1

2411051

Filler

1

Doubler

1

2411054 2411054 2411055 2411055

F4-1 F4-1

1

1

2411051 2411053

0.071

´•´•ChannelAssy.

1

Channel

1

Bulkhead Beam Instl., LH 8 RH ´•´•´•Beam

1 1

S-630

1

2024-T42 Clad

0.063

1

I

2411056

SupportAngle(2 ea.) SupportAngle(2 ea.)

1

2024-T3 Clad

0.040

1

I

2411057

Filler

1

2024-T3 Clad

0.050

Filler

1

2024-T3 Clad

0.050

2411059 1

Filler

1

2024-T3 Clad

0.050

I I I

2411059 1

Doubler

1

2024-T3 Clad

0.040

1 1 1 1

2411055

2411057

Doubler

1

2024-T3 Clad

2411061

2411059 1

´•´•Washer

1

S-610

2411582

´•´•SupportTee

1

S-566

2411583 2411583

Horizontal Beam Instl., LH 8

RHJ

Channel, Upper (2 ea.) Channel, Lower (2 ea.)

2411583 2411583

Splice

Plate

I

I

0.125

I 1

F4-1

1 I I

F4-1 F4-1

1 1

4130 Steel

0.080

F8-1

1

4130 Steel

0.080

F8-1

1

4130 Steel

0.080

F8-1

Replace Replace Replace

1

2411667

Bulkhead Beam Instl., LH 8 RH1 ´•´•´•8eam

1

S-630

I

I

I

2411667

´•´•´•Clip

1

S-571

I

I

I

S-630

I

I

F4-1 F4-1

2411667

2411668

Bulkhead Beam Instl., LH 8 RH ´•´•´•Beam

1

2411669

Bulkhead Beam Instl., LH 8 RH ´•´•´•Beam

1 1

S-630

I

I

2614023 I´•´•Bracket

1

S-642

1

I

2614023

1

2024-T3 Clad

Spacer

Replace Replace

1

2411668 2411669

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

0.040

I

Replace

I

Replace Replace Replace

Nose

Assembly Repair Index Figure 2 (Sheet 4 of 7)

EFFECTIVITY:

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005;

53-10-00

29-004; 31-002 AND SUBSEQUENT; 35-003 AND SUBSEAND SUBSEQUENT 36-001 QUENT;

Page 32 May 15/92

29-001 THRU

SRM´•I

Learjet STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

2311250

1 1

2311250

2311250 2311250 2311250

1

2311250 2311250 2311250

2311250 2311250

1 1

IFINISH GAGE

0.050

1

I

Replace

1

2024-T42 Clad

0.040

1

2024-T3 Clad

0.040

1 1

I I

1

2024-T42 Clad

0.080

1

I

1

2024-T42 Clad

0.040

1

S-549

1

2024-T42 Clad

1

S-306

1

2024-T42 Clad

1

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

(2 ea.) Angle(Gea.) Angle(2 ea.) Bulkhead Segment SupportAngle(2ea.) Seal Angle ´•´•Seal(Fwd) ReinforcementAngle TopPlate(Fwd) Top Plate (Aft) Pan, LH 6 RH (2 ea.)

1

I

1

I

I

I

0.040

1

I

2024-T3 Clad

0.032

1

I

1

2024-T3 Clad

0.032

1 1 1 1

I I I I

1 1

I I

Replace Replace

1 1 1

I I I

I

I

Replace Replace Replace Replace Replace

0.032

I

1

2024-T42 Clad

0.040

1

2024-T3 Clad

0.050

2311250

EndPlate

1

Aft Side Plate, LH 6 RH

1

2024-T42 Clad 2024-T42 Clad

0.050

2311250

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.050

1

2024-T42 Clad

0.063

1

2024-T3 Clad

0.040 0.050

2311250

1

Support (2 ea.) 2311250 Clip 2311250 ´•´•BracketAssy. 2311250 Bracket(~ea.) 2311250 Gusset(4ea.) 2311250 Support 2311250 1 Angle (2 ea.) 2311250 1 Angle(5 ea.)

0.050

1

2024-T42 Clad

1

S-512

1

S-571

I

I

Filler

1

2024-T3 Clad

0.040

2311250

1

2024-T42 Clad

0.050

2311250

SupportChannel(eea.) Pan(2ea.)

1

2024-T3 Clad

0.040

2311250

Cover

1

2024-T42 Clad

0.032

2311250

Clip

1

2024-T42 Clad

0.050

2311250 1

Doubler

1

2024-T42 Clad

0.062

2311250

Hinge Angle

Half

I

1

MS20001V4

i

2024-T42 Clad

0.040

1 1 1 1

I I I I

Replace Replace Replace Replace

1 1

I I

I

I i

Replace Replace Replace Replace Replace Replace Replace Replace

2311250

Channel LH 6 RH

1

2024-T42 Clad

0.040

1 1

2311250

1

2024-T42 Clad

0.032

1

I

2311250

AftTopPlate,RH SidePlate(2ea.)

1

2024-T42 Clad

0.032

2311250

SidePlate,LH

1

2024-T42 Clad

0.032

1 1

I

2311250 1

Doubler

1

2024-T3 Clad

0.050

1

I

2311250

Angle

1

2024-T3 Clad

0.040

1

I

2311250 1

Shim

1

2024-T3 Clad

0.040

1

2317031

Angle Clip

1

2024-T42 Clad

0.050

F4-1

1

2024-T42 Clad

0.050

F4-1

2317031

1

Replace

1

2311250 1

2311250

I

I

Reinforcement Plate

2311250 1

REPAIR FIG. NO.

CODE

2024-T42 Clad

1

Nose Wheel Box Instl. Channel

2311250

I MATERIAL

1

Gusset

2311250 1

I EFF.

´•´•GussetAssy.

2618138 2618138

6

I DESCRIPTION

I

Replace Replace Replace Replace Replace

Assembly Repair Index Figure 2 (Sheet 5 of 7)

Nose

EFFECTIVITY:

SRM-4

24-218, 24-230 THRU 24-357; 25-001 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

53-10-00

Page

13

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

I

DWG. NO.

´•´•NoseGearSafetyCam Instl. Angle(2 ea.) Clip(2 ea.)

2317085

2317085 2317085

REPAIR FIG. NO.

CODE

1

I

I

1

S-512

1

2024-T42 Clad

0.050

F4-1 F4-1

1

2024-T3 Clad

0.125

1

1

2024-T42 Clad

0.063

1

I

2411471

Bracket

1

2024-T42 Clad

0.040

1

I

Cam

´•´•MountingBracket

Instl.

Replace Replace Replace Replace Replace

1

2488676

Pan

1

2024-T3 Clad

0.040

1

I

2488676

Zee

1

2024-T3 Clad

0.040

1

I

1

2024-T42 Clad

0.050

1

Replace Replace Replace

19

2024-T42 Clad

0.050

20

2024-T42 Clad

0.050

1 1

I I

Replace Replace

11

2024-T42 Clad

0.032

1

1

51-70-02

12

2024-T42 Clad

0.032

1

1

51-70-02

2024-T42 Clad

0.040

1

I

Replace

1

2024-T3 Clad

0.050

1

I

Replace

1

S-522

I

I

1

2024-T3 Clad

0.050

1

I

2311450

SplicePlate Lip,Lower(2ea.)

1

2024-T42 Clad

0.040

2311450

HatSection

1

2024-T42 Clad

0.050

1 1

I I

Replace Replace Replace Replace

1

I I

Replace Replace

2310612

1

Doubler(2 ea.)

19

2388366 I´•Doublerlnstl.

Doubler

2388366 2688149 1

Doubler

2610612

1

Bracket

2610612

1

Bracket

17

Assy. Assy.

18

Skin, LH 8 RH 2411001 Skin, LH 8 RH 2310720 I´•Bradtetlnstl., RH 2311500

2311450

1

Bracket

2310720

1

Nose

Equip.:

1 Access Door Instl.

Splice,Plate(eea.)

2311450

2311450 I´•´•Stiffener 2311450

´•´•DoorAssy. (Refer to Chapter 52)

2311450

1

1

1 1

2311000

Channel

4

2024-T42 Clad

0.050

2511500

Channel

5

2024-T42 Clad

0.050

No. 19 LH 6 RH

12

S-554

1

I

1

51-70-04

No. 19 LH 8 RH

11

S-554

1

I

1

51-70-04

No. 18 LH 8 RH

12

S-554

1

I

1

51-70-04

17 LH 8 RH

12

S-554

1

I

1

51-70-04

17 LH

RH

11

S-554

1

I

1

51-70-04

16 LH

RH

12

S-554

1

I

1

51-70-04

16 LH 8 RH

11

S-554

1

I

1

51-70-04

14 LH 8 RH

12

S-554

1

I

1

51-70-04

14 LH 6 RH

11

S-554

1

I

1

51-70-04

13 LH 8 RH

12

S-554

1

I

1

51-70-04

13 LH 8 RH

11

S-522

1

I

1

51-70-04

12 LH 8 RH

12

S-554

1

I

1

51-70-04

12 LH

RH

11

S-554

1

I

1

51-70-04

18 LH 8 RH

12

S-554

1

I

1

51-70-04

No. 18 LH 8 RH

11

S-554

1

I

1

51-70-04

2511500 2311000

1

2511500

Stringer, Stringer, Stringer,

2511500

Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No. Stringer, No.

2311000

Stringer,

2511500 2311000 2511500 231 1 000

9

IFINISH GAGE

Pan

2488676

8

I MATERIAL

2411471

2317093

7

I EFF.

DESCRIPTION

2511500 2311000 2511500 2311000 2511500 2311000

1 1

Assembly Repair Index Figure 2 (Sheet 6 of 7)

Nose

EFFECTIVITY:

s~M-a

24-218, 24-230 THRU 24-357; 25-001 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

53-10-00

Page

14

Jan 15/93

~j Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

10

2511500 2511500

2311000 11

1

2511500 2311000

2311000 2611130 2311000

CODES 1

EFF.

DESCRIPTION

Stringer, Stringer, Stringer, Stringer, Stringer, Stringer, Stringer, Stringer,

MATERIAL

GAGE

FINISH CODE

REPAIR FIG. NO.

No. 11LH

12

S-566

51-70-04

No. 11RH

12

S-544

51-70-04

No. 11 LH 8 RH

11

S-566

51-70-04

No. 10 LH 8 RH

12

S-554

51-70-04

No. 10 LH 8 RH

11

S-554

51-70-04

No. 15 LH 8 RH

15

S-566

51-70-04

No. 15 LH 8 RH

16

S-554

51-70-04

No. 15 LH 8 RH

11

S-554

51-70-04

EFFECTIVITIES 24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004;

SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-218, 24-230 THRU 24-248; 25-002 THRU 25-087 24-249 THRU 24-357; 25-088 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 31-002 AND

2 3

5

25-002 THRU 25-066, EXCEPT 25-061 24-218, 24-230 THRU 24-357; 25-061, 25-067 THRU

6

25-002 THRU 25-087

7

24-252 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU

4

25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

AND

SUBSEQUENT;

35-001 AND

29-004; 31-002

SUBSEQUENT; 36-001 AND SUBSEQUENT

8

25-002 THRU 25-066, EXCEPT 25-061

9

24-350 THRU 24-357; 25-227 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

10

31-002

29-004;

31-002

24-357; 25-227 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-218, 24-230 THRU 24-246; 25-061, 25-067 THRU 25-077

31-002

24-146 THRU AND

11

13

24-247 THRU 24-357; 25-061, 25-078 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT 24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004;

14

35-625 AND

12

35-001 THRU 35-624; 36-001 THRU 36-055 15

16 17 18 19 20

SUBSEQUENT; 36-056 AND SUBSEQUENT 24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 35-001 THRU 35-504; 36-001 THRU 36-052 31-002 AND SUBSEQUENT; 35-505 AND SUBSEQUENT; 36-053 AND SUBSEQUENT 24-218, 24-230 THRU 24357; 25-002 THRU 25-289; 28-001 THRU 28-005; 29-001 THRU 29-004; 35-001 THRU 35-278; 36-001 THRU 36-044 25-290 THRU 25-373; 35-279 AND SUBSEQUENT; 36-045 AND SUBSEQUENT 24-273 THRU 24-350; 25-061, 25-135 THRU 25-226; 35-001 THRU 35-124; 36-001 THRU 36-032 24-351 THRU 24-357; 25-227 THRU 25-373; 35-125 AND SUBSEQUENT; 36-033 AND SUBSEQUENT

Nose

Assembly Repair Index Figure 2 (Sheet 7 of 7)

EFFECTIVITY: SRM-4

24-218, 24-230 THRU 24-357; 25-002 THRU 25-373; 28-001 THRU 28-005; 29-001 THRU 29-004; 31-002 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT

53-10-00

Page 15 May 15/92

Learjet STRUCTURAL REPAIR MANUAL NOSE AS SEMBLY

i.

ALLOWABLE DAMAGE

ALLOWABLE DAMAGELIMITS

All dimensions

NOTE: A.

in inches unless otherwise

are

specified.

Fasteners

(1) Loose

or

failed rivets

are

not allowed. A loose

or

failed rivet

can cause

increased stress concentrainspection must be

failure. A careful

tions on the remaining rivets and lead to progressive joint performed to ensure that joint failure has not spread from the area of the loose or failed rivet. (Refer to Chapter 51 for definition of rivet failure.)

(2) Loose

or

trations

failed

on

performed B.

screws are

surrounding

not allowed. A loose

failed

screw can cause

increased stress

concen-

must be

failure. A careful

inspection progressive joint joint failure has not spread from the area of the loose or failed

screws

to ensure that the

or

and lead to

screw.

Cracks

(1) Cracks in any fitting or forging are not allowed. Cracked fittings or forgings must be replaced. (2) Cracks in components other than fittings and forgings are considered allowable if properly

paired, and refinished C. D.

re-

Chapter 51.

Deformation

(1) Deformation of the nose assembly structure is not allowed. Corrosion(See Figure 101.) (1) Corrosion damage is permissible if the affected area is properly repaired, refinished in accordance with Chapter 51, and these repairs do not reduce the original material thickness more than specified. (Refer to Chapter 51 for protective treatment procedures.) Structural (2) components must be repaired or replaced if corrosion repair reduces the original material thickness

E.

in accordance with

more

than

specified.

Dents

permissible, if smooth and without abrupt changes in contour, do not exceed 0.100 inch mm) in depth, do not exceed 10% of total surface area in one (1) square foot, and are not

(1) Dents (2.54

are

closer than 0.50 inch (12.7 mm) to any rivet or structural area. (2) Dents are not allowed if sharp, a fracture of the skin has occurred, greater than 0.100 inch (2.54 mm) in depth, exceeds 10% of total surface area in one (1) square foot, and are closer than 0.50 inch (12.7 mm) to F.

a

rivet

or

structural

area.

Such dents shall be

repaired

or

the

component

re-

placed. Scratches(SeeFigure 101.) (1) Scratches are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to

Chapter 51

for

protective treatment procedures.) replaced or repaired

(2) Structural components must be thickness by more than specified. G.

if scratches reduce the

original

material

Nicks(See Figure 101.) (1) Nicks are permissible if the affected area is sanded smooth, refinished in accordance with Chapter 51, and the repairs do not reduce the original material thickness more than specified. (Refer to

protective treatment procedures.) components must be replaced or repaired if nicks reduce the original material thickthan ness more specified. Fittings and Forgings (1) Fittings or forgings must be replaced if cracked or if fitting hole (non-bushed) tolerance exceeds the allowable limits. (Refer to Chapter 51.) (2) Fittings or forgings with bushing shall be repaired. Chapter 51

for

(2) Structural

Fl.

EFFECTIVITY: SRM-4

ALL

53-10-00

Page 101 May 15/92

Learjet

STRUCTURAL REPAIR MANUAL

Minimum Thickness

Nominal Thickness

(Inch)

(Inch)

0.016

0.0135

0.020

0.0175

0.025

0.0225

0.032

0.0295

0.040

0.037

0.050

0.046

0.063

0.059

0.071

0.067

0.080

0.076

0.100

0.095

0.125

0.120

0.190

0.180

0.250

0.237

Allowable Material Thickness

Figure EFFECTIVITY: SRM-4

ALL

101

53-20-00

Page 102 May 15/92

Learjet STRUCTURAL REPAIR MANUAL NOSE ASSEMBLY i.

REPAIR

APPROVED REPAIRS A.

RefertoChapterlil fortypicalrepairs.

Em7ECTTVITY: SRM-4

ALL

53-10-00

Page 201 May 15/92

Learjet I STRUCTURAL REPAIR MANUAL FUSELAGE ASSEMBLY 1.

STRUCTURAL IDENTIFICATION

DESCRIPTION A.

The

fuselage assembly

consists of the structural assemblies from frame 5 to frame 22. A forward and

aft pressure bulkhead are installed in the aircraft. The forward pressure bulkhead is located at frame 5, the aft pressure bulkhead location will vary depending upon aircraft model and fuel system

an

configuration.

EFFECTIVITY:

Refer to

31-001 AND

Chapter 51

for forward and aft pressure bulkhead locations.

SUBSEQUENT; 35-001 AND SUBSEQUENT;

36-001 AND SUBSEQUENT SRM-4

53-20-00

Page

1

Jan 15/93

E~Learjef STRUCTURAL REPAIR MANUAL STRUCTURAL IDENTIFICATION

FUSELAGE ASSEMBLY

Frame 17A

Frame 20

Frame 22

Frame 5

Frame 7

Frame 9

Frame 11

Frame 13

Frame 13D

Frame 13B

Frame 14

Frame 16

FS 378.05

FS 402.42

FS 421.42

FS 160.77

FS 184.78

FS 209.19

FS 234.19

FS 258.01

FS 283.99

FS 308.49

FS 332.66

FS 355.49

(Ref)

(Ref)

(ReO

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

Frame 18

(Ref)

(Ref) Frame 13A I

Frame 4

1

Frame 6

Frame 8

Frame 20

Frame 12

1

Frame 13E

FS 151.12

1

FS 172.19

FS 196.99

FS 221.59

FS 246.09

1

FS 271.99

FS 296.49

FS 321.24

FS 346.63

1

FS 368.68

(Ref)

I

(Ref)

(Ref)

(Ref)

(Ref)

I

(Ref)

(ReO

cRef,

cRef,

I

(Ref)

I

I

Frame 13C

Frame 15

FS381.79

Framel7

(Ref)

I

FramelB

Frame 21

FS 392.50

(Ref)

9)

1

I

1

(6)

1

I

I

I

(5)

I

I

(I

1911

1

I18

I_;

;;i;

I~

I

1;1 i~

7~P"

I:

i~il ´•s-~-4

P

I--re

f~_-f-;

~lr I!I

I

--1´•i 1!1

;-----Ti

r;I ;=--;L1

I

.:jj

i t

i----~

i_--J-~

O _~-

I---,--

O

O

(VIEW LH SIDE LOOKING INBOARD) (TYPICAL)

2-150D

EFFECTn/TITY:

Fuselage Assembly Repair Index Figure 1(Sheet 1 of 15) SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR 31-001 AND

36-001 AND SRM-4

53-20-00

Page 2 Jan 15/93

FS411.95

I

(Ref)

Learjet STRUCTURAL REPAIR MANUAL FUSELAGE ASSEMBLY

STRUCTURAL IDENTIFICATION

Frame 17A FS 378.05

(Ref)

FrameZO

Frame22

(Ref)

(ReO

Frame 13D

Frame 13

Frame 1~

Frame 9

Fmme 7

Frame 5

FSZ58.01

88 23419

FS u)9.19

FS1~.78

F5160.77

(ReO

(Refi

(Ren

(ReO

(Refl

FS35j.49

FSJ~2.66

FS308.49

(Ref)

(Refi

(ReO

(ReD

Frame 15

Frame 17

Frame 18

Frame 1JB

FS 283.99

FS 402.42

F5421.42

Frame ~4

Frame 16

Fmme6

Frame 4

FS2n.99

FS 246.09

FS 221.59

FS 196.99

FS~72.19

FS 151.12

[Ref)

(ReO

(Ref)

(Refl

~Ref)

FS 368.68

FS 346.63

FS 321.24

(ReO

(ReD

(Ref)

(Ref)

(Refi

(Ref)

1

I

Frame 19

FS 392.50

(Ref)

(Ref)

~(17)1

1

I

1

I

I

C

/I(

I,

III

I

II

I

i

C-

i.

L~

I

jl

I

r

1~

I

1.

I--------

t--

i

I

II

1

-r-

FmmeB

Frame 13C

FS381.79

Frame 21

FramelO

Frame 13A

FS 296.49

FS411.95

Frame 12

Frame 13E

_I

r

r_______~

i-

I,

r

4--

ic~

I ;Lr~i

(i I’

i-

ir,jI

i

L

1

I

I

’i I’

ii

rl

;f~;-; f

iii

II

,t

!II:

I

I’

II

I

’’I

II

II

I~ ,I

i

r

~Tjl-

1,7

1

1(1

I I ,I

;I I

i,.

1~1

1´•,,

/i

I i

,\__,__

’=-7

ii

i’

´•II

II!:

r

i

I,

i --

i r

t

E

1,

r----

I

nl~

I,

I

II i

II

I

bt~-tr

1

r;;;-----r-r--´•

ii

I I

II

I

I,

71"

II);

,______

Iri

--C----4

Lf----

I ~,-----___

c------i.

r-

(VIEW RH SIDE LOOKING INBOARD) (TWICAL)

nao

EFFECT~VITY:

Fuselage Assembly Repair Tndex Figure 1 (Sheel 2 of 15) 31-001 AND 36-001 AND

SRM-4

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 2´•I-INCH

PASSENGER/CREW DOOR

53-20-00

Page 3 Jan 15/93

I

Learjet

STRUCTURAL REPAIR MANUAL ITEM

DWG,

NO.

NO.

I

I DESCRIPTION

2611003

I EFF.

Fuselage Structure Assembly Fuselage Frames Instl. (Refer to 53-21-00) Fuselage Stringers Instl. (Refer to 53-22-00) Fuselage Windshield Instl. (Refer to 53-24-00) Fuselage Instrument Panel

MATERIAL

IFINISH

REPAIR

CODE

FIG. NO.

I GAGE

1

Structure Instl.

(Refer to 53-25-00) Fuselage Circuit Breaker

Panel

Structure Instl.

(Refer to 53-26-00) Fuselage Skins Instl. (Refer to 53-28-00) Fuselage Keelbeam Assemblies (Refer to 53-50-00) 1

2311150

I´•Bulkheadlnsti. (Frame 15)

1 1

2311150

´•´•Stiffener, Center Stiffener, LH 8 RH (5 ea.)

2311150

´•´•Angle,Support

1

2311150

2311150

1

S-554 S-554

1 1

S-565 2024-T42 Clad 2024-T42 Clad 2024-T3 Clad

I I

I I

0.050

1

I

0.063

1 1

I I

FrameWeb Stiffener

1

1 1

2024-T3 Clad 4130 Steel

0.120

2311154

Strap(4 ea.) Strap(2 ea.) Strap,Outer

2311155

Strap,Outer

1

4130 Steel

0.063

2311153

I´•´•Fitting, Longeron ´•´•SafetyBand(2ea.)

1

2311150

2311150 2311153

2311150

1 1

2311150

Shim

2311150

Plate

2311150

Stiffener, LH

2311150

SafetyBand

1

1

(2ea.) 8 RH

1

2024-T3 Clad

0.032

1

2024-T42 Clad 2024-T3 Clad

0.080

1

0.063

1

I

2024-T3 Clad

0.040

1

I

Replace

3

2024-T3 Clad

0.040

1

2024-T42 Clad 2024-T42 Clad 2024-T3 Clad 2024-T42 Clad

0.080

1

I

1

I

2311150

´•´•WebAssy.

2

2311150 2311151 2

2618326

3

2511321

2

1

0.025

3

Web

2311150

Replace

I

1

1

I´•´•WebAssy.

F8-1

I

Replace Replace Replace Replace Replace Replace

´•´•Shim, Laminated (Max. 0.032)

2311150

I

F8-1

0. 025

1

Web

0.080

2024-T42 2024-T3 Clad

1

2311150 2311150

0.063

Replace Replace Replace Replace Replace Replace Replace Replace

Stiffener(2ea.) Fitting

1

Doubler, RH Side Only Skin Doubler, Escape Hatch

4 1

1.250 0.025 0.080

Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 3 of 15) EFFECTIVITY:

31-001 AND

SUBSEQUENT; 35-001 AND SUBSEQUENT;

53-20-00

Page 4

SRM~

36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR

Jan 15/93

Learjetl STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

4

2511330

5

2611330

6

2611330

7

2611330

8

I

I DESCRIPTION

2511000

1

2511295

1

2311479

1 1 1

Window Doubler, RH Aft Window Doubler, RH Fwd Window Doubler, LH Fwd Window Doubler, LH Aft

Splice

1

Band

(4 ea.) Inner Skin Instl., Door Frame

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

1

2024-T42 Clad

0.063

1

I

1

2024-T42 Clad

0.063

1

2024-T42 Clad

0.063

1 1

I I

5

2024-T42 Clad

0.063

2024-T42 Clad

0.063

1 1

I I

1 1

I I

1 1

I I

Replace Replace Replace Replace Replace

1 1

2024-T42 Clad

0.040

1

0.050

1

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

1

2024-T42 Clad

0.050

2311479 1

Flex Conduit

1

1 1 1

Flex Conduit

(2 ea.) Rigid Conduit Clip(2 ea.)

1 1

5052-0 Tube

0.035

1

I

1

2024-T42 Clad

0.032

I

Channel Intercoastal

1

0.040

Skin

1

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

1 1

0.040

Skin

1

2024-T3 Clad

0.040

1 1 1

I I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

6

2024-T42 Clad

0.020

1

I

Replace

7

2024-T42 Clad

0.020

2024-T3 Clad

0.050

1

2024-T42 Clad

0.080

1 1 1

I I I

Replace

1

2024-T3 Clad 2024-T42 Clad

0.063

1

I

i

0.032

1

I I

I

Replace Replace Replace Replace Replace

2511314

2311479 2311479 2311479 2311479 2511295

1 1

2511295 1 2511295 1 2511295 1 2511295 1 2611092

1

2611092

1

1

1

2511002 1 2311560 2311560

Track

Support)

Filler

I´•Longeron Instl., Top Centerline Fwd 1 Safety Band (2 ea.)

2311560

1

Web, LH Web, LH Web, LH

2311560

1

Angle(2 ea.)

2311560 2311560

0.040

Replace

Replace

1

i

RH Center RH Fwd 8 RH Aft

Torsion Bar Instl., Lower Door

2311272 2311272

0.040

Frame, LH 8 RH

(Curtain Strap

2511000

0.040

Frame, LH 8 RH

(Curtain Track Support)

10

I MATERIAL

Stiffener(8) Clip(2 ea.) Stiffener(7 ea.) Clip(4 ea.) Clip(3 ea.)

2511314

9

I EFF.I

1

2024-T42 Clad

0.032

1

2024-T42 Clad

0.032

1

2024-T42 Clad

0.040

1 1

1

´•´•FittingAssy.

1

2311272

Plate

1

4130 Steel

0.100

1

I

2311272

Fitting

1

4130 Steel

3/8 Dia

I

I

Replace Replace

2311272

(´•´•Bearing

1

i

6061-T6

0.090

1

I

Replace

1

6061-T6

I

I Replace

Bracket

1

2024-T42 Clad

1

I

Spacer EndFitting

1

Phenolic

1

4130 Steel

´•´•´•Plate

2311272 2311272 1 2311272 1 2311272 2311272 2311272

1

I

Sleeve

Torsion Bar

Assy.

0.040

I 1.5 Dia

I

Replace Replace Replace

I

Replace Replace Replace

F8-1

1

2311272

Torsion Bar

1

2311272

Link

1

A151 17-4 P.H. SS A151 17-4 P.H. SS

2311272

Link

1

A151 301 SS

5/16 Dia 0.125 0.125

F-21

1 F-21

Fuselage Assembly Repair Index Figure 1 (Sheet 4 of 15) EFFECTIVITY:

31-001 AND

36-001 AND SRM-4

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page 5 Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

11

I

2311623 1

Shim

I´•´•Support

2311623

12

2311623 I´•´•´•Anale Plate 2311623 Stiffener 2511674 2511674 Angle 2511674

2511664

I 0.100

1

2024-T3 Clad

I

0.050

I I

S-591

1

2024-T3 Clad

0.190

2024-T42 Clad 2024-T42 Clad

0.050

I I

I I

1 I I 1 1

I I I I I

I

I

Replace

1 1 I I

I I I

Replace Replace Replace Replace Replace Replace Replace

2024-T3 Clad

10

1 1

I I

0.250

I I 6061-0

0.190

6061-0

0.100

2315122 2315122 1 2315122 2315122

2315122 2315122

2615123 3315123 2615289 2615123

3315123 2615289 2615123 3315123 2615289

2615123 2615123 2315122

2615181 2411002

1

I 2024-T42 Clad

0.050

1

2024-T42 Clad S-554 S-520

0.040

1 1

I´•´•Angle Sector Support Instl. 1 Sector Support Instl. 1 Bearing Plate Bracket Assy., Upper 1 Bracket Assy., Upper 1 Bracket Assy., Upper 1 1 SectorSupport 1 SectorSupport 1 SectorSupport 1 Spacer Spacer Spacer Bracket Assy., Upper (2 ea.) 1 Sector Support 1 1 Bearing Plate Clamp Support (2 ea.) Clip(2 ea.) 1

I

1 1

Bracket

Replace

I I

1

2315122

Replace

1 1

0.050

1

2315122

I I I I

Replace Replace Replace Replace

I

2024-T42 Clad

2311684 I´•´•´•Channel Bellcrank Support Instl., 2315122 1

Angle ´•´•Angle ´•´•Angle ´•´•SupportAssy.

I I I I I

1

0.050

2311684 I´•´•´•Plate

2315122

I

I 1 I I 1

8 9

RH

I Replace

1

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

Bracket

I

1 1 1 I

1

10

Rudder LH

REPAIR FIG. NO.

CODE

1

I´•´•Fitting 1 Spacer JackPadSupport Instl. Bracket Assy.

2311677

IFINISH GAGE

1

I´•´•Fitting

2315122 1

15

S-578

2511666

2311677

14

1

2511666

2511666 13

2024-T3 Clad

1

Stiffener(2ea.) Clip ´•´•Fitting

2511674

S-551

1

1

I

Fitting Instl. (2 ea.)

1

1

Bracket(2ea.) ´•´•AngleAssy.(2ea.)

2311623

I MATERIAL

1

´•´•Tee

2311623

I EFF.

Support Instl.

2311623

2311623

I DESCRIPTION

I

1 I I

1

2024-T42 Clad

1

S-738

I

I

0.050

1 I

I I

0.050

1 I

I I

I I 1 1 1

I I I I

1 1

I I

0.050

1 I

I I

1 1

I I

1 1

I I

1

10 11

2024-T42 Clad

1 11

I

I

12

1 1

I I

13

11

2024-T42 Clad

0.050

12

0.050

13

2024-T42 Clad 2024-T42 Clad

11

2024-T42 Clad

0.050

12

2024-T42 Clad

0.050

2024-T42 Clad

13

12

0.050

1

I

12

2024-T42 Clad

0.050

12

2024-T42 Clad

0.100

11

2024-T42 Clad 2024-T42 Clad

0.050

1

0.050

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 5 of 15) EFFECTIVITY:

snM-4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

6

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

2411002 2411002

1 1

2411002

1

I DESCRIPTION

Splice Angle (6 ea.) Splice Angle (6 ea.) Splice Angle

I

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

MATERIAL

15

S-544 S-748

1 1

I I

16

S-544

1

I

I

16

S-544

1

I I I

j

14

2411002 I´•Doubler

I I

2411321 1

Channel

1

2024-T42 Clad

0.040

2411321

Gusset(2 ea.) Gusset(2ea.)

1

2024-T42 Clad 2024-T42 Clad

0.040 0.040

I 1 1 1

2024-13 Clad

0.050

1

2024-T3 Clad

0.050

I 1

10

2024-T42 Clad

0.040

1

10

2024-T42 Clad

0.040

10

2024-T3 Clad

0.040

10

2024-T3 Clad

0.050

10

2024-T42 Clad 2024-T42 Clad 4130 Steel

0.040 0.125

1 1 1 1 1

18

2024-T42 Clad

0.063

1

I

19

2024-T42 Clad

0.063

1 I

I I

0.063

1

I

I 1 1 I

I I I I

2511333

1

5

2514303

Doubler Instl., LH 8 RH Doubler

26183811

Doubler Instl.

17

´•´•DoublerAssy.

17

2514303

2618382

2513315 2513315 2513315

1

2513193

1

2513193

1

2513193 2511340

2511340 3111097 i 2388162

1

2388162

1 1

2388162

2388162

2388162 2388162 3111098

1

3111098 3111098 2615101 2615101 2315123

2315123 2315123 2315123 2315123

1

10 10

Replace Replace

0.040

j i i I I

Replace Replace Replace Replace Replace Replace Replace

18 19 20

Clip(4 ea.) Clip(2 ea.) Support Assy., LH 8 RH Support SupportAssy.,LH&RH Support Support, LH 8 RH Support Assy., LH 8 RH (2 ea.) Support Angle(2ea.) Pedestal 8 Controls Support

20

2024-T42 Clad

0.063

20

2024-T42 Clad

0.040

1 1

I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

18

1

19

1

I 2024-T42 Clad 2024-T42 Clad

19 19 20

I 2024-T42 Clad

18

1

0.063 0.063

I

1

RH

BearingSupport,LH&RH Bearing Support, LH RH

Angle(2ea.) SupportFrame Bearing Support,

I

Replace

10

Bracket Shoulder Harness Instl. Shoulder Harness Instl. Shoulder Harness instl.

Structure Instl. Intercostal, LH

1

17

Support,LowerFwd Support,UpperFwd Doubler(3ea.) Spacer Support, Lower Aft Support, Upper Aft

2513315

2388162

1

Seat Belt Instl.

2513315

Replace Replace Replace Replace Replace Replace Replace

1

Doubler

2618382

16

I EFF.

1

2024-T42 Clad

0.063

1

I

Replace

Fwd

21

2024-T42 Clad

0.050

Fwd

22

0.050

I I

i

2024-T42 Clad 2024-T42 Clad

1 1

0.040

1

2024-T42 Clad

0.063

j

1

2024-T42 Clad

0.050

1 1 1

Replace Replace Replace

Replace Replace

LH 8 RH Aft

Fuselage Assembly Repair Index Figure 1 (Sheet 6 of 15) SUBSEQUENT; 35-001 AND SUBSEQUENT;

EFFECTIVITY:

31-001 AND

SRM-4

36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH PASSENCERJCREW DOOR

53-20-00

Page

7

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM NO.

DWG. NO.

I

2511370

1

2511370

2511370 1 2411371

1

2511370 2511370

2411371

I

I

1

2411280 1

Longeron Instl., LH 8 RH AttachAngle(2ea.)

2411280

1

2411280 2411280

2411281 2411281

1

2411281 2411281

1 1

2411281

1

2411281

1

1 2411281 1 2411281 2411281

1

241 1281

2024-T42 Clad

0.063

1

I

1

2024-T3 Clad

0.063

1

I

Drag Block Longeron

1

S-517

1

2024-T42 Clad

0.100

I 1

I I

Filler

1

2024-T3 Clad

0.100

1

I

Drag Block, Fwd

1

S-5017

I

I

I

1

S-308

I I

I I

I I

1

S-308

I

I

I

1

S-308

1

S-308

1

S-308 S-308

I I I

I I I

I I I

Aft

Door Frame Instl.

1

´•´•Seal,FwdUppar ´•´•Seal,AftLower Seal, Aft Upper ´•´•Plug(eea.) ´•´•RainSealDiaphragm Switch Support (8 ea.) Guide Plate (8 ea.) Tube Assy. Seal Plate (2 ea.) Garner

Splice, Corner Splice,

I

1 i 1

Mat. No. 4554

0.013

1

I

1

2024-T42 Clad

0.080

1

I

1

4130 Steel

0.080

1

2024-T3 Clad

0.040

1

I

i

2024-T42 Clad

0.040

1

I

1

2024-T42 Clad 2024-T42 Clad

0.040

1 1 1

I I I

1 1

I I

1

Aft Fwd

1

Fwd

1

2024-T42 Clad 2024-T42 Clad

0.032

Corner Seal Retainer, Corner Seal Retainer,

Aft

1

2024-T42 Clad

0.032

1

2024-T3 Clad

0.063

1

2024-T42 Clad

0.040

Doubler

2411281

Seal Retainer, Tube Assy.

Upr Upr

Upper

1

´•´•´•Tube

1

321

2411281

´•´•´•Tube

1

Stainless~

1

1

MS20001PX4

2411283

Hinge Pin Hinge Half 1 Hinge Assy., Upper ´•´•´•HingeHalf ´•´•´•HingePin ´•´•´•HingeHalf

321 Stainless~MS20253-2-140

2411284

´•´•SealRetainer,Fwd

2411281 2411283

2411283 2411283

2411284 2411282 2411282 2411282 2411281

0.032 0.032

I

Replace Replace Replace Replace Replace

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

I

I I

I I

I I

I I

I I I

1

I

I

I

0.050

j I I

I I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

0.050

1

I

Replace

1

2411281

2411281

I

Corner Seal Retainer, Lwr Fwd Corner Seal Retainer, Lwr Aft

2411281 2411281

REPAIR FIG. NO.

CODE

1

´•´•Seal,Bottom 2411280 1 Seal, Fwd Lower 2411280

IFINISH GAGE

Doubler

2411280 2411280

I MATERIAL

1

´•´•Seal,Top

2411280

I EFF.

DESCRIPTION

1 1

I´•´•SealRetainer, Aft 1 Hinge Assy., Lower ´•´•´•HingeHalf(2ea.) ´•´•´•HingePin Plate (3 ea.)

1

I

1 I I

1

I

1

1

MS20253-5

i

~P

1

S-553 S-553

1

0.050

I 1 1

1 1

~P

1 1

0.050

301 Stainless

0.063

F18

Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 7 of 15) EFFECTIVITY:

SRM-4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

8

Jan 15/93

Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO. 2318763

I

1

2318763 2688038

1

2688038 2688038

1

26183971 2618398 1 2511416

RH

Angle(2ea.) Doubler Instl. (2 ea.) Angle(2ea.) Angle(2 ea.)

1

1

2411323 1

2411323

2411323 2411323

2411323 2411323

1

2411323

1

2411323 2411328

2411325 2411328 2611127 1

1

I

Replace

2024-T42 Clad 2024-T42 Clad

0.050 0.050

1 1

I I

Replace Replace

1

2024-T42 Clad

0.020

1

I

1

2024-T3 Clad 2024-T3 Clad

0.090

1

I

0.032

1

I

Replace Replace Replace

23

27

(18 ea.)

1

Spacer

1

2024-T4 Rod

0.250

1

I

Bellcrank Drive

1

2024-T351 Plate

0.375

1

I

I I

I I

1

´•´•Bellcrankldler Pin (2 ea.) Pin

(2 ea.) ´•´•GuidePin(2ea.) FlushLatch HandleAssy. Spring Retainer ´•´•´•Spring Connector Box Instl.

1

0.375

1

I

2024-T4 Plate

0.375

1

2024-T3

0.125

1

2024-T351 Plate

0.500

1 1 1

I I I

28

2024-T4 Al Rod 2024-T4 Al Rod

0.438

29 1

2024-T351 Plate

0.500

1

30

2611125 2611125

Support

2611126

Rib, LH

8 RH

LH

RH

Cover

2611128

´•´•´•Support(3ea.) Filler(Gea.)

2611128

I

MS24585-C414

I

I

I

I

I

I

1 1 1

I I I

0.050

30

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

30

2024-T42 Clad

0.040

1

30

2024-T42 Clad

0.040

1

I

30

2024-T42 Clad

0.071

1

I

0.050

1

I

0.050

I 1

I I

1 1

I I

0.050

0.050

30

2024-T42 Clad

30

I

I

1

I

0.100 0.063

1 1

I I

2024-T3 Clad

0.080

1

I

Replace

2024-T3 Clad

0.050

1

I

Replace

30

ABS Therm Plastic

0.063

Support Support, LH

30

2024-T42 Clad

0.040

2611125

1 1

30

2611125

1

2611125

1

RH Gusset, LH Filler(2 ea.) Bracket, LH 8 RH

30

S-626 2024-T42 Clad 2024-T3 Clad

30

2024-T42 Clad

I´•Doubler(FS196, between Stringers 10 11) Doubler(FS 196, between 26185511

31

Stringers

32

2511216

8 RH

(2 ea.)

Replace Replace Replace Replace Replace Replace

0.040

30

2611125

Replace Replace

Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

Seal

2511183

Replace Replace

30 S-522 2024-T42 Clad

2611128

F3

1

Replace Replace Replace

30 30

Assy.,

F3

0.438

Replace Replace Replace Replace Replace Replace

1 1

End,LH&RH End, LH 6 RH Bracket,LH&RH

Cover

I I

1

2611123

1

I S-580 6061-T6

i

Cover

2611128

FIG. NO.

0.050

2611118 2611124

REPAIR

CODE

2024-T42 Clad

26

Angle Assy. ´•´•´•Angle I´•´•Spacer Linkage 1 I´•´•Linkage

2411323

IFINISH GAGE

2

25

1

2411323

MATERIAL

2

Doubler Instl. Doubler Shim

I EFF.

24

2411325 I´•ExternalRelease Instl. 2411323

18

Doubler Instl., LH

Filler

2688151

17

I DESCRIPTION

30

1

2618314

10

11)

Fuselage Assembly Repair Index Figure 1 (Sheet 8 of 15) EFFECTIVITY:

SRM-4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-JNCH

PASSENGER/CREW DOOR

53-20-00

Page

9

Jan 15/93

STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

´•´•´•Stiffener(3ea.) Filler

1

0.032

I

2024-T42 Clad

0.507

I I

3111118

Support

33

3111118

Filler

3111119

´•´•´•Angle ´•´•´•Angle ´•´•´•Angle Seal (4 ea.)

2511332

1

2511215

2511216

1

2511216 1 2511216

1

2619042 1

2411321 2311258

1 1

1

I

0.071

0.040

33

2024-T42 Clad 2024-T42 Clad

1 1 1

I I I

33

S-5001

0.010

33

S-5001

0.012

33

S-5001

0.015

I I I I

34

Skin Doubler, LH Aft Blower Evaporator Support

I I I I I

0.063

Channel

37

2024-T42 Clad

0.040

Clip(2 ea.)

37

2024-T42 Clad

0.040

1

2024-T3 Clad

0.050

1 1 1 1 1

1

2024-T42 Clad

0.040

1

I

2024-T42 Clad 2024-T42 Clad

0.050

1

I

0.050

I

2024-T3 Clad 2024-T3 Clad

0.050

1 1 1

I

Replace Replace Replace Replace

1

2024-T3 Clad

0.250

1

2024-T351

1.600

1 1

I I

Replace Replace

0.040

1 I

I I

0.063

1

I

Replace Replace Replace

2024-T42 Clad 2024-T42 Clad 2024-T3 Clad

0.050

1 1 1

I I I

0.050

Bracket

Channel(Above Escape Hatch) Inner Skin Instl. (FS 160 to 209, RH LH)

I

Filler

40

40

1

Escape Hatch Instl. Escape Hatch Assy. (Refer to Chapter 52) Strap 1 Tee Support 1 I´•´•ClipAssy. ClipSupport ´•´•´•Clip Doubler, Aft Fuselage Window 1 Stiffener

Plate Instl., LH

RH

0.063

0.160

1 1

1

1 1

1

2024-T3 Clad NAS1464-038-05C 2024-T42 Clad

I

1 1

2511674

Clip(2 ea.) Angle Plate(LHOnly) Plate(RHOnly) Stiffener(3ea.)

1

2024-T3 Clad 2024-T42 Clad

2511674

Filler

1

2024-T3 Clad

0.063

j 1

2511674 1

Stiffener

1

2024-T42 Clad

0.063

1

2511674 2511674 2511674

Replace Replace Replace Replace Replace Replace

1

2311258 1

2511674 1 2511674

I

2024-T42 Clad 2024-T42 Clad

2311258

2411322

1

36

39

2411322

0.063

1

Skin,LH&RH Strap

2411322

2024-T3 Clad

35

2311258

2411322

0.010

1 1 1 1

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Bracket,LH&RH RH Bracket, LH

38

2411322

0.040

33

Skin,LH&RH

2411322

I 0.050

2311258

2411320

1 2024-T42 Clad 2024-T42 Clad

33

Structure Instl. 2511216

20

S-522

33

33

3111119

I I

33

33

8 RH

I 1

0.507

Rib

3111119

FIG. NO.

2024-T42 Clad

3111118

3111119

REPAIR

CODE

33

3111118

Rib

IFINISH GAGE

I

33

Cover

Assy., LH Rib(2ea.)

3111118

I MATERIAL

33

´•´•CoverAssy.,LH&RH

3111119

I EFF.

Pressurized Connector Box Instl.

3111116 1 3111117 3111119 3111119

19

I DESCRIPTION

1 1 1

0.050 0.080 0.050

j

Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 9 of 15) EFFECTIVITY:

SRM-4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

10

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG, NO.

I

I

I

DESCRIPTION

I

I MATERIAL

EFF.

GAGE

2511674 1

Plate

1

2024-T3 Clad

0.050

2511674

Stiffener

1

2024-T42 Clad

0.063

2511644

I´•´•Fitting

2411324

1

1

I

I

IFINISH CODE

REPAIR

FIG. NO.

1 1

I I

I

I

Replace Replace Replace

1 1 I

I I I

Replace Replace Replace

I 1 1 1

I I I I

Replace Replace Replace Replace

Inner Doubler

Assy., (Escape Hatch)

1

2411324 I´•´•Doubler

41

6061-T6

0.040

2411324 I´•´•Doubler

42

0.040

41 42

2024-T42 Clad

41

2411323

Plate

41

2024-T42 Clad 2024-T42 Clad 2024-T3 Clad

0.040

2411326

Spacer(4 ea.) Spacer(4 ea.) NutRetainer(4ea.) NutRetainer(4ea.)

6061-T6 2024-T42 Clad

2411323

Plate

42

2024-T3 Clad

0.090

1 1

2024-T42 Clad

0.040

1 1

I I

Replace Replace

1

2024-T42 Clad

0.050

1

I

1

2024-T3 Clad

0.125

1

I

I

I

1 1

I

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

2411324 2411324

1 1

2411326

42

2411321 1 Frame(FS 350, RH Side 2489168 I´•Doublerlnstl. 2489168 1 2489168

1

Doubler Radius Filler

2489168

Doubler

2489168 1

Wedae

2489168

1

2489168

2489168 1 2489168

Fwd

1

(2ea.) I

Filler

2489168 2489168

(4 ea.)

´•´•DoublerAssy.,

2489168

Only)

1

Filler(2ea.) Angle Assy. Angle Wedae Doubler Instl.

I

0.090

I 2024-T3 Clad

0.040

1

2024-T3 Clad

0.190

1

2024-T3 Clad

0.050

1

2024-T3 Clad

0.025

I

1

(ADF Antenna)

0.040

1

1

I

A/R A/R

1

I

1

I I

I

I

2024-T42 Clad 2024-T3 Clad

0.050

1

I

0.190

1

I

2

2489168 1

Doubler

1

2024-T42 Clad

0.050

2489168

RadiusFiller(4ea.) Doubler Assy., Aft (2 ea.)

1

2024-T3 Clad

0.125

1 1

I I

0.160

I 1

I I

1

2024-T3 Clad 2024-T3 Clad

1

2024-T3 Clad

0.160

1 1

I I

1

2024-T3 Clad

0.025

1

I

2489168

2489168 1 2489168

1

I

Filler

Wedge Filler(2ea.) ´•´•AngleAssy. Angle

2489168 2489168 2489168 2489168 2489168 1 3118916

Wedae

1 1

Wedae

I

I´•Doublerlnstl. (ADFAntenna)

3118919 I´•´•Doubler

1

I

I

0.050

I

I

I

I

Replace Replace Replace

1

I

Replace Replace Replace

2024-T42 Clad 2024-T3 Clad

0.050

0.190

1

2024-T351 Clad

0.313

1

I

I

Filler

1

2024-T3 Clad

0.063

1

I

2511580

EndPlate

1

1

I

Clip

1

2024-T42 Clad 2024-T3 Clad

0.040

2511580

0.063

1

Filler

1

2024-T3 Clad

0.100

I I

Clip

1

2024-T3 Clad

0.050

1

I

´•´•Shim, Laminated (Max. 0.032)

2511580 2511580 1

2511580 1 2511581

1

Replace Replace Replace Replace

3

3

Crew Seat Rails Instl., LH 8 RH

21 1 2411473

I

1

Replace Replace Replace

I

1

Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 10 of 15) EFFECTIVITY:

SRM-4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

11

ran 15/93

Learjet STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

DESCRIPTION

2511581 1

MATERIAL

Intercostal

1

2024-T3 Clad

0.040

1

0.040

2511581 1

Plate

1

2511581

Floor Board

Support

43

2511581

Floor Board Support Zee, Rail Support Zee, Rail Support

44

2024-T3 Clad 2024-T3 Clad 2024-T42 Clad 2024-T42 Clad

43

2024-T3 Clad

44

2024-T3 Clad

Channel, Rail Support Channel, Rail Support Seat Rail (3 ea.) Seat Rail (3 ea.)

43

2024-T42 Clad

0.040 0.040 0.040

44

2024-T42 Clad

43

SS37

44

S-537

End Plate

45

1

2511581

2511581 2511581 2511581

1

2511582

1

2511582

1 1

2511580

Assy.

EndPlate

2511580

2511580 2511580 2511581 2511581 2511581 2511581

´•´•ClipAssy.(2ea.) Clip(2ea.) Intercostal Assy. (2 ea.)

45 45

Intercostal

1

Rail

Support

Assy. (2 ea.)

45

I Replace

0.040

1

I Replace

0.080

1 1 1 1

I Replace I Replace I Replace I Replace Replace I Replace

0.040

0.040

I 2024-T3 Clad

0.063

1

I 2024-T42 Clad

0.040

1 2024-T3 Clad

0.040

2511581

Plate

45

2024-T3 Clad

0.040

2614063

´•Glareshieldlnstl.

46

2614063

Glareshield Instl.

47

2614063

Glareshield Instl.

48 46

2024-T42 Clad

0.050

49

6061-T6

0.050

46

2024-T42 Clad 2024-T42 Clad

0.050

49 49

3003-H14 Al

Doubler,LH&RH

49

Doubler,Center

49

2024-T3 Clad 2024-T3 Clad 2024-T3 Clad

2614063 I´•´•Glareshield 2614063

1

2614063

2614063

1

2614063 2614063 2611116 2611116

2611122

1

Angle Angle Screen

(3 ea.)

Pressurized ConnectorBox Instl.

1 1

Plate(2 ea.) Cover Assy.,

I I I

I

I

0.050

1

I

Replace Replace Replace Replace Replace Replace Replace

0.050

1

I

Replace

I

I Replace

I I 1

I I I

1

I

I

I

I

I I

I I 1

I I I

0.050

I 0.050

50 50

LH

RH

51

1

Assy., LH

RH

52

1

Cover

53

2611122 I´•´•Channel

53

5-707 S-325

53

2024-T3 Clad

0.050

54

2024-T3 Clad

0.050

Filler(8 ea.)

26111161´• Cover

1

Seal(8 ea.)

1 1

Rib Assy., LH Rib Assy., LH Rib Assy., LH Rib

2611117 1

I 1

50

RH

Replace Replace Replace Replace Replace Replace Replace Replace Replace

1 1

l´•´•Support

2511183 2611 117 2611117 2611117

I I I I I I i I

2611122

1

I Replace

I 1 I 1 I 1 1 1

2611122

2611122

1

I

45

Glareshield

1

I

Zee

2614063 1

Replace

I Replace

I

1

45

Zee

FIG. NO.

I

2024-T42 Clad

45

REPAIR

CODE

1

0.080

1

45

(FINISH GAGE

Angle Tie

1

2511581

22

EFF.

I

51

RH

55

RH

56 50

1 1 2024-T3 Clad

0.063

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1(Sheet 11 of 15) EFFECTIVITY:

SRM4

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

12

Tan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO. 2611118

2611118

I

1 1

2611118 1 2611119

2611119

I DESCRIPTION

1 1

2611119 1

End

I EFF.

Assy., LH 8 RH End Assy., LH 8 RH End

51

1

57

1

End End

Assy., Assy.,

RH

51

LH

RH

57

End

FIG. NO.

I

Replace

I Replace

1 I I 1 I I

I I I I I I

0.063

1 1

I I

0.063

1

I

I

I I I I

0.063

I I 2024-T3 Clad

50

REPAIR

CODE

I

I

1 1

IFINISH GAGE

2024-T3 Clad

50

LH

I MATERIAL

0.063

2611120

Angle Assy. Angle Assy. Angle Angle

2611122

Gusset

50

2024-T3 Clad 2024-T3 Clad 2024-T24 Clad

2611122

Angle, LH RH Support, LH RH Support, LH RH Cover(2 ea.)

50

S-522

60

2024-T3 Clad

0.032

56

2024-T3 Clad 2024-T42 Clad

0.032

1 1

0.050

1

2611120 2611120 2611120

2611122 2611122 2611122

1

58 59 58

59

50

1 1

I I 0.063

1

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 1 (Sheet 12 of 15) EFFECTIVITY:

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR 31-001 AND 36-001 AND

SRM4

53-20-00

Page

13

Jan 15/93

Learjet STRUCTURAL REPAIR MANUAL CODES

EFFECTIVITIES

SUBSEQUENT;

SUBSEQUENT; 36-001 AND SUBSEQUENT SUBSEQUENT; 36-001 AND SUBSEQUENT

35-001 AND

1

31-001 AND

2 3

31-001 THRU 31-034; 35-001 AND 31-035 AND SUBSEQUENT

4

31-001 AND

5

35-001 THRU 35-264; 36-001 AND SUBSEQUENT 35-001 THRU 35-477; 36-001 THRU 36-050 35-478 AND SUBSEQUENT; 36-051 AND SUBSEQUENT

6 7 8 9

10

SUBSEQUENT; 35-492 AND SUBSEQUENT;

36-051 AND SUBSEQUENT

31-001 THRU 31-027; 35-001 THRU 35-658, 35-660 THRU 35-662; 36-001 THRU 36-063 31-028 THRU 31-041, 31-043 THRU 31-051; 35-659, 35-663 THRU 35-666 31-042, 31-052 AND SUBSEQUENT; 35-676 AND SUBSEQUENT 36-064 AND SUBSEQUENT

12

35-001 THRU 35-519; 36-001 THRU 36-053 35-520 THRU 35-623; 36-054, 36-055

13

35-624 AND

14 15

35-001 THRU 35-534, 35-589, 35-590; 36-001 THRU 36-053 35-535 THRU 35-588, 35-591 AND SUBSEQUENT; 36-054 AND SUBSEQUENT

16

35-001 THRU

17

31-001 AND

18

31-001 THRU 31-022, 31-035 THRU 31-038; 35-478 THRU 35-668; 36-051 THRU 36-036 31-023 THRU 31-034; 35-662 THRU 35-666 31-039 AND SUBSEQUENT; 35-669 AND SUBSEQUENT; 36-064 AND SUBSEQUENT

11

19 20

SUBSEQUENT; 36-056 AND SUBSEQUENT

35-505; 36-001 THRU 36-053

SUBSEQUENT;

35-456 AND

SUBSEQUENT;

36-051 AND SUBSEQUENT

22

35-001 THRU 35-130; 36-001 THRU 36-033 35-131 AND SUBSEQUENT; 36-034 AND SUBSEQUENT

23

36-051 AND SUBSEQUENT

24

35-281 AND

25

26

35-001 THRU 35-281; 36-001 THRU 36-044 35-282 AND SUBSEQUENT; 36-045 AND SUBSEQUENT

27

31-011 AND

28 29

35-001 THRU 35-264; 36-001 THRU 36-044 35-265 AND SUBSEQUENT; 36-045 AND SUBSEQUENT

30

36-001 AND SUBSEQUENT

31 32

31-001 THRU 31-060; 35-390, 35-394 THRU 35-673; 36-048 THRU 36-063 31-061 AND SUBSEQUENT; 35-674 AND SUBSEQUENT; 36-064 AND SUBSEQUENT

33

31 SERIES AIRCRAFT EQUIPPED FOR EXTENDED RANGE

34

31-001 AND

35 36

35-001 THRU 35-091; 36-001 THRU 36-024 35-092 AND SUBSEQUENT; 36-025 AND SUBSEQUENT

37

36-001 THRU 36-059

38 39

35-001 THRU 35-122, 35-149 AND SUBSEQUENT; 36-001 THRU 36-032, 36-037 AND SUBSEQUENT 35-123 THRU 35-148; 36-033 THRU 36-036

40

35-123 AND

41

35-001 THRU 35-130; 36-001 THRU 35-034 35-131 AND SUBSEQUENT; 36-035 AND SUBSEQUENT

21

42

SUBSEQUENT; 36-045 AND SUBSEQUENT

SUBSEQUENT;

35-647 AND

SUBSEQUENT;

36-058 AND SUBSEQUENT

SUBSEQUENT; 35-265, 35-369, 35-371 AND SUBSEQU ENT

SUBSEQUENT; 36-042 AND SUBSEQUENT

Fuselage Assembly Repair Index Figure 1 (Sheet 13 of 15)

I

SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

EFFECTIVITY:

31-001 AND

SRM-4

PASSENGER/CREW DOOR

53-20-00

Page

14

Jan 15/93

STRUCTURAL REPAIR MANUAL 43

35-001 THRU

44

35-630 AND

45

31-063

46

35-001

35-629; 36-001 THRU 36-055 SUBSEQUENT; 36-056 AND SUBSEQUENT AND SUBSEQUENT; 35-675 AND SUBSEQUENT; 36-064 AND SUBSEQUENT THRU 35-039; 36-001 THRU 36-016 THRU 35-642; 36-017 AND SUBSEQUENT AND SUBSEQUENT; 35-643 AND SUBSEQUENT AND SUBSEQUENT; 35-040 AND SUBSEQUENT; 36-017 AND SUBSEQUENT AND SUBSEQUENT; 35-370, 35-390 AND SUBSEQUENT

47

35-040

48

31-001

49

31-001

50

31-001

51 53

35-370, 35-390 THRU 35-508 31-001 THRU 31-030; 35-509 THRU 35-664 31-001 THRU 31-030; 35-370, 35-390 THRU 35-664

54

31-031 AND

52

55

56 57 58 59 60

SUBSEQUENT; 35-665 AND SUBSEQUENT 31-072; 35-509 THRU 35-676 31-073 AND SUBSEQUENT; 35-677 AND SUBSEQUENT 31-001 AND SUBSEQUENT; 35-509 AND SUBSEQUENT 31-001 THRU 31-063; 35-001 THRU 35-674 31-064 AND SUBSEQUENT; 35-675 AND SUBSEQUENT 31-001 THRU 31-072; 35-370, 35-390 THRU 35-676 31-001 THRU

Fuselage Assembly Repair Index Figure 1 (Sheet 14 of 15) EFFECTIVITY:

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 24-INCH PASSENGER/CREW DOOR 31-001 AND

36-001 AND SRM-4

53-20-00

Page

15

Jan 15/93

Learjet STRUCTURAL REPAIR MANUAL NOTES:

Laminated shim stock, 0.002

or

0.003 lamination per MIL-S-22499

Type

1 Class 1

or

Class 2 1145-H19 aluminum

sheet.

1/4 OD

x

3/16 ID Teflon

1/2 OD

x

3/8 ID Teflon

3/8 OD

x

0.065 Wall

Type

I~

FBG

or

Tubing

Tubing

Tubing

FBM per MIL-P-15035

Heat Treat to 180,000 PSI Condition 1/2 Hard

Commercial Grade, Low

~g

Density Silicon Sponge Rubber

Tubing

0.650 OD

x

0.065 Wall 4130 Steel

0.187 OD

x

0.035 Wall 321 Stainless Steel

0.250 OD

x

0.035 Wall 321 Stainless Steel

321

or

347 Stainless Steel

Condition 1/4 Hard

~9

Make from NAS1169DD1OL

Screens 3/16. 0.032, 1/4- inch Centers

ABS Thermo Plastic 0.063,

Optional

to make from 0.060 Thermo Formidable Plastic

Fuselage Assembly Repair Index Figure 1 (Sheet 15 of 15)

EFFECTIVITY:

SRM-´•1

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT; 36-001 AND SUBSEQUENT, EQUIPPED WITH 24-INCH

PASSENGER/CREW DOOR

53-20-00

Page

16

Tan 15/93

Learietl STRUCTURAL REPAIR MANUAL FUSELAGEASSEMBLY-STRUCTURALIDENTIFTCATION Frame 17A FS 378.05

(ReD Frame 18 Frame 5

Frame 7

Frame 9

FS 160.77

FS 184.78

FS 209.19

FS 234.19

(Ref)

(Ref)

(Ref)

(Ref)

Frame 6

Frame 8

Frame 10

FS 151.12

FS 172.19

FS 196.99

FS 22159

(Ref)

(Ref)

(Ref)

(Ref)

Frame 4

1

9)

FS 381.79

Frame 11

Frame 13

Frame 13D

Frame 138

Frame 14

Frame 16

FS 258.01

FS 283.99

FS 308.49

FS 332.66

FS 355.49

1

1 1

I

(Ref)

(Ref)

(Ref)

Frame 13E

Frame 13C

FS 245.59

FS 271.99

FS 296.49

FS 321.24

(Ref)

(ReO

(ReO

(Ref)

I

I

I

I

I

I

1

------~L;

ii

1

1

litiTr~´•

~it

II I

_J~;i;

FS 346.63

FS 368.68

FS 392.50

(Ref)

(Ref)

(Ref)

(ReO

(7)

1

´•´•Cj

In I

I ,I

Il

II

ii\ il ii

j

J

1

(19

ii

IiI

5

(Ref) Frame 21 FS 411.95

i

j/l

;Sil

(ReD Frame 19

1

at,I:ii 1cIi -ii i´•lipI ia ti

_Ji i,

(6‘)

1

Frame 22 FS 421,42

Frame 17

Frame 15

Frame 13A

F’ame 20 FS 402.42

(Ref)

(Ref)

Frame 12

(Ref)

ii[i I

L___~

!_____.

iit I

ii ii i Il~i

ii’ ii ii ii __1__

-----,,,r---I

1

i

i

;I

;i

iic--~

ii

iblU

~uf

---------if---

~CiFC;

r,

-bll i,if

i1

i II

13)

(16~

(11)

(15)

(n)

(le)

(12

(VIEW LH SIDE LOOKING TNBOARD)

(TYPICAL)

2-15JD

Fuselage Assembly Repair Index Figure 2 (Sheet 1 of 15)

EFFECTIVITY:

31-001 AND SUBSEQUENT; 35-001 AND SUBSEQUENT;

SRM-4

36-001 AND SUBSEQUENT, EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

a

iii

;I

53-20-00

Page

17

Jan 15/93

I ii

~L

STRUCTURAL REPAIR NIANUAL FUSELAGE ASSEMBLY

STRUCTURAL IDENTIFICATION

Frame 17A

Frame 22

Frame 20

FS 421.42

FS 402.42

(ReR

(ReO

FS 378.05

Frame 16

Frame 14

Frame 13B

Frame 13D

Frame 13

Frame 11

Frame 9

Frame 7

Frame 5

(Rff)

FS 355.49

FS 332.66

FS 308.49

FS 283.99

FS 258.01

FS 234.19

FS 209.19

FS1&1.78

FS 160.77

(ReD

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

(Ref)

i

Frame 13C

Frame 13E

Frame 18

Frame 17

FramelS

Frame I3A

FS 381.79 1

FS 368.68

FS 346.63

FS 321.24

FS 296.49

FS 271.99

IRef)

(Ref)

(Ref)

(ReR

(ReR

(Ref) Frame 21

Frame 19

FS 411.95

FS 392.50

(Ref)

(Ref)

I

I

Frame #12 FS 245.59

I

(Ref)

Frame lO

1

I

FS 221.59

(Ref)

Frame 6 FS 172.19

FS 151.12

(Ref)

(Ref)

I

I

(Ref)

r

I;I

i s

1

f"

;´•i

i!ll’i;:---~II-lf I

I&

-----~lliZ---- --F L------

-----r

i:----.~____

L----4

r I ,~I, ,=,,i~Z----------h

O

(VIEW RH SIDE LOOKING ZNBOARD) (TYPICAL)

2-1491)

EFFECTZ?VITY:

Fuselage Assembly Repair Index Figure 2 (Sheet 2 of 15) SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITI-l 36-~CH PASSENGER/CREW DOOR 31-001 AND

36-001 AND

SRM-4

53-20-00

Page

18

Jan 15/93

1

Frame 8 FS 196.99

Frame 4

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

I DESCRIPTION

Fuselage StructureAssembly Fuselage Frames Instl. (Refer to 53-21-00) Fuselage Stringers Instl. (Refer to 53-22-00) Fuselage Windshield Instl. (Refer to 53-24-00) Fuselage Instrument Panel

2611000

I EFF.I

I MATERIAL

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

1

Structure Instl.

(Refer to 53-25-00) Fuselage Circuit Breaker

Panel

Structure Instl.

1

2311150

(Refer to 53-26-00) Fuselage Skins Instl. (Refer to 53-28-00) Fuselage Seat 8 Baggage Flr. (Refer to 53-29-00) Fuselage t

0.050

1

301 Stainless

0.063

F18

Replace

Fuselage Assembly Repair Index Figure 2 (Sheet 7 of 15) EFFECTIVITY:

SRM-4

31-001 AND

SUBSEQUENT; 35-001 AND SUBSEQUENT;

36-001 AND

SUBSEQUENT, EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR

53-20-00

Page

23

Tan 15/93

Lear ~Learjefl

STRUCTURAL REPAIR MANUAL ITEM NO.

JF~NISH

DWG. NO.

DESCRIPTION

2318763

Doubler Instl., LH 8 RH

2318763

Angle(2ea.) Doubler Instl. (2 ea.) Angle(2ea.) Angle(2ea.)

1

2688038 2688038 2688038

EFF.

REPAIR FIG. NO.

CODE

2 24

2024-T42 Clad

0.050

1

25

2024-T42 Clad 2024-T42 Clad

0.050

1

0.050

26

I

Replace

1

I

Replace Replace

1

Replace Replace Replace Replace Replace Replace Replace Replace

23

2618398

Doubler

1

2024-T42 Clad

0.020

2688151

Filler

1

2024-T3 Clad

0.090

27

2024-T3 Clad

0.032

1

I I I

Shim

2511416

(18 ea.)

2411325 I´•ExternalRelease Instl.

1

2411323 2411323

1

2024-T4 Rod

0.250

i

I

1

2024-T351 Plate

0.375

1

I

I I

I I

2411323 2411323 2411323 2411323 2411323

2411323 2411323 2411323

Spacer ´•´•BellcrankDrive

Angle Assy. ´•´•´•Angle I´•´•Spacer Linkage 1 I´•´•Linkage

1

1 1

1 1

I

´•´•Bellcrankldler Pin (2 ea.) Pin

(2 ea.)

2411328

2411325

Spring ´•´•Spring

2411328 2611127 1

6061-T6

0.375

1

0.375

1

1

2024-T3

0.125

1

2024-T351 Plate 2024-T4 Al Rod

0.500

2024-T4 Al Rod 2024-T351 Plate

0.438

1

Ij9

1

MS24585-C414

30 30

2611125

End,LH&RH End,LH&RH Bracket,LH&RH

2611125

Support

30

2611124

2611126 2611128

Rib, LH

1

2611128

Cover

8 RH

8 RH

Cover

2611128

´•´•´•Support(3ea.) Filler(Gea.)

2611128

30

I´•Doubler(FS196, between Stringers 10 8 11) Doubler (FS 196, between Stringers 10 8 11)

261 8551

0.050

1 1

I I

0.071

1

I

30

2024-T42 Clad

0.050

1

I

30

S-522

30

2024-T42 Clad ABS Therm Plastic 2024-T42 Clad S-626 2024-T42 Clad

0.050

1 1

I I I

Replace Replace Replace Replace Replace Replace

30

30

2618314

Replace Replace

1

Filler(2ea.) RH

I

0.040

2611125

Bracket, LH

I

I

1

2611125

1

Replace Replace

0.040

30

2511216

I

0.050

30

Support Support, LH 8 RH (2 ea.) Gusset,LH&RH

1

2611125

F3

Replace Replace Replace Replace

1

0.500

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

30

30

2611125

I F3

0.050

Seal

2511183

1

0.438

2024-T42 Clad 2024-T42 Clad 2024-T42 Clad

30

Assy., LH

I

1

Connector Box Instl. Cover

2611118 1 2611123

I

2024-T4 Plate

1

Assy.

S-580

1

29

Retainer

I

1

28

Guide Pin (2 ea.) Flush Latch Handle

2411323

18

I GAGE

2

2618397 I´•Doublerlnstl.

17

MATERIAL

30 30 30

2024-T3 Clad 2024-T42 Clad

I

I

0.040

1

I

0.100 0.063

1 1

I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace

0.063 0.040

1

31

12024-T3 Clad

0.080

1

I

Replace

32

2024-T3 Clad

0.050

1

I

Replace

Fuselage Assembly Repair Index Figure 2 (Sheet 8 of 15) EFFECTIVITY:

31-001 AND

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR 36-001 AND

aad~

53-20-00

Page 24 Jan 15/93

Learjet

SIRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

3111116 1

RibAssy., LH Rib(2ea.)

3111118 3111118

8 RH

IFINISH

REPAIR

CODE

FIG. NO.

GAGE

I

I

2024-T42 Clad

0.507

1

I

33

S-522

0.032

33

2024-T42 Clad

0.507

1 1 I

I I I

1 1

I I

1 1 1 1

I I I I

33

I

1

33

I 2024-T42 Clad 2024-T42 Clad

0.050

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

3111118

Rib

33

3111118

Support

33

2024-T42 Clad

0.040

3111118

Filler

33

2024-T42 Clad

0.040

´•´•´•Angle ´•´•´•Angle

33

S-5001

0.010

33

S-5001

0.012

´•´•´•Angle Seal (4 ea.)

33

S-5001

0.015

33

[i~

0.010

1

I

34

2024-T3 Clad

0.063

1

I

2024-T42 2024-T42 2024-T42 2024-T42

Clad Clad Clad

0.063

1

I

0.063

1

I

0.040

1

I

Clad

0.040

2024-T3 Clad 2024-T42 Clad

0.050

1 1 1

I I I

I I I

Replace Replace Replace Replace

Replace Replace

3111119

3111119 3111119 3111119 2511332

2511215

1

Skin Doubler, LH Aft Blower Evaporator Support Structure instl.

2511216 2511216 1 2511216

1

2619042 1

2411321

1

2311258

1

2311258

1

35 36

Channel

37

Clip(2 ea.)

37

Bracket

1

Channel(Above Escape Hatch) Inner Skin Instl. (FS 160 to 209, RH 8 LH) Skin, LH

0.071

1

Bracket,LH&RH Bracket,LH&RH

2511216

20

1

33

Filler

3111119

I MATERIAL

33 33

´•´•´•Stiffener(3ea.)

3111119

1

Pressurized Connector Box Instl. Cover

3111119

I EFF.

´•´•CoverAssy.,LH&RH

3111117

19

I DESCRIPTION

1

0.040

1

8 RH

38

2024-T42 Clad

0.050

2311258

Skin, LH 6 RH

39

2024-T42 Clad

0.050

2311258

Strap

40

2024-T3 Clad

0.050

1 1 1

2311258 1

Filler

40

2024-T3 Clad

0.160

1

1

2024-T3 Clad

0.250

1

I

1

2024-T351

1.600

1

I

0.040

1

j

I

I

2411320

1

2411322

Escape Hatch Instl. Escape Hatch Assy. (Refer to Chapter 52)

1

2411322

I´•´•ClipAssy.

2411322

1

1

ClipSupport

1

2024-T3 Clad

1

NAS1464-038-05C

Doubler, Aft Fuselage Window

1

2024-T42 Clad

0.063

1

I

Stiffener 8 Plate Instl., LH

1 1

2024-T42 Clad

0.050

1

0.050

1

2024-T42 Clad 2024-T3 Clad 2024-T3 Clad 2024-T42 Clad

I I I I I

´•´•´•Clip

2411322 2411322

1

Strap Tee Support

2411322

1

2511674

1 1 1 1

RH

I

2511674

Clip(2 ea.) Angle Plate (LH Only) Plate (RH Only) Stiffener(3 ea.)

0.050

1 1 1 1 1

2511674

Filler

1

2024-T3 Clad

0.063

1

I

2511674 i

Stiffener

1

2024-T42 Clad

0.063

1

I

2511674

2511674 2511674

251 1 674

Replace Replace Replace Replace Replace Replace

1 1

0.080 0.050

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 2 (Sheet 9 of 15) SUBSEQUENT;

35-001 AND

SUBSEQUENT;

EFFECTIVITY:

31-001 AND

SRM-4

36-001 AND SUBSEQUENT, EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR

53-20-00

Page

25

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL ITEM

NO.

DWG. NO.

I

2511674 2511644

I´•´•Fitting

2411324

1

I EFF.

I

IFINISH GAGE

2024-T3 Clad 2024-T42 Clad

1 1

I MATERIAL

1

Plate Stiffener

2511674

0.050

0.063

I

REPAIR FIG. NO.

CODE

1 1

I I

I

I

Replace Replace Replace

Inner Doubler

Assy., (Escape Hatch)

1

2411324 I´•´•Doubler

41

6061-T6

0.040

1

I

2411324 I´•´•Doubler

42 41

A/R

1 I

2411324 2411326 2411326

Spacer(4ea.) Spacer(4ea.) NutRetainer(4ea.) NutRetainer(4ea.)

6061-T6 2024-T42 Clad

0.040

I I

42

2024-T42 Clad

A/R

I

41

2024-T42 Clad

0.040

I I

42

2024-T42 Clad

0.040

2411323 1

Plate

41

2024-T3 Clad

0.090

42

2024-T3 Clad

0.090

2024-T42 Clad

0.040

1 1 1 1

I I I I

Replace Replace Replace Replace Replace Replace Replace Replace Replace

1 I 1 1 1

I I I I I I

Replace Replace Replace Replace Replace Replace

1 I 1 1

I I I I

Replace Replace Replace Replace

1 1

I I

I

I I

0.050

2411324

Plate

2411323 1

2411321

1

Frame (FS 350, RH Side Doubler Instl.

2489168

Only)

1 1

2489168

Doubler

1

2024-T42 Clad

0.050

2489168

RadiusFiller(4ea.) DoublerAssy., Fwd (2 ea.)

1

2024-T3 Clad

0.125

2489168 2489168

Doubler

2489168 1

Wedae

2489168

Filler

2489168 2489168

2489168 1 2489168

1

2489168 2489168

1

I

Filler(eea.) ´•´•AngleAssy. Angle

2489168

1

2489168 1

Aft

2489168 1

Wedne

I

3118916

Wedae

I

´•´•Doubler Crew Seat Rails

2411473

2024-T3 Clad

0.050

1

2024-T3 Clad

0.025

2024-T42 Clad 2024-T3 Clad

0.050

1

2024-T42 Clad

0.050

1

2024-T3 Clad

0.125

I

1

0.160

1

I

1

2024-T3 Clad 2024-T3 Clad 2024-T3 Clad

0.160

1

I

1

2024-T3 Clad

0.025

I I I I I

Replace

I

1

I

1

2024-TJ2 Clad

0.050

1

2024-T3 Clad

0.190

1 I 1 1

2024-T351 Clad

0.313

1

I

I

3

3

Instl., LH 8 RH

0.190

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

1

I´•Doublerlnstl. (ADFAntenna)

3118919

0.190

1

1

Filler(2ea.) ´•´•AngleAssy. Angle

2489168 1

2024-T3 Clad

1

(2ea.)

2489168

2489168

0.040

1

2

I

2489168

I 2024-T3 Clad

1

I

Wedae Filler

2489168

I

1

1

Wedae Doubler Instl. (ADF Antenna) Doubler Radius Filler (4 ea.)

´•´•DaublerAssy.,

2489168

21

I DESCRIPTION

1

I

I Replace

2511580 1

Filler

1

2024-T3 Clad

0.063

1

I

2511580 1

End Plate

1

2024-T42 Clad

0.040

1

I

Clip

1

2024-T3 Clad

0.063

Filler

1

2024-T3 Clad

0.100

1 j

I I

Replace Replace Replace Replace

Clip

1

2024-T3 Clad

0.050

1

I

Replace

´•´•Shim, Laminated (Max. 0.032)

2511580

2511580

1

2511580 1

2511581

1

I

1

Fuselage Assembly Repair Index Figure 2 (Sheet 10 of 15)

I

EFFECTIVITY:

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 36-INCH PASSENGER/CREW DOOR 31-001 AND 36-001 AND

SRM-4

53-20-00

Page

26

Jan 15/93

Learjet j

STRUCTURAL REPAIR MANUAL ITEM

DWG.

NO.

NO.

I

2511581 1 2511581

I DESCRIPTION

1

Intercostal Tie

End Plate

2511580 2511580

2511581

Intercostal

2511581 2511581

22

I

1

I

0.040 0.080

1 1 1

I I

44

2024-T3 Clad 2024-T42 Clad 2024-T42 Clad 2024-T3 Clad 2024-T3 Clad

43

2024-T42 Clad

0.040

1 1

I I

44

2024-T42 Clad

0.040

43

S-537

1

1 I

I I

44

S-537

1

I

I

Replace Replace Replace Replace

I

I 1

I I

Replace Replace

I I I I I I

Replace Replace Replace Replace Replace Replace Replace

43 44 43

45

1

45

Assy. (2 ea.)

1

0.040

0.040

I

2024-T3 Clad 2024-T3 Clad

0.040 0.040

1

I

46

2024-T42 Clad

0.050

49

0.050

1 1

I I

0.050

1

I

0.050

1

I 1 1

j

1 I I I I

I I I I I

1

I

45

1

45

0.063

I 2024-T42 Clad

1

0.040

I

46

47 48

Angle

46

6061-T6 2024-T42 Clad

2614063

Angle

49

2024-T42 Clad

2614063

Screen

49

3003-H14 Al

49

2024-T3 Clad

0.050

49

2024-T3 Clad

0.050

2614063

´•´•Glareshield

2614063

1

1

Pressurized ConnectorBox Instl.

2611116

2611116 2611122 2611122 2611122 2611122

Plate(2 ea.) Assy., Cover Assy., 1 ´•´•Support Cover

2611122

2611116 1 2511183 2611117

(3 ea.) RH Doubler, LH

Doubler, Center

2614063

1 1 1

2611117 2611117 1 26111171

I

Replace Replace Replace Replace

1

Replace Replace Replace

50

2024-T3 Clad

50

LH 8 RH

51

RH

52

LH

Replace Replace

I 1 I 1 I 1

45

2614063

2614063

Replace Replace Replace Replace Replace

0.040

2024-T3 Clad

45

45

´•Glareshieldlnstl. Glareshield Instl. 2614063 Glareshield Instl. 2614063 Glareshield 2614063 1

0.080

2024-T42 Clad

45

Rail Support Zee Zee Plate

2511581 2511581

1

45

´•´•ClipAssy.(2ea.) Clip(2ea.) Intercostal Assy. (2 ea.)

2511580

CODE

0.040

1

Support Floor Board Support 2511581 2511581 Zee, Rail Support 2511581 1 Zee, Rail Support 2511581 1 Channel, Rail Support 2511581 1 Channel, Rail Support 2511582 ´•´•SeatRail(3ea.) 2511582 ´•´•SeatRail(Sea.) 2511580 ´•´•EndPlateAssy.

REPAIR FIG. NO.

IFINISH GAGE 0.040

1

Floor Board

2511581

I MATERIAL 2024-T3 Clad 2024-T3 Clad

1

Angle Plate

2511581

I EFF.I

1 1

53

S-707

´•´•Channel

53

S-325

´•´•FiBer(8ea.)

0.050

I I I 1

53

\2024-T3Clad

Cover

54

2024-T3 Clad

Seal (8 ea.) Rib Assy., LH 8 RH

50

51

1

I

I

I

Rib Assy., LH 6 RH RH Rib Assy., LH Rib

55

1

I

I

I

56

1

I

I 1

I j

0.050 0.050

1

50

2024-T3 Clad

I

0.063

Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 2 (Sheet 11 of 15) EFFECTIVITY:

31-001 AND

36-001 AND

SUBSEQUENT; 35-001 AND SUBSEQUENT;

SUBSEQUENT, EQUIPPED

PASSENGER/CREW DOOR

WITH 36-INCH

53-20-00

Page

27

jan 15/93

~i´•tl STRUCTURAL REPAIR MANUAL ITEM NO.

DWG. NO.

I

2611118

1 1

2611118

2611118 1

2611119

2611119 2611119

I DESCRIPTION

1 1

End Assy., LH 8 RH End Assy., LH 8 RH End End End

Assy., Assy.,

LH 8 RH LH 8 RH

End

I EFF. 51 57

MATERIAL

1 i

51 57

I I 2024-T3 Clad

50

1 1

0.063

I I 2024-T3 Clad

50

IFINISH GAGE

58

2024-T3 Clad

0.063

2611120

59

0.063

2611122

Gusset

50

2024-T3 Clad 2024-T24 Clad

2611122

Angle, LH 8 RH Support, LH 8 RH Support, LH 8 RH Cover (2 ea.)

50

S-522

60

2024-T3 Clad

0.032

55

2024-T3 Clad 2024-T42 Clad

0.032

2611120 2611120

1

2611122 2611122 2611122

1

58 59

50

1 1

I I

I Replace I Replace

1

I

I I

I Replace I Replace

I I

I Replace I Replace

1

I

1

I

I

I

1

I

1

I

0.063

Angle Assy. Angle Assy. Angle Angle

2611120

REPAIR FIG. NO.

CODE

I 0.063

1 0.050

Replace

Replace

Replace Replace Replace Replace Replace Replace Replace

Fuselage Assembly Repair Index Figure 2 (Sheet 12 of 15) EFFECTIVITY:

31-001 AND 36-001 AND

SRM-I

SUBSEQUENT; 35-001 AND SUBSEQUENT; SUBSEQUENT, EQUIPPED WITH 36-INCH

PASSENGER/CREW DOOR

53-20-00

Page

28

Jan 15/93

Learjet

STRUCTURAL REPAIR MANUAL CODES

EFFECTIVIT\ES

SUBSEQUENT;

SUBSEQUENT; 36-001 AND SUBSEQUENT SUBSEQUENT; 36-001 AND SUBSEQUENT

35-001 AND

1

31-001 AND

2 3

31-001 THRU 31-034; 35-001 AND 31-035 AND SUBSEQU ENT

4

31-001 AND SUBSEQU ENT; 35-492 AND

5

35-001 THRU

6 7 8

9 10 11 12 13 14 15 16

SUBSEQUENT;

36-051 AND SUBSEQUENT

35-264; 36-001 AND SUBSEQUENT 35-001 THRU 35-477; 36-001 THRU 36-050 35-478 AND SUBSEQUENT; 36-051 AND SUBSEQUENT 31-001 THRU 31-027; 35-001 THRU 35-658, 35-660 THRU 35-662; 36-001 THRU 36-063 31-028 THRU 31-041, 31-043 THRU 31-051;35-659, 35-663 THRU 35-666 31-042, 31-052 AND SUBSEQUENT; 35-676 AND SUBSEQUENT; 36-064 AND SUBSEQUENT 35-001 THRU 35-519; 36-001 THRU 36-053 35-520 THRU 35-623; 36-054, 36-055 35-624 AND SUBSEQUENT; 36-056 AND SUBSEQUENT 35-001 THRU 35-534, 35-589, 35-590; 36-001 THRU 36-053 35-535 THRU 35-588, 35-591 AND SUBSEQUENT; 36-054 AND SUBSEQUENT 35-001 THRU 35-505; 36-001 THRU 36-053

17

31-001 AND

18

SUBSEQUENT;

35-456 AND

SUBSEQUENT;

36-051 AND SUBSEQUENT

19

31-001 THRU 31-022, 31-035 THRU 31-038; 35-478 THRU 35-668; 36-051 THRU 36-036 31-023 THRU 31-034; 35-662 THRU 35-666

20

31-039 AND

21

35-001 THRU

22

35-131

23

36-051 AND SUBSEQUENT

24

35-281 AND

25

SUBSEQUENT; 35-669 AND SUBSEQUENT; 36-064 AND SUBSEQUENT 35-130; 36-001 THRU 36-033 AND SUBSEQUENT; 36-034 AND SUBSEQUENT SUBSEQUENT; 36-045 AND SUBSEQUENT

26

35-001 THRU 35-281; 36-001 THRU 36-044 35-282 AND SUBSEQUENT; 36-045 AND SUBSEQUENT

27

31-011 AND

28

35-001 THRU

29

35-265 AND

30

36-001 AND SUBSEQUENT

SUBSEQUENT; 35-647 AND SUBSEQUENT; 35-264; 36-001 THRU 36-044

SUBSEQUENT;

31

31-001 THRU

32

31-061 AND

36-058 AND SUBSEQUENT

36-045 AND SUBSEQUENT

31-06