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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
0020
R3)
Page
7 of
7
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
51-Contents
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Learjet I Learjet
STRUCTURAL REPAIR MANUAL Chapter
Chapter Section
Subject
Page
I
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Date
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Subject
1
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SRM-I
Date
List of Effective
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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
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0 O
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b
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n~
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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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fuselage skin.
~e
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a46’
Measured at OML of Bulkhead Intersection with Bottom apt
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ar
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ii
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(TYPICAL) (DOUBLE FRAME MEMBER CROSS SECTION)
Icno
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
Ui~´•
Stringer LO
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Stringer 11
Stringer 12 Stringer 13
Stringer 13 Stringer 14
Stringer 14 Stringer 15
Stringer 16 Stringer 17 Stringer 18 Stringer 19
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0
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Stringer 14
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Stringer 15
Stringer 16 Stringer 17 Stringer 18 Stringer
I’-b
I
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19
Stringer 21-~
’--Stringer 21
(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
Stringer 2
Stringer 3
Stringer 3 Stringer 4
1
Stringer 4 Stringer 5 Stringer 6
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Stringer Stringer 6 Stringer
1
7
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Stringer 8
Stringer 9 Stringer 10
Stringer
11 Door Frame
Stringer 12 Stringer 13
Seat Track
Stringer 14
Stringer 15 Stringer 16 Keel Beam Web
Stringer Door
Stringer 18 Stringer 19
Stringer
Stringer 21
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(FRAME 13 LOOKING AFT) Stringer Stringer 3 Stringer 4 Stringer 5Stringer 6 --~J_/ Stringer 7
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Stringer 10
Stringer 10 Support
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Stringer 11
Stringer 11
Stringer 12 Stringer 13 Longeron
\~n
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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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0~ 00
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\
8 in
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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
´•4L~
9
3´•‘b~
1
I
,1´•´•c:2;"*2´•\
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Aircraft Skin (ReO
a
\F’:FPb\
(TYPICAL)
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(SINGLE FRAME MEMBER CROSS SECTION)
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8p ~L’
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(TYPICAL) (DOUBLE FRAME MEMBER CROSS SECTION)
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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9
Stringer 10
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L5
Stringer 16 Stringer 17
Stringer 16 Stringer 17
Stringer 18 Stringer 19
0.0
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(FRAME 5 LOOK1[NG AI;T)
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Stringer Stringer 3 Stringer 4 Stringer 5
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Stringer 13 Stringer 14
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IZb
Stringer
O Deer
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19
Stringer 21--~
’-Stringer
21
(FRAME 11Z~OOKING AFT)
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
Stringerl Stringer 3 Stringer4
Stringer 5 Stringer 6
Stringer Stringer 6 Stringer
3
7
1
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Stringer
9
Stringer
10
Stringer
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Stringer 12 Stringer 13
Seat Track
Stringer 14 Stringer 15 Stringer 16 Keel Beam Web
iL1
Stringer
Door
Stringer 18 Stringer 19
Stringer
Stringer
21
IIinge
21
(FRAME 13 LOOKING AFT) Stringer 2 Stringer 3 Stringer Stringer 5 Stringer 6 Stringer 7
Stringer
"7
2 ~--Strineer 3 4
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/V
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Stringer
Stringer 8
i
8
Stringer 9
Stringer 9
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I \-B. L.
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MODEL 25SERIESAIRCRA~T
2
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SRM~
0.00
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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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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
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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.
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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
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606.084
589.28
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STRUCTURAL STATIONS
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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.
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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--\
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(I
I
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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
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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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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
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Stringer 5 Stringer 6 Stringer 7
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Stringer
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Stringef~cStringer 2 r
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Stringer 10
I Support
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~B.L.
Stringer 12 Stringer 13
Longeron
St ringer 6
Stringer 7
Splice
Stringer 8
StringerlO
3
Stringer 4
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0´•00
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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
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34’
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125. 00
117.10’
108.10
106.15
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86.50
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77.70 69.
60.05’
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00
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37.85 31.35
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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
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b-I
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BL 4. 50
BL 13. 24
BL
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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
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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
(FS 8~.75)
00000
Waterlines
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Wt, 48.75
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I
I
FuselageVertical Centerline
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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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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\\~Stringer
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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~,
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AILERONSTRUCTURAL
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STA~IONS
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59.46 ~W.S. 244.102 51.40 ----1---
51.10
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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
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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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(VIEW LOOKING AFT)
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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
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9
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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
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STA.
624.63
644.89
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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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FLAP STRUCTURAL STATIONS
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’
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BL
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BL
54
BL, 23. 17
BL 44. l0 BL 86. 215 BL
35BL,
67.
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7
1
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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
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Aircraft Measurement
EFFE(-TIVITY:
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WL 61.96
a
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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
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(LH SmB LDDKING ATT)
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M
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(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
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o
Is
200
o
o
o
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o
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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
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s
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~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
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,1
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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
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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
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L
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4
1
6
2
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19
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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
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11---/
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~---15
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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
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6 7
8 9
10 11 12
101 102 201
202 1
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3
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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
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201 101
101
or
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52-40-20
102
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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
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53-Contents
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margin of the
page. 53
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List of Effective
Pages Page 1
Jun 1/95
Learjet ~Learjet STRUCTURAL REPAIR MANUAL Chapter
Chapter I
Section
Subject
Page
53-22-05
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1 1
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101
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
5
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Date
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
subject
Page
53-55-00 53-55-00
101
5355-00
201
102
Date
May 15/92 May 15/92 May 15/92
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