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Do - L 410 - 1232.2 MAINTENANCE MANUAL FOR THE L410 UVP - E AEROPLANE L410 UVP – E9 AEROPLANE L410 UVP – E20 AEROPLANE
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Do - L 410 - 1232.2
MAINTENANCE MANUAL FOR THE
L410 UVP - E AEROPLANE L410 UVP – E9 AEROPLANE L410 UVP – E20 AEROPLANE
November 1/2011 edition
686 04 Kunovice Czech Republic
We cannot correct an error unless we know of its existence, therefore, it is essential that you do your part. Comments, corrections regarding this manual are welcomed and should be sent to:
Documentation Department Aircraft Industries, a.s. Na Záhonech 1177 686 04 Kunovice Czech Republic
EUROPE or fax us to:
Documentation Department +420 572 816 006 or e-mail us to:
[email protected]
2011 Aircraft Industries, a.s., 686 04 Kunovice, Czech Republic All rights reserved. No part of this manual may be reproduced or transmitted in any form or by any means, electronic or mechanical, including photocopying and recording, for any purpose without the express written permission of Aircraft Industries, a.s.
MAINTENANCE MANUAL
LIST OF CHAPTERS CHAPTER 0 CHAPTER 5 CHAPTER 6 CHAPTER 7 CHAPTER 8 CHAPTER 9 CHAPTER 10 CHAPTER 11 CHAPTER 12 CHAPTER 20 CHAPTER 21 CHAPTER 22 CHAPTER 23 CHAPTER 24 CHAPTER 25 CHAPTER 26 CHAPTER 27 CHAPTER 28 CHAPTER 29 CHAPTER 30 CHAPTER 31 CHAPTER 32 CHAPTER 33 CHAPTER 34 CHAPTER 35 CHAPTER 38 CHAPTER 51 CHAPTER 52 CHAPTER 53 CHAPTER 54 CHAPTER 55 CHAPTER 56 CHAPTER 57 CHAPTER 61 CHAPTER 71 CHAPTER 76 CHAPTER 77 CHAPTER 79 CHAPTER 80 CHAPTER 82 CHAPTER 90
EFFECTIVITY ALL
AIRCRAFT TIME LIMITS / MAINTENANCE CHECKS DIMENSIONS AND AREAS LIFTING AND SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING PLACARDS AND MARKINGS SERVICING STANDARD PRACTICES AIR CONDITIONING AUTO FLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT / FURNISHINGS FIRE PROTECTION FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION INDICATING / RECORDING SYSTEMS LANDING GEAR LIGHTS NAVIGATION AND PITOT / STATIC OXYGEN WATER / WASTE STRUCTURES DOORS FUSELAGE NACELLES STABILIZERS WINDOWS WING PROPELLERS POWER PLANT ENGINE CONTROLS ENGINE INDICATING OIL STARTING WATER INJECTION SUPPLEMENTS
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MAINTENANCE MANUAL
RECORD OF ISSUED DOCUMENTATION BULLETINS No.
Bulletin No. L 410 UVP-E / ....
Data of issue
Number of Revised chapters
1
001 d
Dec 15 / 95
000-1, 009-1, 010-1, 011-1, 012-1, 020-1, 022-1, 023-1, 024-1, 025-1, 026-1, 027-1, 028-1, 029-1, 030-1, 031-1, 032-1, 033-1, 035-1, 051-1, 052-1, 077-1, 079-1, 082-1, 090-1
2
004 d
Dec 15 / 95
034-1,
Jan 8 / 96
000-2, 021-2, 023-2, 024-2, 027-2, 028-2, 029-2, 051-2, 053-2, 055-1, 057-1, 076-1
3
006 d
Aug 20 / 96
011-2, 012-2, 022-2, 031-2, 038-1
4
010 d
Jan 10 / 97
033-2
5
020 d
Mar 28 / 97
020-2, 027-3, 029-3, 031-3, 032-2, 034-2, 035-2, 071-1
6
027 d
Jan 6 / 98
009-2, 012-3, 027-4, 028-3
7
028 d
Feb 10 / 98
011-3
8
037 d
Oct 1 / 98
022-3, 026-2, 027-5, 028-4, 029-4, 030-2, 031-4, 032-3, 034-3, 035-3, 061-1, 071-2, 076-2, 079-2
9
040 d
Feb 25 / 99
025-2, 033-3
10
045 d
May 3 / 99
020-3
11
053 d
Apr 30 / 99
007-1, 027-6, 028-5, 082-2
12
060 d
Nov 20 / 01
012-4
13
062 d
Aug 17 / 05
024-3, 026-3, 028-6, 029-5, 030-3, 031-5, 032-4, 033-4, 034-4, 061-2, 076-3, 077-2
14
068 d
Sep 11 / 06
031-6
15
070 d
Sep 11 / 06
051-3
16
075 d
17
081 d
Feb 23 / 07
008-2, 012-6, 027-8, 057-2
18
097 d
Nov 20 / 07
004-1, 008-3, 009-3, 011-4, 012-7, 024-4, 025-3, 026-4, 027-9, 028-7, 029-6, 033-5, 034-5
19
098 d
Mar 11 / 08
022-4, 029-7, 030-5, 032-5, 033-6, 079-3
20
101 d
May 16 / 08
20-4
21
102 d
Oct 31 / 08
012-8, 023-3, 028-8, 030-6
EFFECTIVITY
ALL
Date of Entry and Signature
Not issued
RECORD OF ISSUED DOCUMENTATION BULLETINS Page: 1 Nov 1/11
MAINTENANCE MANUAL
No.
Bulletin No. L 410 UVP-E / ....
Data of issue
Number of Revised chapters
22
107 d
Nov 18 / 08
004-2, 012-9, 024-5, 025-4, 026-5, 027-10, 028-9, 029-8, 033-7, 034-6, 052-2, 055-2, 079-4, 080-1
23
135d
Nov 1 / 11
022-5
24
142d
Feb 15/12
022-6, 030-7
Date of Entry and Signature
MM is reissued Nov 1/11. This contains revisions from No. 1 to No. 24 012-10, 020-5, 023-4, 024-6, 026-6, 027-11, 028-10, 030-8, 034-7, 055-3, 057-3, 061-3 005-1, 012-11, 020-6, 022-7, 023-5, 026-7, 027-12, 028-11, 029-9, 030-9, 031-7, 032-6, 033-8, 034-8, 053-2, 061-4, 071-3, 076-4, 077-3, 079-5 020-7, 024-7, 027-13, 029-10, 032-7, 034-9
25
145d
May 31/12
26
170d
Apr 5/13
27
178d
Nov 15/13
28
196d
May 30/14
010-2, 012-12, 020-8, 021-3, 023-6, 024-8, 025-5, 026-8, 027-14, 028-12, 029-11, 030-10, 031-8, 032-8, 033-9, 034-10, 035-4, 051-4, 052-3, 053-3, 054-1, 055-4, 056-1, 057-4, 061-5, 071-4, 076-5, 077-4, 079-6, 080-2, 082-3
29
208d
Dec 10/14
011-5, 012-13, 020-9, 021-4, 022-8, 023-7, 024-9, 025-6, 028-13, 029-12, 034-11, 057-5, 061-6
30
212d
Apr 15/15
31
220d
Nov 20/15
32
225d
Mar 30/16
33
236d
Mar 10/17
005-2, 012-14, 020-10, 022-9, 023-8, 027-15, 031-9, 032-9, 034-12, 057-6 012-15, 020-11, 022-10, 024-10; 026-9; 027-16, 028-14, 029-13; 032-10, 034-13, 057-7, 077-5 011-6, 020-12, 025-7, 051-5, 055-5, 057-8 008-4, 009-4, 022-11, 027-17, 028-15, 029-14, 032-11, 034-14, 051-6
EFFECTIVITY
ALL
RECORD OF ISSUED DOCUMENTATION BULLETINS Page: 2 Mar 10/17
CHAPTER
AIRCRAFT
MAINTENANCE MANUAL
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MAINTENANCE MANUAL
CHAPTER 0 AIRCRAFT CONTENTS Subject
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INTRODUCTION Description and Operation General Conception Maintenance manual breakdown Figures Revisions Modifications Limitation of information effectivity Replacement of instruments and units Abbreviations
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INTRODUCTION DESCRIPTION AND OPERATION 1. General The Maintenance Manual (hereinafter referred to as MM) has been prepared according to the specification for manufactures maintenance data - A.T.A. Specification No. 100 and GAMA Specification No. 2. It covers the technical description and instructions for operation and maintenance of all aircraft parts. Exception is being made for complicated purchased products only (engines, propellers, radio communication, etc.), which are provided with separate documentation by the manufacturer. Reference is made to such documentation in this MM. This MM applies to the L 410 UVP-E, L 410 UVP-E9 and L 410 UVP-E20 aircrafts. All pages are identified by the model designation L 410 UVP-E, E9, E20 in the heading. Complete new chapters, sections or subjects are being issued to distinguish information applicable to each of the above aircraft types. Any modifications are covered by the appropriate supplements to this MM – refer to the chapter 90. This MM entitles the operators carry out work given in the MM only on the aircraft of which they are owners. This MM is inalienable and cannot be transferred to third party, otherwise the operator loses the possibility for the MM to be maintained and revised.
2. Conception Every system of the aircraft having a specific function is comprehended in an independent chapter as is obvious from the MANUAL BREAKDOWN REFERENCE LIST. General technological instructions and procedures, which are commonly known, as e.g. riveting, cable splicing, welding, etc., are not included in this MM, as it is anticipated that servicing personnel are of relevant qualification.
3. Maintenance manual breakdown The MM is divided into chapters that are further divided into sections and subjects. The division is expressed by a number that is located on the outer bottom edge of the page. For example:
32 20 LANDING GEAR (chapter) NOSE GEAR (section)
29 11 01 HYDRAULIC POWER (chapter) NORMAL CONTROLS (section) SUCTION FILLING CONNECTION (subject)
EFFECTIVITY: ALL
000.01.00 Page: 1 Nov 1/11
MAINTENANCE MANUAL Page numbering is separate for each section and subject. In the numbering, the internal breakdown of each subject to the individual topics is reflected, which makes orientation and introduction of amendments easier. Page numbering is separate for each section and subject: DESCRIPTION AND OPERATION
TROUBLE SHOOTING
SERVICING
REMOVAL / INSTALLATION
ADJUSTMENT / TEST
INSPECTION / CHECK
EFFECTIVITY: ALL
Page
1 to 100 (eff. L410 UVP-E; E9; E20)
Page
1001 to 1100 (eff. L410 UVP-E)
Page
2001 to 2100 (eff. L410 UVP-E9)
Page
3001 to 3100 (eff. L410 UVP-E20)
Page
101 to 200 (eff. L410 UVP-E; E9; E20)
Page
1101 to 1200 (eff. L410 UVP-E)
Page
2101 to 2200 (eff. L410 UVP-E9)
Page
3101 to 3200 (eff. L410 UVP-E20)
Page
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Page
1301 to 1400 (eff. L410 UVP-E)
Page
2301 to 2400 (eff. L410 UVP-E9)
Page
3301 to 3400 (eff. L410 UVP-E20)
Page
401 to 500 (eff. L410 UVP-E; E9; E20)
Page
1401 to 1500 (eff. L410 UVP-E)
Page
2401 to 2500 (eff. L410 UVP-E9)
Page
3401 to 3500 (eff. L410 UVP-E20)
Page
501 to 600 (eff. L410 UVP-E; E9; E20)
Page
1501 to 1600 (eff. L410 UVP-E)
Page
2501 to 2600 (eff. L410 UVP-E9)
Page
3501 to 3600 (eff. L410 UVP-E20)
Page
601 to 700 (eff. L410 UVP-E; E9; E20)
Page
1601 to 1700 (eff. L410 UVP-E)
Page
2601 to 2700 (eff. L410 UVP-E9)
Page
3601 to 3700 (eff. L410 UVP-E20)
000.01.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL CLEANING / PAINTING
APPROVED REPAIRS
Page
701 to 800 (eff. L410 UVP-E; E9; E20)
Page
1701 to 1800 (eff. L410 UVP-E)
Page
2701 to 2800 (eff. L410 UVP-E9)
Page
3701 to 3800 (eff. L410 UVP-E20)
Page
801 to 900 (eff. L410 UVP-E; E9; E20)
Page
1801 to 1900 (eff. L410 UVP-E)
Page
2801 to 2900 (eff. L410 UVP-E9)
Page
3801 to 3900 (eff. L410 UVP-E20)
For example a trouble shooting procedure concerning a particular nose gear defect is to be located in the section 32-20 and page 101 with which the Trouble Shooting topic begins.
4. Figures Numbering of figures is consistently related to the page number block for each topic. For example Fig. 1 ( or 1001, 2001, 3001) will be the first figure in DESCRIPTION AND OPERATION, Fig. 301 (or 1301, 2301, 3301) will be the first figure in SERVICING, Fig. 401 ( or 1401, 2401, 3401) will be the first figure in REMOVAL/ INSTALLATION, etc.
5. Revisions Revisions in the MM are carried out by means of replacement pages that are always accompanied by a new list of effective pages of the corresponding chapter. The revision (the replacement pages) are sent to the holder of the MM in the form of Documentation Bulletins (a list of issued bulletins is filed after the title page of Book 1). The holder of the MM is obliged to make sure that the pages in his manual correspond to the list of effective pages that is filed on the beginning of each chapter. Pages that do not correspond to the list must be discarded. Revisions are identified by a thick vertical line along the margin of the page, and a revised or new page is marked with the date of issue. If a portion of the text is shifted to the following page due to an extension of the changed text, only that position of the text that was changed is identified with the vertical line (the original text is not marked even through shifted). If there is no other change except for shifting of the text, a letter R is added to the date of issue. Before the issue of replacement sheets the holder of the MM may be informed about the revisions being prepared by a TEMPORARY REVISION. The temporary revisions are filed by the holder of the MM face the corresponding Manual sheet. After the receipt and filing of the new sheet, the original sheet with its TEMPORARY REVISIONS is to be deleted from the Manual.
EFFECTIVITY: ALL
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MAINTENANCE MANUAL The holder of the MM having received a revision and made the corresponding change to the MM, will enter the revision number in the Record of revisions together with the date when the revision was inserted, and the signature of the person having made the change. The Record of Revisions is located in the introductory section after the Title page of each chapter. NOTE:
Chapter 90 is an exception, the record of revisions being located behind the Title Page in the introductory section, and also behind the Title Page of each Supplement.
6. Modifications The modifications (differences from the basic aircraft version), are described in supplements to the relevant chapters of the MM - see chapter 90.
7. Limitation of information effectivity Limitation of information effectivity (indication of the aircraft type) is identified in the effectivity block as follows: -
If a page applies to all aircraft types (i.e. L410 UVP-E, L410 UVP-E9, L410 UVP-E20) the word “ALL” is indicated in the effectivity block
-
If a page applies to L 410 UVP-E aircrafts, “L 410 UVP-E” is indicated in the effectivity block.
-
If a page applies to L 410 UVPE-E9 aircrafts, “L 410 UVP-E9” is indicated in the effectivity block.
-
If a page applies to L 410 UVP-E20 aircrafts, “L 410 UVP-E20” is indicated in the effectivity block.
Any modification of any aircraft type is described in a supplement to the MM - as indicated in para 6 above. In the information which is explained on a page is effective for certain aircrafts only (e.g. certain series or certain serial numbers), these are specified behind the word EFFECTIVITY (with the indication of aircraft type). For example: applies to EFFECTIVITY:
L410 UVP-E
ALL
L410 UVP-E9 L410 UVP-E20
EFFECTIVITY: ALL (S/ No.2202)
applies to EFFECTIVITY: L410 UVP-E
L410 UVP-E
EFFECTIVITY: L410 UVP-E (S/No.2832)
EFFECTIVITY: ALL
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MAINTENANCE MANUAL applies to EFFECTIVITY:
L410 UVP-E9
L410 UVP-E9
EFFECTIVITY: L410 UVP-E9 (S/No.1324)
applies to EFFECTIVITY:
L410 UVP-E20
L410 UVP-E20
EFFECTIVITY: L410 UVP-E20 (S/No.2711)
8. Replacement of instruments and units Instruments and units which have been found out as unfit for further operation are allowed to be replaced with instruments (units) of the same type. Instruments and units to be installed into aircraft must be tested before the installation.
EFFECTIVITY: ALL
000.01.00 Page: 5 Nov 1/11
MAINTENANCE MANUAL
9. Abbreviations AFM
- Airplane Flight Manual
MM
- Maintenance Manual
WM
- Wiring Manual
MS
- Maintenance Schedule
IM
- Inspection Manual
LH
- Left-Hand (Port)
RH
- Right-Hand (Starboard)
Rud
- Rudder
Elev
- Elevator
L/G
- Landing Gear
ng
- gas generator speed
np
- propeller speed
V (IAS)
- indicated airspeed
TQ (TRQ)
- torque
ITT
- Interstage Turbine Temperature
Λ ITT / ΛT
- temperature growth speed between turbines
GT
- Gas Generator
TCL
- Throttle Control Lever
PCL
- Propeller Control Lever
ECL
- Engine Control Lever
AP
- Autopilot
IELU
- Integrated Engine Limiter Unit
VT (FT)
- Free Turbine
PVD
- Pitot Static System
EFFECTIVITY: ALL
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MAINTENANCE MANUAL
SURVEY OF PRIMARY AND SECONDARY AIRCRAFT STRUCTURES DESCRIPTION AND OPERATION 1. General Survey of primary airframe structures: •
electrical power (see Chapter 24)
•
fire protection (see Chapter 26)
•
flight controls (see Chapter 27)
•
fuel (see Chapter 28)
•
hydraulic power (see Chapter 29)
•
ice and rain protection (see Chapter 30)
•
indicating/recording system (see Chapter 31)
•
landing gear (see Chapter 32)
•
navigation and Pitot/static (see Chapter 34)
•
doors (see Chapter 52)
•
fuselage (see Chapter 53)
•
nacelles (see Chapter 54)
•
stabilizers (see Chapter 55)
•
wings (see Chapter 57)
•
propellers (see Chapter 61)
•
power plant (see Chapter 71)
•
engine controls (see Chapter 76)
•
engine indicating (see Chapter 77)
•
oil (see Chapter 79)
•
starting (see Chapter 80)
•
water injection (see Chapter 82)
The rest of the aircraft parts can be classified as secondary structures.
EFFECTIVITY: ALL
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CHAPTER
TIME LIMITS/ MAINTENANCE CHECKS
MAINTENANCE MANUAL
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L410UVP-E/170d
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TIME LIMITS General
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TIME LIMITS
1. General For the EASA certified airplanes, the AIRWORTHINESS LIMITATIONS SECTION is contained in the Maintenance Schedule (MS), Doc. No. – Do-L410-1222.1, Do-L410-1225.2, Do-L410-1223.2, which are separate documents. The Airworthiness Limitations are included in the following chapters: •
Chapter 2 - AIRWORTHINESS LIMITATION SECTION of Maintenance Schedule (MS)
•
Chapter 9.7 - OPERATION OF INSTRUMENTS AND MAJOR COMPONENTS of Maintenance Schedule (MS)
For the FAA validated L 410 UVP-E20 and L 410 UVP-E20 CARGO airplanes, the AIRWORTHINESS LIMITATIONS SECTION is contained in the Maintenance Schedule (MS), Doc. No. Do-L410-1223.2-FAA, which is the separate document. The Airworthiness Limitations are included in the following chapters: •
Chapter 2 - AIRWORTHINESS LIMITATION SECTION of Maintenance Schedule (MS)
•
Chapter 9.6 - OPERATION OF INSTRUMENTS AND MAJOR COMPONENTS of Maintenance Schedule (MS)
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005.10.00 Page: 1 Apr 15/15
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Appropriate documents for the engine and the propeller are as follows: GE WALTER Manuals: •
Maintenance Manual turboprop engine models WALTER M 601 E, WALTER M 601-E21 P/N 0982055;
The AVIA Propeller Manuals: •
Document No. E-1500 - “Operation and installation manual reversible hydraulically controlled variable pitch propellers (constant speed) V510( ) “.
•
Operator's Installation and Maintenance Manual V510 Propeller P/N 068-8912.7
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005.10.00 Page: 2 Apr 5/13
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SCHEDULED MAINTENANCE CHECK DESCRIPTION AND OPERATION 1. General The content of this Section such as mandatory replacement time, structural inspection interval, and related structural inspection interval, and related structural inspection procedure required for type certification is included in a separate manual - Maintenance Schedule (MS) Document No. – Do-L410-1222.1, Do-L410-1225.2, Do-L410-1223.2, Do-L410-1223.2-FAA.
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MAINTENANCE MANUAL
CHAPTER 6 DIMENSION AND AREAS CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
CONVERSION TABLES Description and Operation Conversion of mm to inch Conversion of inch to mm Conversion of m to foot Conversion of foot to m Conversion of sq. cm of sq. inch Conversion of sq. inch to sq. cm Conversion of sq. dm to sq. foot Conversion of sq. foot to sq. dm Conversion of litters to gallons Conversion of gallons to litters Conversion of kg to pound Conversion of pound to kg Conversion of strength units (kp to lbf) Conversion of strength units (lbf to kp) Conversion of pressure units (N/sq. cm to psi) Conversion of pressure units (psi to N/sq. cm) Conversion of pressure units (kp/ sq. cm to psi) Conversion of pressure units (psi to kp/sq. cm) Conversion of inch fraction to mm Temperature conversion from Celsius to Fahrenheit
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DIMENSIONS AND AREAS Description and Operation Main dimensions Wing Stabilizer and elevator Fin and rudder
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AIRCRAFT ZONING Description and Operation General
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ACCESS DOORS AND PANELS Description and Operation General Method of identification
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CONVERSION TABLES DESCRIPTION AND OPERATION 1. Conversion of mm to inch 1 mm = 0.03937 in mm
in
mm
in
mm
in
1
0.03937
35
1.37795
69
2.71653
2
0.07874
36
1.41732
70
2.75590
3
0.11811
37
1.45669
71
2.79527
4
0.15748
38
1.49606
72
2.83464
5
0.19685
39
1.53543
73
2.87401
6
0.23622
40
1.57480
74
2.91338
7
0.27559
41
1.61417
75
2.95275
8
0.31496
42
1.65354
76
2.99212
9
0.35433
43
1.69291
77
3.03149
10
0.39370
44
1.73228
78
3.07086
11
0.43307
45
1.77165
79
3.11023
12
0.47244
46
1.81102
80
3.14960
13
0.51181
47
1.85039
81
3.18897
14
0.55118
48
1.88976
82
3.22834
15
0.59055
49
1.92913
83
3.26771
16
0.62992
50
1.96850
84
3.30708
17
0.66929
51
2.00787
85
3.34645
18
0.70866
52
2.04724
86
3.38582
19
0.74803
53
2.08661
87
3.42519
20
0.78740
54
2.12598
88
3.46456
21
0.82677
55
2.16535
89
3.50393
22
0.86614
56
2.20472
90
3.54330
23
0.90551
57
2.24409
91
3.58267
24
0.94488
58
2.28346
92
3.62204
25
0.98425
59
2.32283
93
3.66141
26
1.02362
60
2.36220
94
3.70078
27
1.06299
61
2.40157
95
3.74015
28
1.10236
62
2.44094
96
3.77952
29
1.14173
63
2.48031
97
3.81889
30
1.18110
64
2.51968
98
3.85826
31
1.22047
65
2.55905
99
3.89763
32
1.25984
66
2.59842
100
3.93700
33
1.29921
67
2.63779
34
1.33858
68
2.67716
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MAINTENANCE MANUAL
2. Conversion of inch to mm 1 in = 25.4 mm in
mm
in
mm
in
mm
1
25.40000
35
889.00000
69
1752.60000
2
50.80000
36
914.40000
70
1778.00000
3
76.20000
37
939.80000
71
1803.40000
4
101.60000
38
965.20000
72
1828.80000
5
127.00000
39
990.60000
73
1854.20000
6
152.40000
40
1016.00000
74
1879.60000
7
177.80000
41
1041.40000
75
1905.00000
8
203.20000
42
1066.80000
76
1930.40000
9
228.60000
43
1092.20000
77
1955.80000
10
254.00000
44
1117.60000
78
1981.20000
11
279.40000
45
1143.00000
79
2006.60000
12
304.80000
46
1168.40000
80
2032.00000
13
330.20000
47
1193.80000
81
2057.40000
14
355.60000
48
1219.20000
82
2082.80000
15
381.00000
49
1244.60000
83
2108.20000
16
406.40000
50
1270.00000
84
2133.60000
17
431.80000
51
1295.40000
85
2159.00000
18
457.20000
52
1320.80000
86
2184.40000
19
482.60000
53
1346.20000
87
2209.80000
20
508.00000
54
1371.60000
88
2235.20000
21
533.40000
55
1397.00000
89
2260.60000
22
558.80000
56
1422.40000
90
2286.00000
23
584.20000
57
1447.80000
91
2311.40000
24
609.60000
58
1473.20000
92
2336.80000
25
635.00000
59
1498.60000
93
2362.20000
26
660.40000
60
1524.00000
94
2387.60000
27
685.80000
61
1549.40000
95
2413.00000
28
711.20000
62
1574.80000
96
2438.40000
29
736.60000
63
1600.20000
9T
2463.80000
30
762.00000
64
1625.60000
98
2489.20000
31
787.40000
65
1651.00000
99
2514.60000
32
812.80000
66
1676.40000
100
2540.000000
33
838.20000
67
1701.80000
34
863.60000
68
1727.20000
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3. Conversion of m to foot 1 m = 3.28084 foot m
ft
m
ft
m
ft
1
3.280840
35
114.829400
69
226.377960
2
6.561680
36
118.110240
70
229.658800
3
9.842520
37
121.391080
71
232.939640
4
13.123360
38
124.671920
72
236.220480
5
16.404200
39
127.952760
73
239.501320
6
19.685040
40
131.233600
74
242.782160
7
22.965880
41
134.514440
75
246.063000
8
26.246720
42
137.795280
76
249.343840
9
29.527560
43
141.076120
77
252.624680
10
32.808400
44
144.356960
78
255.905520
11
36.089240
45
147.637800
79
259.186360
12
39.370080
46
150.918640
80
262.467200
13
42.650920
47
154.199480
81
265.748040
14
45.931760
48
157.480320
82
269.028880
15
49.212600
49
160.761160
83
272.309720
16
52.493440
50
164.042000
84
275.590560
17
55.774280
51
167.322840
85
278.871400
18
59.055120
52
170.603680
86
282.152240
19
62.335960
53
173.884520
87
285.433080
20
65.616800
54
177.165360
88
288.713920
21
68.897640
55
180.446200
89
291.994760
22
72.178480
56
183.727040
90
295.275600
23
75.459320
57
187.007880
91
298.556440
24
78.740160
58
190.288720
92
301.837280
25
82.021000
59
193.569560
93
305.118120
26
85.301840
60
196.850400
94
308.398960
27
88.582680
61
200.131240
95
311.679800
28
91.863520
62
203.412080
96
314.960640
29
95.144360
63
206.692920
97
318.241480
30
98.425200
64
209.973760
98
321.522320
31
101.706040
65
213.254600
99
324.803160
32
104.986880
66
216.535440
100
328.084000
33
108.267720
67
219.816280
34
111.548560
68
223.097120
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4. Conversion of foot to m 1 ft = 0.3048 m ft
m
ft
m
ft
m
1
0.304800
35
10.668000
69
21.031200
2
0.609600
36
10.972800
70
21.336000
3
0.914400
37
11.277600
71
21.640800
4
1.219200
38
11.582400
72
21.945600
5
1.524000
39
11.887200
73
22.250400
6
1.828800
40
12.192000
74
22.555200
7
2.133600
41
12.496800
75
22.860000
8
2.438400
42
12.801600
76
23.164800
9
2.743200
43
13.106400
77
23.469600
10
3.048000
44
13.411200
78
23.774400
11
3.352800
45
13.716000
79
24.079200
12
3.657600
46
14.020800
80
24.384000
13
3.962400
47
14.325600
81
24.688800
14
4.267200
48
14.630400
82
24.993600
15
4.572000
49
14.935200
83
25.298400
16
4.876800
50
15.240000
84
25.603200
17
5.181600
51
15.544800
85
25.908000
18
5.486400
52
15.849600
86
26.212800
19
5.791200
53
16.154400
87
26.517600
20
6.096000
54
16.459200
88
26.822400
21
6.400800
55
16.764000
89
27.127200
22
6.705600
56
17.068800
90
27.432000
23
7.010400
57
17.373600
91
27.736800
24
7.315200
58
17.678400
92
28.041600
25
7.620000
59
17.983200
93
28.346400
26
7.924800
60
18.288000
94
28.651200
27
8.229600
61
18.592800
95
28.956000
28
8.534400
62
18.897600
96
29.260800
29
8.839200
63
19.202400
97
29.565600
30
9.144000
64
19.507200
98
29.870400
31
9.448800
65
19.812000
99
30.175200
32
9.753600
66
20.116800
100
30.4800000
33
10.058400
67
20.421600
34
10.363200
68
20.726400
EFFECTIVITY: ALL
006.00.01 Page: 4 Nov 1/11
MAINTENANCE MANUAL
5. Conversion of sq.cm of sq.inch 1 cm = 0.3937 in sq.cm
sq.in
sq.cm
sq.in
sq.cm
sq.in
1
0.155000
35
5.424989
69
10.694979
2
0.309999
36
5.579989
70
10.849978
3
0.464999
37
5.734989
71
11.004978
4
0.619999
38
5.889988
72
11.159978
5
0.774998
39
6.044988
73
11.314977
6
0.929998
40
6.199988
74
11.469977
7
1.084998
41
6.354987
75
11.624977
8
1.239998
42
6.509987
76
11.779976
9
1.394997
43
6.664987
77
11.934976
10
1.549997
44
6.819986
78
12.089976
11
1.704997
45
6.974986
79
12.244976
12
1.859996
46
7.129986
80
12.399975
13
2.014996
47
7.284985
81
12.554975
14
2.169996
48
7.439985
82
12.709975
15
2.324995
49
7.594985
83
12.864974
16
2.479995
50
7.749985
84
13.019974
17
2.634995
51
7.904984
85
13.174974
18
2.789994
52
8.059984
86
13.329973
19
2.944994
53
8.214984
87
13.484973
20
3.099994
54
8.369983
88
13.639973
21
3.254993
55
8.524983
89
13.794972
22
3.409993
56
8.679983
90
13.949972
23
3.564993
57
8.834982
91
14.104972
24
3.719993
58
8.989982
92
14.259971
25
3.874992
59
9.144982
93
14.414971
26
4.029992
60
9.299981
94
14.569971
27
4.184992
61
9.454981
95
14.724971
28
4.339991
62
9.609981
96
14.879970
29
4.494991
63
9.764980
97
15.034970
30
4.649991
64
9.919980
98
15.189970
31
4.804990
65
10.074980
99
15.344969
32
4.959990
66
10.229980
100
15.499969
33
5.114990
67
10.384979
34
5.269989
68
10.539979
EFFECTIVITY: ALL
006.00.01 Page: 5 Nov 1/11
MAINTENANCE MANUAL
6. Conversion of sq.inch to sq.cm 1 in = 2.54 cm sq.in
sq.cm
sq.in
sq.cm
sq.in
sq.cm
1
6.451600
35
225.806000
69
445.160400
2
12.903200
36
232.257600
70
451.612000
3
19.354800
37
238.709200
71
458.063600
4
25.806400
38
245.160800
72
464.515200
5
32.258000
39
251.612400
73
470.966800
6
38.709600
40
258.064000
74
477.418400
7
45.161200
41
264.515600
75
483.870000
8
51.612800
42
270.967200
76
490.321600
9
58.064400
43
277.418800
77
496.773200
10
64.516000
44
283.870400
78
503.224800
11
70.967600
45
290.322000
79
509.676400
12
77.419200
46
296.773600
80
516.128000
13
83.870800
47
303.225200
81
522.579600
14
90.322400
48
309.676800
82
529.031200
15
96.774000
49
316.128400
83
535.482800
16
103.225600
50
322.580000
84
541.934400
17
109.677200
51
329.031600
85
548.386000
18
116.128800
52
335.483200
86
554.837600
19
122.580400
53
341.934800
87
561.289200
20
129.032000
54
348.386400
88
567.740800
21
135.483600
55
354.838000
89
574.192400
22
141.935200
56
361.289600
90
580.644000
23
148.386800
57
367.741200
91
587.095600
24
154.838400
58
374.192800
92
593.547200
25
161.290000
59
380.644400
93
599.998800
26
167.741600
60
387.096000
94
606.450400
27
174.193200
61
393.547600
95
612.902000
28
180.644800
62
399.999200
96
619.353600
29
187.096400
63
406.450800
97
625.805200
30
193.548000
64
412.902400
98
632.256800
31
199.999600
65
419.354000
99
638.708400
32
206.451200
66
425.805600
100
645.160000
33
212.902800
67
432.257200
34
219.354400
68
438.708800
EFFECTIVITY: ALL
006.00.01 Page: 6 Nov 1/11
MAINTENANCE MANUAL
7. Conversion of sq.dm to sq. foot 1 dm = 0.328084 ft sq.dm
sq.ft
sq.dm
sq.ft
sq.dm
sq.ft
1
0.107639
35
3.767369
69
7.427099
2
0.215278
36
3.875008
70
7.534738
3
0.322917
37
3.982647
71
7.642377
4
0.430556
38
4.090286
72
7.750016
5
0.538196
39
4.197925
73
7.857655
6
0.645835
40
4.305564
74
7.965294
7
0.753474
41
4.413204
75
8.072933
8
0.861113
42
4.520843
76
8.180572
9
0.968752
43
4.628482
77
8.288212
10
1.076391
44
4.736121
78
8.395851
11
1.184030
45
4.843760
79
8.503490
12
1.291669
46
4.951399
80
8.611129
13
1.399308
47
5.059038
81
8.718768
14
1.506948
48
5.166677
82
8.826407
15
1.614587
49
5.274316
83
8.934046
16
1.722226
50
5.381956
84
9.041685
17
1.829865
51
5.489595
85
9.149324
18
1.937504
52
5.597234
86
9.256964
19
2.045143
53
5.704873
87
9.364603
20
2.152782
54
5.812512
88
9.472242
21
2.260421
55
5.920151
89
9.579881
22
2.368060
56
6.027790
90
9.687520
23
2.475700
57
6.135429
91
9.795159
24
2.583339
58
6.243068
92
9.902798
25
2.690978
59
6.350708
93
10.010437
26
2.798617
60
6.458347
94
10.118076
27
2.906256
61
6.565986
95
10.225716
28
3.013895
62
6.673625
96
10.333355
29
3.121534
63
6.781264
97
10.440994
30
3.229173
64
6.888903
98
10.548633
31
3.336812
65
6.996542
99
10.656272
32
3.444452
66
7.104181
100
10.763911
33
3.552091
67
7.211820
34
3.659730
68
7.319460
EFFECTIVITY: ALL
006.00.01 Page: 7 Nov 1/11
MAINTENANCE MANUAL 8. Conversion of sq.foot to sq.dm 1 ft = 3.048 dm sq.ft
sq.dm
sq.ft
sq.dm
sq.ft
sq.dm
1
9.290304
35
325.160640
69
641.030976
2
18.580608
36
334.450944
70
650.321280
3
27.870912
37
343.741248
71
659.611584
4
37.161216
38
353.03!552
72
668.901888
5
46.451520
39
362.321856
73
678.192192
6
55.741824
40
371.612160
74
687.482496
7
65.032128
41
380.902464
75
696.772800
8
74.322432
42
390.192768
76
706.063104
9
83.612736
43
399.483072
77
715.353408
10
92.903040
44
408.773376
78
724.643712
11
102.193344
45
418.063680
79
733.934016
12
111.483648
46
427.353984
80
743.224320
13
120.773952
47
436.644288
81
752.514624
14
130.064256
48
445.934592
82
761.804928
15
139.354560
49
455.224896
83
771.095232
16
148.644864
50
464.515200
84
780.385536
17
157.935168
51
473.805504
85
789.675840
18
167.225472
52
483.095808
86
798.966144
19
176.515776
53
492.386112
87
808.256448
20
185.806080
54
501.676416
88
817.546752
21
195.096384
55
510.966720
89
826.837056
22
204.386688
56
520.257024
90
836.127360
23
213.676992
57
529.547328
91
845.417664
24
222.967296
58
538.837632
92
854.707968
25
232.257600
59
548.127936
93
863.998272
26
241.547904
60
557.418240
94
873.288576
27
250.838208
61
566.708544
95
882.578880
28
260.128512
62
575.998848
96
891.869184
29
269.418816
63
585.289152
97
901.159488
30
278.709120
64
594.579456
98
910.449792
31
287.999424
65
603.869760
99
919.740096
32
297.289728
66
613.160064
100
929.030400
33
306.580032
67
622.450368
34
315.870336
68
631.7406?2
EFFECTIVITY: ALL
006.00.01 Page: 8 Nov 1/11
MAINTENANCE MANUAL
9. Conversion of liters to gallons 1 l = 0.220 UK gall 1 l = 0.264 US gall l
UK gall
US gall
l
UK gall
US gall
l
UK gall
US gall
1
0.220
0.264
35
7.700
9.246
69
15.180
18.227
2
0.440
0.528
36
7.920
9.510
70
15.400
18.492
3
0.660
0.792
37
8.140
9.774
71
15.620
18.756
4
0.880
1.056
38
8.360
10.038
72
15.840
19.020
5
1.100
1.320
39
8.580
10.302
73
16.060
19.284
6
1.320
1.585
40
8.800
10.566
74
16.280
19.548
7
1.540
1.849
41
9.020
10.831
75
16.500
19.812
8
1.760
2.113
42
9.240
11.095
76
16.720
20.077
9
1.980
2.377
43
9.460
11.359
77
16.940
20.341
10
2.200
2.641
44
9.680
11.623
78
17.160
20.605
11
2.420
2.905
45
9.900
11.887
79
17.380
20.849
12
2.640
3.170
46
10.120
12.151
80
17.600
21.133
13
2.860
3.434
47
10.340
12.416
81
17.820
21.397
14
3.080
3.698
48
10.560
12.680
82
18.040
21.662
15
3.300
3.962
49
10.780
12.944
83
18.260
21.926
16
3.520
4.226
50
11.000
13.208
84
18.480
22.190
17
3.740
4.490
51
11.220
13.472
85
18.700
22.454
18
3.960
4.755
52
11.440
13.736
86
18.920
22.718
19
4.180
5.019
53
11.660
14.001
87
19.140
22.982
20
4.400
5.283
54
11.880
14.265
88
19.360
23.247
21
4.620
5.547
55
12.100
14.529
89
19.580
23.511
22
4.840
5.811
56
12.320
14.793
90
19.800
23.775
23
5.060
6.075
57
12.540
15.057
91
20.020
24.039
24
5.280
6.340
58
12.760
15.321
92
20.240
24.303
25
5.500
6.604
59
12.980
15.586
93
20.460
24.568
26
5.720
6.868
60
13.200
15.850
94
20.680
24.832
27
5.940
7.132
61
13.420
16.114
95
20.900
25.096
28
6.160
7.396
62
13.640
16.378
96
21.120
25.360
29
6.380
7.660
63
13.860
16.642
97
21.340
25.624
30
6.600
7.925
64
14.080
16.907
98
21.560
25.888
31
6.820
8.189
65
14.300
17.171
99
21.780
26.153
32
7.040
8.453
66
14.520
17.435
100
22.000
26.417
33
7.260
8.717
67
14.740
17.699
34
7.480
8.981
68
14.960
17.963
EFFECTIVITY: ALL
006.00.01 Page: 9 Nov 1/11
MAINTENANCE MANUAL 10. Conversion of gallons to liters 1 U.S. gall = 3.785 l U.S. gall
l
U.S. gall
l
U.S. gall
l
1
3.785
35
132.489
69
261.193
2
7.570
36
136.274
70
264.978
3
11.356
37
140.060
71
268.764
4
15.141
38
143.845
72
272.549
5
18.927
39
147.631
73
276.335
6
22.712
40
151.416
74
280.120
7
26.497
41
155.201
75
283.905
8
30.283
42
158.987
76
287.691
9
34.068
43
162.772
77
291.476
10
37.854
44
166.558
78
295.262
11
41.639
45
170.343
79
299.047
12
45.424
46
174.128
80
302.832
13
49.210
47
177.914
81
306.618
14
52.995
48
181.699
82
310.403
15
56.781
49
185.485
83
314.189
16
60.566
50
189.270
84
317.974
17
64.352
51
193.056
85
321.760
18
68.137
52
196.841
86
325.545
19
71.922
53
200.626
87
329.330
20
75.708
54
204.412
88
333.116
21
79.493
55
208.197
89
336.901
22
83.279
56
211.983
90
340.687
23
87.064
57
215.768
91
344.472
24
90.849
58
219.553
92
348.257
25
94.635
59
223.339
93
352.043
26
98.420
60
227.124
94
355.828
27
102.206
61
230.910
95
359.614
28
105.991
62
234.695
96
363.399
29
109.776
63
238.408
97
367.184
30
113.562
64
242.266
98
370.970
31
117.347
65
246.051
99
374.755
32
121.133
66
249.837
100
378.541
33
124.918
67
253.622
34
128.704
68
257.408
EFFECTIVITY: ALL
006.00.01 Page: 10 Nov 1/11
MAINTENANCE MANUAL 1 U.K. gall = 4.546 l U.K. gall
l
U.K. gall
l
U.K. gall
l
1
4.546
35
159.110
69
313.674
2
9.092
36
163.656
70
318.220
3
13.638
37
168.202
71
322.766
4
18.184
38
172.748
72
327.312
5
22.730
39
177.294
73
331.858
6
27.276
40
181.840
74
336.404
7
31.822
41
186.386
75
340.950
8
36.368
42
190.932
76
345.496
9
40.914
43
195.478
77
350.042
10
45.460
44
200.024
78
354.588
11
50.006
45
204.570
79
359.134
12
54.552
46
209.116
80
363.680
13
59.098
47
213.662
81
368.226
14
63.644
48
218.208
82
372.772
15
68.190
49
222.754
83
377.318
16
72.736
50
227.300
84
381.864
17
77.282
51
231.846
85
386.410
18
81.828
52
236.392
86
390.956
19
86.374
53
240.938
87
395.502
20
90.920
54
245.484
88
400.048
21
95.466
55
250.030
89
404.594
22
100.012
56
254.576
90
409.140
23
104.558
57
259.122
91
413.686
24
109.104
58
263.668
92
418.232
25
113.650
59
268.214
93
422.778
26
118.196
60
272.760
94
427.324
27
122.742
61
277.306
95
431.870
28
127.288
62
281.852
96
436.416
29
131.834
63
286.398
97
440.962
30
136.380
64
290.944
98
445.508
31
140.926
65
295.490
99
450.054
32
145.472
66
300.036
100
454.600
33
150.018
67
304.582
34
154.564
68
309.128
EFFECTIVITY: ALL
006.00.01 Page: 11 Nov 1/11
MAINTENANCE MANUAL
11. Conversion of kg to pound 1 kg = 2.2046223 lb kg
lb
kg
lb
kg
lb
1
2.2046223
35
77.1617805
69
152.1189387
2
4.4092446
36
79.3664028
70
154.3235610
3
6.6138669
37
81.5710251
71
156.5281833
4
8.8184892
38
83.7756474
72
158.7328056
5
11.0231115
39
85.9802697
73
160.9374279
6
13.2277338
40
88.1848920
74
163.1420502
7
15.4323561
41
90.3895143
75
165.3466725
8
17.6369784
42
92.5941366
76
167.5512948
9
19.8416007
43
94.7987589
77
169.7559171
10
22.0462230
44
97.0033812
78
171.9605394
11
24.2508453
45
99.2080035
79
174.1651617
12
26.4554676
46
101.4126258
80
176.3697840
13
28.6600899
47
103.6172481
81
178.5744063
14
30.8647122
48
105.8218704
82
180.7790286
15
33.0693345
49
108.0264927
83
182.9836509
16
35.2739568
50
110.2311150
84
185.1882732
17
37.4785791
51
112.4357373
85
187.3928955
18
39.6832014
52
114.6403596
86
189.5975178
19
41.8878237
53
116.8449819
87
191.8021401
20
44.0924460
54
119.0496042
88
194.0067624
21
46.2970683
55
121.2542265
89
196.2113847
22
48.5016906
56
123.4588488
90
198.4160070
23
50.7063129
57
125.6634711
91
200.6206293
24
52.9109352
58
127.8680934
92
202.8252516
25
55.1155575
59
130.0727157
93
205.0298739
26
57.3201798
60
132.2773380
94
207.2344962
27
59.5248021
61
134.4819603
95
209.4391185
28
61.7294244
62
136.6865826
96
211.6437408
29
63.9340467
63
138.8912049
97
213.8483631
30
66.1386690
64
141.0958272
98
216.0529854
31
68.3432913
65
143.3004495
99
218.2576077
32
70.5479136
66
145.50507181
100
220.4622300
33
72.7525359
67
147.7096941
34
74.9571582
68
149.9143164
EFFECTIVITY: ALL
006.00.01 Page: 12 Nov 1/11
MAINTENANCE MANUAL
12. Conversion of pound to kg 1 lb = 0.453592 kg lb
kg
lb
kg
lb
kg
1
0.4535920
35
15.8757200
69
31.2978480
2
0.9071840
36
16.3293120
70
31.7514400
3
1.3607760
37
16.7829040
71
32.2050320
4
1.8143680
38
17.2364960
72
32.6586240
5
2.2679600
39
17.6900880
73
33.1122160
6
2.7215520
40
18.1436800
74
33.5658080
7
3.1751440
41
18.5972720
75
34.0194000
8
3.6287360
42
19.0508640
76
34.4729920
9
4.0823280
43
19.5044560
77
34.9265840
10
4.5359200
44
19.9580480
78
35.3801760
11
4.9895120
45
20.4116400
79
35.8337680
12
5.4431040
46
20.8652320
80
36.2873600
13
5.8966960
47
21.3188240
81
36.7409520
14
6.3502880
48
21.7724160
82
37.1945440
15
6.8038800
49
22.2260080
83
37.6481360
16
7.2574720
50
22.6796000
84
38.1017280
17
7.7110640
51
23.1331920
85
38.5553200
18
8.1646560
52
23.5867840
86
39.0089120
19
8.6182480
53
24.0403760
87
39.4625040
20
9.0718400
54
24.4939680
88
39.9160960
21
9.5254320
55
24.9475600
89
40.3696880
22
9.9790240
56
25.4011520
90
40.8232800
23
10.4326160
57
25.8547440
91
41.2768720
24
10.8862080
58
26.3083360
92
41.7304640
25
11.3398000
59
26.7619280
93
42.1840560
26
11.7933920
60
27.2155200
94
42.6376480
27
12.2469840
61
27.6691120
95
43.0912400
28
12.7005760
62
28.1227040
96
43.5448320
29
13.1541680
63
28.5762960
97
43.9984240
30
13.6077600
64
29.0298880
98
44.4520160
31
14.0613520
65
29.4834800
99
44.9056080
32
14.5149440
66
29.9370720
100
45.3592000
33
14.9685360
67
30.3906640
34
15.4221280
68
30.8442560
EFFECTIVITY: ALL
006.00.01 Page: 13 Nov 1/11
MAINTENANCE MANUAL 13. Conversion of strength units (kp to lbf) 1 kp = 2.2046223 lbf kp
lbf
kp
lbf
kp
lbf
1
2.2046223
35
77.1617805
69
152.1189387
2
4.4092446
36
79.3664028
70
154.3235610
3
6.6138669
37
81.5710251
71
156.5281833
4
8.8184892
38
83.7756474
72
158.7328056
5
11.0231115
39
85.9802697
73
160.9374279
6
13.2277338
40
88.1848920
74
163.1420502
7
15.4323561
41
90.3895143
75
165.3466725
8
17.6369784
42
92.5941366
76
167.5512948
9
19.8416007
43
94.7987589
77
169.7559171
10
22.0462230
44
97.0033812
78
171.9605394
11
24.2508453
45
99.2080035
79
174.1651617
12
26.4554676
46
101.4126258
80
176.3697840
13
28.6600899
47
103.6172481
81
178.5744063
14
30.8647122
48
105.8218704
82
180.7790286
15
33.0693345
49
108.0264927
83
182.9836509
16
35.2739568
50
110.2311150
84
185.1882732
17
37.4785791
51
112.4357373
85
187.3928955
18
39.6832014
52
114.6403596
86
189.5975178
19
41.8878237
53
116.8449819
87
191.8021401
20
44.0924460
54
119.0496042
88
194.0067624
21
46.2970683
55
121.2542265
89
196.2113847
22
48.5016906
56
123.4588488
90
198.4160070
23
50.7063129
57
125.6634711
91
200.6206293
24
52.9109352
58
127.8680934
92
202.8252516
25
55.1155575
59
130.0727157
93
205.0298739
26
57.3201798
60
132.2773380
94
207.2344962
27
59.5248021
61
134.4819603
95
209.4391185
28
61.7294244
62
136.6865826
96
211.6437408
29
63.9340467
63
138.8912049
97
213.8483631
30
66.1386690
64
141.0958272
98
216.0529854
31
68.3432913
65
143.3004495
99
218.2576077
32
70.5479136
66
145.5050718
100
220.4622300
33
72.7525359
67
147.7096941
34
74.9571582
68
149.9143164
EFFECTIVITY: ALL
006.00.01 Page: 14 Nov 1/11
MAINTENANCE MANUAL
14. Conversion of strength units (lbf to kp) 1 lbf = 0.453592 kp lbf
kp
lbf
kp
lbf
Kp
1
0.4535920
35
15.8757200
69
31.2978480
2
0.9071840
36
16.3293120
70
31.7514400
3
1.3607760
37
16.7829040
71
32.2050320
4
1.8143680
38
17.2364960
72
32.6586240
5
2.2679600
39
17.6900880
73
33.1122160
6
2.7215520
40
18.1436800
74
33.5658080
7
3.1751440
41
18.5972720
75
34.0194000
8
3.6287360
42
19.0508640
76
34.4729920
9
4.0823280
43
19.5044560
77
34.9265840
10
4.5359200
44
19.9580480
78
35.3801760
11
4.9895120
45
20.4116400
79
35.8337680
12
5.4431040
46
20.8652320
80
36.2873600
13
5.8966960
47
21.3188240
81
36.7409520
14
6.3502880
48
21.7724160
82
37.1945440
15
6.8038800
49
22.2260080
83
37.6481360
16
7.2574720
50
22.6796000
84
38.1017280
17
7.7110640
51
23.1331920
85
38.5553200
18
8.1646560
52
23.5867840
86
39.0089120
19
8.6182480
53
24.0403760
87
39.4625040
20
9.0718400
54
24.4939680
88
39.9160960
21
9.5254320
55
24.9475600
89
40.3696880
22
9.9790240
56
25.4011520
90
40.8232800
23
10.4326160
57
25.8547440
91
41.2768720
24
10.8862080
58
26.3083360
92
41.7304640
25
11.3398000
59
26.7619280
93
42.1840560
26
11.7933920
60
27.2155200
94
42.6376480
27
12.2469840
61
27.6691120
95
43.0912400
28
12.7005760
62
28.1227040
96
43.5448320
29
13.1541680
63
28.5762960
97
43.9984240
30
13.6077600
64
29.0298880
98
44.4520160
31
14.0613520
65
29.4834800
99
44.9056080
32
14.5149440
66
29.9370720
100
45.3592000
33
14.9685360
67
30.3906640
34
15.4221280
68
30.8442560
EFFECTIVITY: ALL
006.00.01 Page: 15 Nov 1/11
MAINTENANCE MANUAL 15. Conversion of pressure units (N/sq.cm to psi) 1 N/sq.cm = 1.450 psi N/sq.cm
psi
N/sq.cm
psi
N/sq.cm
psi
1
1.450
35
50.763
69
100.076
2
2.900
36
52.213
70
101.526
3
4.351
37
53.663
71
102.976
4
5.801
38
55.114
72
104.427
5
7.251
39
56.564
73
105.877
6
8.702
40
58.015
74
107.327
7
10.152
41
59.465
75
108.778
8
11.603
42
60.915
76
110.228
9
13.053
43
62.366
77
111.679
10
14.503
44
63.816
78
113.129
11
15.954
45
65.266
79
114.579
12
17.404
46
66.717
80
116.030
13
18.854
47
68.167
81
117.480
14
20.305
48
69.618
82
118.930
15
21.755
49
71.068
83
120.381
16
23.206
50
72.518
84
121.831
17
24.656
51
73.969
85
123.282
18
26.106
52
75.419
86
124.732
19
27.557
53
76.870
87
126.182
20
29.007
54
78.320
88
127.633
21
30.457
55
79.770
89
129.083
22
31.908
56
81.221
90
130.533
23
33.358
57
82.671
91
131.984
24
34.809
58
84.121
92
133.434
25
36.259
59
85.572
93
134.885
26
37.709
60
87.022
94
136.335
27
39.160
61
88.473
95
137.785
28
40.610
62
89.923
96
139.236
29
42.060
63
91.373
97
140.686
30
43.511
64
92.824
98
142.136
31
44.961
65
94.274
99
143.587
32
46.412
66
95.724
100
145.037
33
47.862
67
97.175
34
49.312
68
98.625
EFFECTIVITY: ALL
006.00.01 Page: 16 Nov 1/11
MAINTENANCE MANUAL
16. Conversion of pressure units (psi to N/sq.cm) 1 psi = 0.689 N/sq.cm psi
N/sq.cm
psi
N/sq.cm
psi
N/sq.cm
1
0.689
35
24.115
69
47.541
2
1.378
36
24.804
70
48.230
3
2.067
37
25.493
71
48.919
4
2.756
38
26.182
72
49.608
5
3.445
39
26.871
73
50.297
6
4.134
40
27.560
74
50.986
7
4.823
41
28.249
75
51.675
8
5.512
42
28.938
76
52.364
9
6.201
43
29.627
77
53.053
10
6.890
44
3Q.316
78
53.742
11
7.579
45
31.005
79
54.431
12
8.268
46
31.694
80
55.120
13
8.957
47
32.383
81
55.809
14
9.646
48
33.072
82
56.498
15
10.335
49
33.761
83
57.187
16
11.024
50
34.450
84
57.876
17
11.713
51
35.139
85
58.565
18
12.402
52
35.828
86
59.254
19
13.091
53
36.517
87
59.943
20
13.780
54
37.206
88
60.632
21
14.469
55
37.895
89
61.321
22
15.158
56
38.584
90
62.010
23
15.847
57
39.273
91
62.699
24
16.536
58
39.962
92
63.388
25
17.225
59
40.651
93
64.077
26
17.914
60
41.340
94
64.766
27
18.603
61
42.029
95
65.455
28
19.292
62
42.718
96
66.144
29
19.981
63
43.407
97
66.833
30
20.670
64
44.096
98
67.522
31
21.359
65
44.785
99
68.211
32
22.048
66
45.474
100
68.900
33
22.737
67
46.163
34
23.426
68
46.852
EFFECTIVITY: ALL
006.00.01 Page: 17 Nov 1/11
MAINTENANCE MANUAL 17. Conversion of pressure units (kp/sq.cm to psi) 1 kp/sq.cm = 14.503 psi kp/sq.cm
psi
kp/sq.cm
psi
kp/sq.cm
psi
1
14.503
35
507.632
69
1.000.760
2
29.007
36
522.135
70
1.015.264
3
43.511
37
536.639
71
1.029.767
4
58.015
38
551.143
72
1.044.271
5
72.518
39
565.647
73
1.058.775
6
87.022
40
58Q.150
74
1.073.279
7
101.526
41
594.654
75
1.087.783
8
116.030
42
609.158
76
1.102.286
9
130.533
43
623.662
77
1.116.790
10
145.037
44
638.166
78
1.131.294
11
159.541
45
652.669
79
1.145.798
22
174.045
46
667.173
80
1.160.301
13
188.549
47
681.677
81
1.174.805
14
203.052
48
696.181
82
1.189.309
15
217.556
49
710.684
83
1.203.813
16
232.060
50
725.188
84
1.218.317
17
246.564
51
739.692
85
1.232.820
18
261.067
52
754.196
86
1.247.324
19
275.571
53
768.700
87
1.261.828
20
290.075
54
783.203
88
1.276.332
21
304.579
55
797.707
89
1.290.835
22
319.083
56
812.211
90
1.305.339
23
333.586
57
826.715
91
1.319.843
24
348.090
58
841.218
92
1.334.347
25
362.594
59
855.722
93
1.348.850
26
377.098
60
870.226
94
1.363.354
27
391.601
61
884.730
95
1.377.858
28
406.105
62
899.233
96
1.392.362
29
420.609
63
913.737
97
1.406.866
30
435.113
64
928.241
98
1.421.369
31
449.616
65
942.745
99
1.435.873
32
464.120
66
957.249
100
1.450.377
33
478.624
67
971.752
34
493.128
68
986.256
EFFECTIVITY: ALL
006.00.01 Page: 18 Nov 1/11
MAINTENANCE MANUAL
18. Conversion of pressure units (psi to kp/sq.cm) 1 psi = 0.068 kp/sq.cm psi
kp/sq.cm
psi
kp/sq.cm
psi
kp/sq.cm
1
0.068
35
2.413
69
4.757
2
0.137
36
2.482
70
4.826
3
0.206
37
2.551
71
4.895
4
0.275
38
2.620
72
4.964
5
0.344
39
2.688
73
5.033
6
0.413
40
2.757
74
5.102
7
0.482
41
2.826
75
5.171
8
0.551
42
2.895
76
5.240
9
0.620
43
2.964
77
5.308
10
0.689
44
3.033
78
5.377
11
0.758
45
3.102
79
5.446
12
0.827
46
3.171
80
5.515
13
0.896
47
3.240
81
5.584
14
0.965
48
3.309
82
5.653
15
1.034
49
3.378
83
5.722
16
1.103
50
3.447
84
5.791
17
1.172
51
3.516
85
5.860
18
1.241
52
3.585
86
5.929
19
1.310
53
3.654
87
5.998
20
l.378
54
3.723
88
6.067
21
1.447
55
3.792
89
6.136
22
1.516
56
3.861
90
6.205
23
1.585
57
3.930
91
6.274
24
1.654
58
3.998
92
6.343
25
1.723
59
4.067
93
6.412
26
1.792
60
4.136
94
6.481
27
1.861
61
4.205
95
6.550
28
1.930
62
4.274
96
6.618
29
1.999
63
4.343
97
6.687
30
2.068
64
4.412
98
6. 56
31
2.137
65
4.481
99
6.825
32
2.206
66
4.550
100
6.8940
33
2.275
67
4.619
34
2.344
68
4.688
EFFECTIVITY: ALL
006.00.01 Page: 19 Nov 1/11
MAINTENANCE MANUAL 19. Conversion of inch fraction to mm 1 inch = 25.4 mm Inch fraction 1/2
1/4
1/8
1/16
Inch (decimal)
1
0.015 625
0.396 875
2
0.031 250
0.793 750
3
0.046 875
1.090 625
4
0.062 050
1.587 500
5
0.078 125
1.984 375
6
0.093 750
2.381 250
7
0.109 375
2.778 125
8
0.125 000
3.175 000
9
0.140 625
3.571 875
10
0.156 250
3.968 750
11
0.171 875
3.365 625
12
0.187 500
4.762 500
13
0.203 125
5.159 375
14
0.218 750
5.556 250
15
0.234 375
5.953 125
16
0.250 000
6.350 000
17
0.256 625
6.746 875
18
0.281 250
7.143 750
19
0.296 875
7.540 625
20
0.312 500
7.937 500
21
0.328 125
8.334 375
22
0.343 750
8.731 250
23
0.359 375
9.128 125
24
0.375 000
9.525 000
25
0.390 625
9.921 875
13
26
0.406 250
10.318 750
27
0.421 875
10.715 625
14
28
0.437 500
11.112 500
29
0453 125
11.509 375
30
0.468 750
11.906 250
31
0.484 375
12.303 125
32
0.500 000
12.700 000
33
0.515 625
13.096 975
34
0.531 250
13.493 750
35
0.546 875
13.890 625
1
1
2
3
1
2
4
5
3
6
7
1
2
4
8
9
5
10
11
3
6
7
12
15
1
2
4
8
16
17
EFFECTIVITY: ALL
mm
1/64
1/32
006.00.01 Page: 20 Nov 1/11
MAINTENANCE MANUAL
Inch fraction 1/2
1/4
1/8
Inch 1/32
1/64
(decimal)
9
18
36
0.562 500
14.287 500
37
0.578 125
14.684 375
38
0.593 750
15.081 250
39
0.609 375
15.478 125
40
0.625 000
15.875 000
41
0.640 625
16.271 875
42
0.656 250
16.668 750
43
0.671 875
17.065 625
44
0.687 500
17.462 500
45
0.703 125
17.859 375
46
0.718 750
18.256 250
47
0.734 375
18.653 125
48
0.750 000
19.050 000
49
0.765 625
19.446 875
50
0.781 250
19.843 750
51
0.796 875
20.240 625
52
0.812 500
20.637 500
53
0.828 125
21.034 375
54
0.843 750
21.431 250
55
0.859 375
21.828 125
56
0.875 000
22.225 000
57
0.890 625
22.621 875
58
0.906 250
23.018 750
59
0.921 875
23.415 625
60
0.937 500
23.812 500
61
0.953 125
24.209 375
31
62
0.968 750
24.606 250
63
0.984 375
25.003 125
32
64
1.000 000
25.400 000
19
5
10
20
21
11
22
23
3
6
12
24
25
13
26
27
7
14
28
29
15
2
EFFECTIVITY: ALL
4
8
mm
1/16
16
30
006.00.01 Page: 21 Nov 1/11
MAINTENANCE MANUAL
20. Temperature conversion from Celsius to Fahrenheit
EFFECTIVITY: ALL
006.00.01 Page: 22 Nov 1/11
MAINTENANCE MANUAL
DIMENSIONS AND AREAS DESCRIPTION AND OPERATION 1. Main dimensions Length........................................................................................................... 14 424 mm Height (on the ground).................................................................................... 5 829 mm Landing gear spacing ..................................................................................... 3 650 mm Landing gear wheel base ............................................................................... 3 666 mm
2. Wing Span: a) Configuration with tips ............................................................................ 19 479 mm b) Configuration with wing tip tanks............................................................ 19 980 mm Wing area (without the tips)........................................................................ 34.860 sq.m Wing tip area ............................................................................................ 2 x 0.16 sq.m Mean aerodynamic chord ............................................................................... 1 918 mm Aspect ratio............................................................................................................ 10.45 Taper ratio ......................................................................................................... 0.44158 Wing twist: •
aerodynamic .........................................................................................................0°
•
geometric......................................................................................................- 2° 48'
Sweep back angle (at 25%, centerline) .......................................................................0° Angle of incidence at root .........................................................................................+ 2° Dihedral angle ....................................................................................................... 1° 45' Ailerons: Span ......................................................................................................... 2 x 3 822 mm Area ........................................................................................................ 2 x 1.448 sq.m Aileron deflection: •
up ............................................................................................................... 27° ± 1°
•
down ........................................................................................................... 14° ± 1°
NOTE:
Max. aileron deflections are marked by gauge lines on the airplane - see Fig. 2.
Trim tab span (left aileron only) ...................................................................... 1 030 mm Trim tab area .............................................................................................. 0.1966 sq.m
EFFECTIVITY: ALL
006.00.02 Page: 1 Nov 1/11
MAINTENANCE MANUAL Trim tab deflection: •
up................................................................................................................ 20° ± 2°
•
down ........................................................................................................... 20° ± 2°
Win flaps: Span..........................................................................................................2 x 4 830 mm Area .......................................................................................................... 2 x 2.96 sq.m Deflection of outer wing flap: •
take - off...................................................................................................... 18° ± 1°
•
landing ........................................................................................................ 42° ± 1°
Deflection differentiation of inner wing flap: •
take - off...............................................................................................not specified
•
landing ....................................................................................................+ 10° ± 30'
Ground spoilers: Span..........................................................................................................2 x 2 695 mm Area ...................................................................................................... 2 x 0.4353 sq.m Deflection...................................................................................................... 72°30' ± 2° ABC tabs: Span..........................................................................................................2 x 1 000 mm Area ...................................................................................................... 2 x 0.0983 sq.m Deflection........................................................................................................... 55° ± 2°
EFFECTIVITY: ALL
006.00.02 Page: 2 Nov 1/11
MAINTENANCE MANUAL
FIG. 1
MAIN DIMENSIONS
EFFECTIVITY: ALL
006.00.02 Page: 3 Nov 1/11
MAINTENANCE MANUAL
FIG. 2
GAUGE LINES MARKING MAX. AILERON DEFLECTIONS (1) Gauge lines in red color marking aileron max. deflections (2) Aileron control rod shroud varnished in white color
EFFECTIVITY: ALL
006.00.02 Page: 4 Nov 1/11
MAINTENANCE MANUAL
3. Stabilizer and elevator Span ............................................................................................................... 6 736 mm Total area ....................................................................................................... 9.56 sq.m Sweep-back angle (at quarter-chord) ..........................................................................5° Dihedral angle .............................................................................................................7° Taper ratio ................................................................................................................. 0.6 Aspect ratio.............................................................................................................. 4.79 Mean aerodynamic chord ............................................................................... 1 469 mm Angle of stabilizer setting..........................................................................................+ 2° Elevator: Area ........................................................................................................ 2 x 1.575 sq.m Max. deflection: •
up ............................................................................................................... 30° ± 1°
•
down .................................................................................................. 14° + 1° / - 0°
NOTE:
Max. elevator deflections are marked by gauge lines on the airplane - see Fig. 3.
Elevator trim tab area ............................................................................. 2 x 0.192 sq.m Elevator trim tab max. deflection: •
up ............................................................................................................... 10° ± 1°
•
down ........................................................................................................... 16° ± 1°
EFFECTIVITY: ALL
006.00.02 Page: 5 Nov 1/11
MAINTENANCE MANUAL
FIG. 3
GAUGE LINES MARKING MAX. ELEVATOR DEFLECTIONS (1) Gauge lines in red color marking elevator max. deflections (2) Edge of stabilizer lower skin varnished in white color
EFFECTIVITY: ALL
006.00.02 Page: 6 Nov 1/11
MAINTENANCE MANUAL
4. Fin and rudder Height ............................................................................................................. 3 310 mm Total area ......................................................................................................... 7.3 sq.m Sweep angle (at quarter-chord).................................................................................35° Aspect ratio................................................................................................................ 1.5 Taper ratio ................................................................................................................. 0.5 Mean aerodynamic chord ............................................................................... 2 285 mm Rudder: Area .............................................................................................................. 2.814 sq.m Max. deflection (to both sides)................................................................ 17° + 0 ° / - 30° NOTE:
Max. rudder deflections are marked by gauge lines on the airplane - see Fig. 4
Rudder trim tab area..................................................................................... 0.433 sq.m Max. rudder trim tab deflection (if UT-6D electromechanical strut is installed): .........................................................................................10° + 0° / - 1° (to the left side) .................................................................................10° + 0° / - 1° 30' ( to the right side) Max. rudder trim tab deflection (if 60 LUN 2520 linear actuator is installed): ............................................................................... 28° + 1° 30' / - 1° 30' (to both sides)
EFFECTIVITY: ALL
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FIG. 4
GAUGE LINES MARKING MAX. RUDDER DEFLECTIONS (1) Gauge lines in red color to check max. rudder deflection (2) Gauge line in white color
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AIRCRAFT ZONING DESCRIPTION AND OPERATION 1. General This section includes a description of the method used in zoning the aircraft and defines the boundaries of the major zones and major sub - zones. All zones are identified by three-digit numbers. The first digit defines the major zone. The major zones are identified in Figure 1 and are as follows: Major zone No. 100
Lower half of fuselage to rear bulkhead No. 21
200
Upper half of fuselage to rear bulkhead No. 21
300
Stabilizers. Includes stabilizers, rudder, elevators and tail section of fuselage aft of bulkhead No. 21
400
Power plants and struts
500
Left wing
600
Right wing
700
Landing gear and landing gear doors
800
Doors
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Definition
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FIG. 1
MAJOR ZONES
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MAINTENANCE MANUAL This major sub zones are identified by the remaining two digits and are shown in Figure 2 and 3. They are defined as follows: Major Sub-zone No.
Definition
110
Between fuselage stations No. 1 and No. 4 but excluding the nose wheel well which is part of major zone 700
120
Between fuselage stations No. 4 and No. 7
130
Between fuselage stations No. 7 and No. 21
140
-
150
-
210
Fuselage nose
220
Between fuselage nose and fuselage station No. 4
230
Between fuselage stations No. 4 and No. 7
240
Between fuselage stations No. 7 and No. 21 and between passenger compartment floor and roof levels
250
Between fuselage stations No. 7 and No. 12
260
Between fuselage stations No. 12 and No. 14 (wing center)
261
Fwd. fairing
270
Between fuselage stations No. 14 and No. 21
280
Passenger cabin-internal sub-divided: 281 - station No. 7 - No. 9 282 - station No. 9 - No. 12 283 - station No. 12 - No. 13 284 - station No. 13 - No. 14 285 - station No. 14 - No. 15 286 - station No. 15 - No. 18 287 - station No. 18 - No. 21
310
Fuselage rear section of bulkhead No. 21
311
Aft fairing
312
Ventral fin and tail cone
320
Vertical stabilizer
321
Vertical stabilizer
322
Rudder
323
Rudder trimming tab
330
Left horizontal stabilizer
331
Left horizontal stabilizer
332
Left elevator
333
Left elevator trimming tab
340
Right horizontal stabilizer
341
Right stabilizer
342
Right elevator
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Major Sub-zone No. 343
Right elevator trimming tab
410
Engine nacelle
420
-
430
Engine mount
440
Fire bulkhead
510 (610)
Left (right) wing leading edge to rear spar between aircraft center line and wing tip root rib
520 (620)
Left (right) wing trailing edge aft of rear spar between fuselage side and wing tip root rib
530 (630)
Left (right) wing flaps and slots
540 (640)
Left (right) aileron
541
Left aileron trim tab
550 (650)
Left (right) interceptor
560 (660)
Left (right) ABC tab
710
Nose wheel well and nose landing gear doors
720 (730)
Left (right) landing gear nacelle. Left (right) main landing gear tilting door
810 (820)
Left (right) front compartment door
830
Pilot's cockpit emergency exit door
840 (850) 860
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Definition
Left (right) passenger compartment emergency exit door Main door (entrance door, cargo door)
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FIG. 2
MAJOR SUB - ZONES - FUSELAGE AND TAIL
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FIG. 3
MAJOR SUB-ZONES-FUSELAGE AND TAIL PLANE
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ACCESS DOORS AND PANELS DESCRIPTION AND OPERATION 1. General Figure 1 provides master referral to Figures 2 to 13 inclusive, which taken as a group, identify all access doors and panels throughout the aircraft (both external and internal).
2. Method of identification Each access door or panel is identified by a numeric / alpha number. The numeric component of the number is the three digit number which identifies the smallest zone in which the door is located. The two-element alpha suffix designates the location of the door within the zone. The first alpha letter identifies each door within the zone in a logical sequence, i.e. inboard to outboard or front to rear, starting with A, AA in each zone. The second alpha letter locates the door in its relationship to the aircraft, as follows:
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T
=
Top
B
=
Bottom
L
=
Left hand
R
=
Right hand
Z
=
Internal
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FIG. 1
ACCESS PANELS - FIGURE IDENTIFICATION NOTE:
Figures 2, 3, 4, 5 cover all internal panels Figures 6 thru 13 cover all exterior panels
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FIG. 2
ACCESS PANELS OF FUSELAGE FRONT SECTION.
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FIG. 3
ACCESS PANELS - FLIGHT COMPT.
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FIG. 4
ACCESS PANELS - PASSENGER COMPT.
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FIG. 5
ACCESS PANELS - AFT BAGGAGE AND TOILET COMPT.
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FIG. 6
ACCESS PANELS - FWD. FAIRING
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FIG. 7
ACCESS PANELS - AFT FAIRING
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FIG. 8
ACCESS PANELS - POWER PLANT
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FIG. 9
ACCESS PANELS - WINGS
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FIG. 10
ACCESS PANELS - LANDING GEAR NACELLE
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FIG. 11
ACCESS PANELS - VERTICAL AND HORIZONTAL STABILIZERS
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FIG. 12
ACCESS PANELS - FUSELAGE
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FIG. 13
ACCESS PANELS - VENTRAL FIN AND TAIL CONE
EFFECTIVITY: ALL
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CHAPTER
LIFTING AND SHORING
MAINTENANCE MANUAL
CHAPTER 7 LIFTING AND SHORING LIST OF EFFECTIVE PAGES Chapter, Section, Subject
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CHAPTER 7 LIFTING AND SHORING CONTENTS Chapter, Section, Subject
Page
Effectivity
LIFTING AND SHORING (GENERAL) Description and Operation General Aircraft lifting Aircraft lowering Measures to be taken when lifting one wheel only Aircraft lifting by means of on - board hydraulic lifting jack Aircraft lowering by means of on - board hydraulic jack Application of the rear shore Installation of on - board hydraulic jack in the aircraft
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ALL
HZ 4 - 3 OR B 097 700 P/L HYDRAULIC JACK Description and Operation Purpose Technical data Servicing Maintenance of lifting hydraulic jack Check of HZ 4-3 hydraulic jack
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LIFTING AND SHORING (GENERAL) DESCRIPTION AND OPERATION 1. General 3 hydraulic lighting jacks and a tail prop strut B 962 104 N are supplied together with the aircraft for its lifting due to aircraft maintenance or leveling. On - boar hydraulic lifting jack, which is a part of ground equipment 1 : 1, is supplied for emergency cases during aircraft operation - tyre blowing, etc. For lifting the aircraft with one hydraulic lifting jack in case of defect of the nose wheel, one short tail prop B 596 340 N is supplied, which is a part of ground equipment 1 : 1.
2. Aircraft lifting CAUTION:
AIRCRAFT LIFTING MAY BY CARRIED OUT ONLY IN THE HANGAR, A ROOFED HALL, ETC. IN THE OPEN SPACE, THE LIFTING MAY BE CARRIED OUT ONLY WHEN NO WIND IS BLOWING.
A.
Remove covers enabling the access to jacking points on landing gear nacelle - see Fig. 1. NOTE:
B.
Jacking points for hydraulic lifting jacks are marked with inscription PROP LOCATION.
Position the hydraulic lifting jacks under the respective aircraft jack point (see Fig. 2).
C. Check on, whether the overflow valve of lifting jacks is closed (position 5) - see Fig. 1 of subject 007.00.01. D. Open the vent valve (7). E.
Shift the control bar (8) on the pump (9) and start pumping. If possible, do use the whole stroke of the pump for pumping. NOTE:
Hydraulic lifting jack is not equipped with safety relief valve, therefore the maximum lifting jack extension is limited by fixed stops. If you feel increased resistance during the pumping, it means the jack has reached the maximum of hydraulic stroke. Stop pumping. When using the lifting jack at temperatures of - 45°C up to - 50°C, approximately 60 strokes / minute must be performed, so as to assure the lifting jack full efficiency and preventing its aeration.
F.
After lifting the aircraft to the necessary height, secure the lifting jack by the security strut (4). WARNING:
WITHOUT USING THE SECURITY STRUT, NO PERSON MUST STAY UNDER THE AIRCRAFT.
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MAINTENANCE MANUAL G. Position the tail prop strut into the hole in the lower fin of fuselage rear part near the frame No. 24 and adjust the length of the prop B 962 104 N such, that its base is touching the ground. CAUTION:
(1) WITH THIS POSITION OF THE TAIL PROP STRUT, THE HYDRAULIC LIFTING JACKS MUST NOT BE MANIPULATED TO AVOID FUSELAGE REAR PART DEFORMATION. (2) IF THE AIRCRAFT RESTS ON THE LIFTING JACKS, THERE MUST BE NO ASYMMETRIC LOAD ON ONE WING. THIS MIGHT CAUSE AIRCRAFT TILTING OVER TO THE SIDE OF HEAVIER LOAD. MAX. PERMISSIBLE DIFFERENCE OF THE LOAD AT THE WING END IS 50 KP.
3. Aircraft lowering CAUTION:
BEFORE YOU START TO SINK THE HYDRAULIC LIFTING JACKS, MAKE SURE THAT THE TAIL PROP STRUT B 962 104 N HAS BEEN REMOVED. IF NOT, THE DEFORMATION OF FUSELAGE REAR PART MAY HAPPEN.
A.
Loosen the tightening nuts of the locking struts (4) - see Fig. 1 in subject 007.00.01 and loosen the locking struts of all 3 lifting hydraulic jacks.
B.
Loosen the overflow valve (5) of all 3 hydraulic lifting jacks simultaneously to enable the plane to sink evenly.
4. Measures to be taken when lifting one wheel only A.
Position the lifting hydraulic jack under the jack point at the proximity either of the main or nose wheel. On soft soil use a pad under the hydraulic lifting jack base.
B.
When lifting the main landing gear (1) Turn the nose wheel so, that the lateral side of the nose wheel will remain turned towards the main wheel, which remains on the ground. Do not use chocks to secure the nose wheel. You will enable easier balancing of the aircraft position in lifting it in one point only. (2) Secure main wheel, which remains on the ground by means of chocks from both sides. (3) When putting the lifting jack under the aircraft, position the jack such way as to be slightly deviated (1°approx) from the aircraft center line. The devia tion will enable the lifting jack balancing when is being lifted.
C. When lifting the nose landing gear Before lifting the aircraft front part it is necessary to install the shortened tail prop strut B 596 340 N. Secure at least one main wheel by chocks from both sides. The chock in the front must be approx. 5 cm from the tyre, since main wheels will shift slightly forward during the lifting.
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FIG. 1
FULCRUM IN THE LANDING GEAR NACELLE (1) Landing gear nacelle; (2) Detachable cover; (3) Rear spar of the landing gear nacelle
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FIG. 2
SCHEME OF LIFTING JACKS AND TAIL PROP STRUT LOCATION (1) Left - hand hydraulic lifting jack HZ 4-3 or B 097 700 L, execution 3 (2) Right - hand hydraulic lifting jack HZ 4-3 or B 097 700 P, execution 3 (3) Tail prop strut L 410.9620 (4) Pin securing the prop in the fuselage (5) Locking pin for the prop length adjustment (6) Shortened tail prop strut B 596 340 N (not shown in the Fig. 2)
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MAINTENANCE MANUAL 5. Aircraft lifting by means of on - board hydraulic lifting jack A.
Check on, whether the overflow valve (2) is closed - see Fig. 2 in subject 007.00.01.
B.
Open the vent valve (4).
C. Shift on the control bar (3) and start pumping. Use the whole pump stroke for pumping, if possible. NOTE:
The jack is not equipped with a relief valve, therefore the jack maximum shift - out is determined by dead stops. If you feel increased resistance during pumping, it means the jack has reached the maximum of the hydraulic stroke. Stop pumping. When using the lifting jack at temperatures, ranging from - 45°C t o - 50°C, approx. 60 strokes per minute must be performed in order guarantee the lifting jack full efficiency and prevent its aeration.
D. After lifting the aircraft at the necessary height, secure the lifting jack by security strut (6). WARNING:
WITHOUT USING THE SECURITY STRUT NO PERSON IS ALLOWED TO STAY UNDER THE AIRCRAFT.
6. Aircraft lowering by means of on - board hydraulic jack A.
Remove the security strut (6) - see Fig. 2 in subject 007.00.01.
B.
Slowly open the overflow valve to allow the aircraft to sink slowly.
7. Application of the rear shore Tail prop strut XL 410.9620 and shortened tail prop strut B 596 340 N serve to secure the aircraft against tipping over on the fuselage rear part, when the aircraft rests lifted on the lifting jacks, when are carried on in the fuselage rear section (e.g. in the cargo compartment) and when engines are dismantled in spite of the aircraft not being lifted on the lifting jacks. It is fixed in a hole in the lower fin, near the 24th frame. The tail prop height must be adjusted as follows: •
when the aircraft is on lifting jacks - with the base touching the ground.
•
when the aircraft is not on lifting jacks - with the prop base elevated 10 cm from the ground, as far as the terrain inclination permits for it (10 cm reserve allows for the possible undercarriage dampers spring action).
8. Installation of on - board hydraulic jack HZ 4-3 in the aircraft On - board hydraulic lifting jack and securing prop are placed between the 12th and 13th frames on the passenger cabin right side under the seat no. 8. Hydraulic jack including the pad for soft terrain is fixed with two bolts provided with wing nuts into the thread holes in the passenger cabin floor. NOTE:
For fixing of on - board lifting jack use always only bolts L 410.9515-01 with washers 8.2 CSN 021740.14.
Security strut including the handle of lifting jack pump is stored in artificial leather packing and is fixed with two straps to the passenger cabin floor. EFFECTIVITY: ALL
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HYDRAULIC JACK HZ 4 - 3 OR B 097 700 P/L DESCRIPTION AND OPERATION 1. Purpose Hydraulic lifting jacks are designed for aircraft lifting. They are supplied in two executions: •
HZ 4 - 3 P/L or B 097 700 P/L, execution 3, see Fig. 1 - this are designed for the operation in the hangar
•
HZ 4 - 3 execution 2; see Fig. 2 - this are designed for emergency cases during operation
When positioning the lifting jack under the landing gear nacelle, the right - hand jack must be put under the right hand nacelle and the left - hand jack under the left - hand nacelle. The left and right hand jacks can be distinguished by looking at the jack from the manipulation handle - the right hand jack has a locking strut on the right - hand side, the left - hand jack has a locking strut on the left - hand side. NOTE:
The locking strut (4) position is easy to be changed by unscrewing the lock screw (3) on the upper side of the jack frame, the locking strut (4) is to be turned into the required position and the lock screw (3) is screwed on again. Thus the lifting jack may be adjusted to become the “right-hand” or “left-hand”.
2. Technical data Maximum loading (bearing capacity)
4t
Maximum axis deviation of shifted - out lifting jack from the vertical e.g. 25 mm at the jack basic height of 300 mm.
5°
Hydraulic liquid
AMG - 10
Operational temperature range for the lifting jack:
- 50°C till + 60°C
NOTE:
When ambient air temperature is - 45°C up to - 50°C it is necessary to keep 60 strokes per minute during the lifting, in order to guarantee the lifting jack full efficiency and prevent its aeration (due to the changing density of hydraulic liquid at low temperatures).
Strength measured 50 mm from the control bar end at the nominal loading capacity
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max. 350 N (35 kp)
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FIG. 1
HYDRAULIC JACK HZ 4-3 OR B 097 700 P/L EXECUTION 3 (1) Hydraulic lifting jack Hz 4-3; (2) Jack frame; (3) Security screw; (4) Locking strut; (5) Overflow valve; (6) Filling hole; (7) Vent valve; (8) Handle bar; (9) Pump
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FIG. 2
ON - BOARD HYDRAULIC LIFTING JACK HZ 4-3, EXECUTION 2 (1) Filling hole; (2) Overflow valve; (3) Handle bar; (4) Vent valve; (5) Pad for soft terrain; (6) Locking strut; (7) One piston pump
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HYDRAULIC JACK HZ 4 - 3 OR B 097 700 P/L SERVICING 1. Maintenance of lifting hydraulic jack HZ 4-3 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
MK 8 Oil
C. Tools
Not applicable
D. Referenced Information
-
E.
Procedures (1) Deaeration With a new hydraulic lifting jack, so far never in operation or having been stored for a longer time, deaeration must be performed as mentioned below: (a) Check on whether the overflow valve is closed and start pumping. In case the pump does not work within the whole range, it is obvious the pump is aerated and deaeration must be carried out. (b) Open the vent valve and press the jack down to the initial position. (c) Close the vent valve, put the jack in a horizontal position with the pump downwards and pump several times. Thus the air escapes from the area under the pump piston and the lifting jack is ready for use. Complete air discharging from the area under the pump piston results in proper pump operation within the whole range. (2) Filling with hydraulic liquid Check on the filling of the lifting jack by hydraulic liquid as follows: Tilt the jack to the angle of 45° with the filler u pwards. The hydraulic liquid level must reach the lower edge of the filler. Possible refilling is to be carried with hydraulic liquid AMG-10 into the filler. (3) Lubrication Lubrication is carried out periodically (once a year) or in case of need more frequently by oil MK 8. Lifting jack moving parts are to be lubricated. (4) Storage If the hydraulic lifting jack is not supposed to be used for a longer period, it is necessary to operate it at least once in a half year by pumping it to the extreme position without the load. The function of the lifting jack is thus checked on and jack sliding surfaces are conserved. For storage, the lifting jack has to be positioned in vertical position.
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2. Check of HZ 4-3 hydraulic jack or B 097 700 P/L A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
-
E.
Procedures (1) Functional check (a) Put a load of 4,000 kg on the hydraulic jack. (b) Check that the relief valve is closed and start swinging the hand lever of the jack. The following defects are not permissible: jamming, seizing, cut-outs, settling or other defects affecting correct functioning of the jack. (c) When the small piston has reached approximately 30 % to 50 % of its travel, stop swinging the hand lever and watch the spontaneous settling of the piston for a period of 2 minutes. The piston must not settle by more than 1.7 mm. (2) Check for strength of the jack frame and adjustable strut. (a) Extend the jack to its max. height of 850 ± 3 mm and support its head with the adjustable strut. NOTE:
Maximally 125 full strokes of the hand lever are permitted to extend the large piston by 100 mm.
(b) Apply a force of 20,000 N (2,000 kp) to the jack head. (c) Open the relief valve slowly. (d) The force is to be applied for a period of 5 minutes. The following defects are not permissible: any deformation (deflection) of the jack frame or adjustable strut. (e) Remove the force acting on the jack head. Remove the adjustable strut and reset the piston to its original position. The force required to reset the piston to its original position must not exceed 350 N (35 kp). CAUTION:
EFFECTIVITY ALL
NO HYDRAULIC FLUID LEAKAGE CAN OCCUR DURING THE TEST.
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CHAPTER
8 LEVELLING AND WEIGHING
MAINTENANCE MANUAL
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CHAPTER 8 LEVELLING AND WEIGHING CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
WEIGHING Description and Operation General Weighing procedure
008.10.00
1 1 1 2
ALL
LEVELLING Description and Operation General Positioning of the airplane into horizontal position Positioning of the airplane into the “flight” position (e.g. for adjustment of fuel gauges, autopilot adjustment etc.)
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WEIGHING DESCRIPTION AND OPERATION 1. General Aircraft weighing and counterbalancing is made by means of three balances, on which the aircraft is positioned by hydraulic lifting jack - see Fig. 1. Balances inaccuracy for aircraft weighing may be 0.2 % max.
FIG. 1
AIRCRAFT POSITIONED ON BALANCES (1) Front balance; (2) Left - hand balance; (3) Right - hand balance
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2. Weighing procedure A.
Before starting the aircraft weighing, the aircraft must be in horizontal position according to section 008.20.00.
B.
Find out, whether the aircraft outfit corresponds to the required configuration supposed to be weighed.
C. Record the values ascertained on the particular balances (R 1 , R 2 ). NOTE:
R 2 = R 2LH + R 2RH
D. Put the ascertained values into the formula and execute the calculation. The center of gravity from the reference plane:
X AP =
R 1 × X1 + R 2 × X 2 = ............. [m] G AP
Center of gravity in respect to the mean aerodynamic chord (MAC):
XT =
(X AP − A) × 100 = .............% MAC MAC
Symbols used: X AP
(m)
center of gravity position from reference plane (leveling point No. 2).
X1
(m)
distance of the front prop axis from leveling point No. 2 (X 1 = 0.865 m).
X2
(m)
distance of the left and right - hand axis from leveling point No. 2 (X 2 = 3.700 m).
R1
(kg)
reaction on front balance (after subtracting the hydraulic lifting jack weight).
R2
(kg)
reaction on rear balances (sum of reaction on the left and right - hand balance after subtracting the hydraulic jack weight).
G AP
(kg)
aircraft total weight.
A
(m)
distance from leveling point No. 2 to the beginning of mean aerodynamic chord (A = 2.19055 m).
MAC
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(m)
length of mean aerodynamic chord (b = 1.9178 m).
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FIG. 2
SCHEME FOR COUNTERBALANCING CALCULATION For other symbols see above text.
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LEVELLING DESCRIPTION AND OPERATION 1. General The airplane levelling must be done in following cases: •
after disassembly and assembly of a wing, a vertical stabilizer and horizontal stabilizer,
•
in case, that the maximum speed has been exceeded, or the operational load factor has been exceeded (acceleration),
•
after extraordinary hard landing or more serious airplane damage,
•
in case of flight performance deterioration that has been caused by airframe deformation.
2. Positioning of the airplane into horizontal position The positioning of the airplane into horizontal position is done as follows: •
in transversal plane by means of levelling points No. 19 on the left and right wing – refer to the fig. 1. Both levelling points must be found in one plane (left and right point).
•
in longitudinal plane by means of levelling points No. 1, 7. The horizontal positioning of the airplane itself is made by means of hydraulic lifting jacks in accordance with Chapter 7. A list of levelling points and other dimensions for the levelling are given in the Levelling Record, Document No. – Do-L410-1262.2, which is issued by the manufacturer for each airplane separately. When checking on the levelling in operation, the previously measured levelling values have to be relied upon; these are mentioned in the Levelling Record.
3. Positioning of the airplane into the “flight” position (e.g. for adjustment of fuel gauges, autopilot adjustment etc.) - eventually other units according to the requirement in other chapters. The positioning itself into the required position is made by the means of hydraulic lifting jacks in accordance with Chapter 7. The positioning of the airplane into the “flight” position (e.g. for adjustment of fuel gauges, autopilot adjustment etc.) is made as follows: •
in transversal plane by means of levelling points no.19 on the left and right wing
Both levelling points must be found in one plane (left and right point) •
in longitudinal plane into the position 1.5° of the front fuselage section up from the horizon plane by means of levelling points No.3 and 6 situated in levelling plane of the fuselage – refer to the Levelling Record.
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MAINTENANCE MANUAL At lifted front fuselage about angle α=1.5° and at distance between the levelling points (3-6) L=4484 mm levelling point No.3 is to be about distance H NB3 higher from the horizontal plane passing through the levelling point No.6. H NB3 = L x sin α = 4484 mm x sin 1.5° = 117 mm
FIG. 1
HORIZONTAL POSITIONING OF THE AIRPLANE (Except levelling points No. 1 and 7, which are important for positioning into the horizontal position, there are also levelling points No. 3 and 6 marked situated in fuselage levelling plane – refer to the Levelling Record)
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CHAPTER
9 TOWING AND TAXIING
MAINTENANCE MANUAL
CHAPTER 9 TOWING AND TAXIING LIST OF EFFECTIVE PAGES Chapter, Section, Subject
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CHAPTER 9 TOWING AND TAXIING RECORD OF TEMPORARY REVISIONS Rev. No.
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CHAPTER 9 TOWING AND TAXIING CONTENTS Subject
TOWING AND TAXIING (GENERAL) Description and Operation Minimum turning radius when airplane taxiing on the ground Tractor towing Airplane handling by means of hand towing equipment
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TOWING AND TAXIING (GENERAL) DESCRIPTION AND OPERATION 1. Minimum turning radius when airplane taxiing on the ground Fig. 1 shows the necessary space shown by circles for the turning of the airplane. The smaller circle shows the circle written by the outside wheel of main landing gear, the bigger circle shows the circle, written by the tip of the wing. The values are given the maximum deviation of the nose wheel, i.e. 50° - 5° (the marginal tolerance of - 5°, i.e. 45° is considered).
FIG. 1
MINIMUM TURNING RADIUS FOR AIRPLANE TAXIING OF THE GROUND The values are given in meters and rounded - off to tenths of meter.
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MAINTENANCE MANUAL 2. Tractor towing Towing the airplane by a tractor is performed by means of towing equipment B097581N or B097582N. A.
B097581N Towing equipment (refer to the Fig. 2) B097581N towing equipment is secured against shocks by a spring damper, located in the front part of the towing shaft - bar. The shaft bar itself (tube) of the towing equipment is connected with the suspension device by a connecting element with 2 security pins – refer to the pos. (4) and (5). The material of security pins is selected such, that the front pin will be damaged in case of excess load in the straight direction and the rear pin will be damaged if excess force is developed in the lateral direction. A label is attached on the bar referring to the pins material to be unconditionally used, if the pins must be replaced: SECURITY PINS MATERIAL: STEEL TENSILE STRENGHT σ PT = 392 MPa (40 kp/mm2) Attachment of towing equipment is carried out as follows: Position the shaft - bar of the towing equipment against the hole in the swinging arm of the nose landing gear and insert the pin (2) into hole. Secure the pin (2) by a security plunger (3).
FIG. 2
B097581N TOWING EQUIPMENT (1) Towing equipment; (2) Pin; (3) Security plunger; (4) B952222N Front security pin; (5) B952272N Rear security pin; (6) Label; (7) Nose landing gear leg
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MAINTENANCE MANUAL B. B097582N Towing equipment (refer to the Fig. 3) (if supplied) The towing equipment is equipped with a security pin (6) against landing gear damage in case the maximum deviation angle of the nose wheel is exceeded. CAUTION:
IF THIS PIN HAS BEEN DAMAGE, THE PIN MAY BE REPLACED ONLY BY THE B952272N PIN OR BY A PIN, MADE OF MATERIAL WITH RENSILE STRENGHT MAX. 392 MPa (40 kp/mm2).
Attach towing equipment as follows: Position the shaft-bar of the towing equipment (2) against the hole in the swinging arm of the nose landing gear, insert the pin (4) and secure it by putting down the latch. Position the yokes (7) which are at the end of the towing cable on the main landing gear by means of pins (8) inserted into holes in the hollow pins fastening the landing gear damper and secure them with a wedge (9).
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FIG. 3
B097582N TOWING EQUIPMENT (1) Towing equipment; (2) Shaft-bar; (3) Cable; (4) Pin for attachment to the nose landing gear; (5) Nose landing gear; (6) B952272N Safety pin; (7) Yoke; (8) Pin for attachment to the main landing gear; (9) Wedge; (10) Main landing gear, (11), (12) Safety connection assembly, (13) Cable, (14) Pin; (15) B952348N Safety connection (2 pcs for the RH side), (16) B952353N Safety connection (2 pcs for the LH side), (17) M12 ISO 7042 Safety nut; (18) B098756N Pin; (19) B098757N Distance ring (P) – Detail of the attachment to main landing gear (R) – Detail of the attachment to the nose landing gear
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MAINTENANCE MANUAL C. Instructions for towing with a tractor When towing the airplane by a tractor, the following regulations must be observed: (1) In the cockpit cabin a pilot or mechanician must be seated, familiar with the attendance of the airplane brakes. (2) The B596476N blocking strut of the steering (refer to the Fig. 1 in Section 010.10.00) must be removed. (3) The servo of the nose wheel as well as the nose wheel from the pedals must be shut - off, i.e. PEDAL NOSE WHEEL STEERING on the control console must be in neutral position. (4) The brakes accumulator must have a pressure of at least 9.80 MPa (100 kp/cm2). NOTE:
The pressure gauge of brakes accumulator indicates only with the 36V inverter on. After checking on the pressure, switch - off the converter immediately. If the pressure in the brakes accumulator is not sufficient, the airplane may be towed exceptionally, but the pilot (mechanician) must bear in mind, that in emergency case, when the situation will require braking the airplane, he will apply the parking brake.
(5) The maximum turning angle of the airplane nose wheel as the tractor starts its way with the airplane attached must not exceed 25°. NOTE:
During manual towing it is allowed maximum turning angle of the nose wheel of 30° when starting pull.
(6) Before you instruct the tractor driver to start towing check on whether the parking brake is off and the airplane door is closed. CAUTION:
THE AIRPLANE MUST NOT BE MOVED OR TOWED WITH ENTRANCE DOOR OPEN.
(7) During the towing, the nose wheel may be swiveled to the maximum of 30°. (8) When towing the airplane, the tractor driver must avoid rash movements with the steering wheel and sudden braking. It is recommended not to exceed the speed of 10 - 15 km/hour. (9) When towing the airplane at limited visibility, switch on the airplane position lights. (10) Rearward towing (Airplane PUSH BACK, i.e. tail ahead) of the airplane by a tractor is not permitted. In case of necessary, the airplane can be pushed by means of tractor and B097581N towing equipment . CAUTION:
TAKE GREAT CARE TO PREVENT DAMAGE TO THE WINGS OR TAIL UNIT. DO NOT EXCEED MAX. SPEED OF 5 KM/HR.
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3. Airplane handling by means of hand towing equipment To manipulate the airplane as it is towed out of the hangar, etc., a B952053N hand towing equipment is used, which is substantially lighter than the towing equipment, used for towing the airplane by a tractor. The hand towing equipment is attached by means of a pin in the swinging arm of the nose landing gear leg – refer to the Fig. 4.
FIG. 4
B952053N HAND TOWING EQUIPMENT (1) Manual bar; (2) Pin; (3) Nose landing gear leg
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CHAPTER
PARKING AND MOORING
MAINTENANCE MANUAL
CHAPTER 10 PARKING AND MOORING LIST OF EFFECTIVE PAGES Chapter, Section, Subject
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Servicing
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CHAPTER 10 PARKING AND MOORING CONTENTS Subject
Chapter, Section, Subject
PARKING 010.10.00 Description and Operation Parking equipment for parking during a flight day Parking equipment Coating assembly (if supplied) Grounding assembly Servicing Setting of the chocks under the aircraft wheels Removal of the chocks from the aircraft wheels Setting of the covers on the Pitot and static pressure probes, the engines and generators air inlets and the canvas on the windshield and windows of the pilot's cockpit Securing of the aircraft control column by means of a blocking strut Installation of the devices on the aircraft for parking on the apron Aircraft grounding Fitting complete covers on the aircraft Removal of the devices from the aircraft after parking Removal of the blocking strut of the aircraft control column MOORING Description and Operation General Servicing Aircraft mooring Removal of the aircraft mooring device
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PARKING DESCRIPTION AND OPERATION 1. Parking equipment for parking during a flight day To secure the aircraft for parking during a flight day a blocking strut B 596 476 N is used.
FIG. 1
SECURING OF COLUMN BY BLOCKING STRUT (1) Column; (2) Lid in the cover between the pedals; (3) Blocking strut B 596 476N; (4) Tension nut
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2. Parking equipment To secure the aircraft parking on the apron, the following parking equipment is used: No.
Name
Qty
1.
Propeller blocking
B 596 276 N or B 596 695 N
2
2.
Wheel chock
B 925 028 N (L410.9250) or B 596 895 N
3
3.
Aileron security clamp
L410.9220
2
4.
Elevator blocking
L410.9220
2
5.
Rudder blocking
B 596 790 N or B 096 107 N
1
6.
Cover of engine air inlet
B 596 452 N
2
7.
Exhaust cover / for winter season
B 096 127 P/L
Exhaust coating / for summer season
B 096 008 N
4
8.
Pitot nozzle cover
B 096 360 N
2
9.
Blind flanges for static pressure pickups
L 410M.9537
2
10.
Coating for windshield flight compartment
B 596 798 N or L410.9516
1
11.
Toilette ventilation cover
B 596 420 N
1
12.
Cover of starting generator air inlet
B 596 580 N
2
13.
Locking pins for securing the emergency exit door B 596 555 N (valid only for aircraft with emergency exit door under the wing)
3
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Type (Dwg. No.)
2+2
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FIG. 2
PARKING EQUIPMENT FOR PARKING ON THE APRON Legend to fig.: see table in para 2. Locking pins (13) are not drawn.
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MAINTENANCE MANUAL 3.
Coating assembly (if supplied) Coating assemblies serves for aircraft protection on the apron. The coatings are marked with serial numbers 1 – 24 and are inserted into coating wrappings L410.9320-19, marked with serial numbers I – VI. The aircraft coatings assemblies include: Coating wrapping
I
II
Coating number
Name
Drawing number
Pcs
1
L.H. wing coating
B 596 397 L b.v.
1
21
L.H. fuel tank coating
B 596 338 L b.v.
1
23
Coating of wing tip
B 596 451 L b.v.
1
2
L.H wing-fuselage coating
B 096 076 L b.v.
1
3
Engine coating
B 096 077 L b.v.
1
4
R.H. wing coating
B 596 397 P b.v.
1
22
R.H. fuel tank coating
B 596 338 P b.v.
1
24
Coating of wing tip
B 596 451 P b.v.
1
5
R.H. wing-fuselage coating
B 096 076 P b.v.
1
6
Engine coating
B 096 077 P b.v.
1
7
Propeller blade coating
B 596 398 N b.v.
8
8
Propeller cap coating
B 596 400 N b.v.
2
9
Propeller blade coating with strap
B 596 399 N b.v.
2
10
Flight compartment coating
B 596 405 N b.v.
1
11
Fuselage rear part coating
B 096 078 N b.v.
1
12
Fuselage central part coating
B 096 075 N b.v.
1
13
Antenna coating
L410M.9322-37b.v.
2
14
L.H. stabilizer coating
B 096 080 L b.v.
1
15
R.H. stabilizer coating
B 096 080 P b.v.
1
16
Fin coating
B 096 081 N b.v.
1
17
L.H. landing gear nacelle coating
B 596 396 L b.v.
1
18
R.H. landing gear nacelle coating
B 596 396 P b.v.
1
III
IV
V
VI
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MAINTENANCE MANUAL Coating wrapping
Coating number
Name
Drawing number
19
Nose landing gear coating
B 096 072 N b.v.
20
Wheel coating
B 096 085 L/P b.v.
Pcs 1
VI 1+1
4. Grounding assembly Grounding equipment B 096 432 N is designed for grounding of the aircraft.
FIG. 3
COVERS FOR AIRCRAFT COVERING Legend to fig – see table in para 3.
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PARKING SERVICING 1. Setting of the chocks under the aircraft wheels Removal of the chocks from the aircraft wheels A.
Fixture, Test and Support Equipment
B 925 028 N Wheel chock (3pcs) B 596 895 N Wheel chock (3pcs)
B. Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
010.10.00.A Routine
E.
Procedures (1) Underlay the aircraft wheels with the chocks (the main wheels from the rear, the nose wheels from the front) see fig. 301. NOTE:
For current parking use the B 596 895 N chocks, when engine test is carried out use the B 925 028 N chocks
(2) Remove the chocks from the aircraft wheels (the main wheels from the rear, the nose wheels from the front).
FIG. 301
DIAGRAM OF THE WHEEL CHOCKS POSITIONING (1) Wheel chocks (3 pcs)
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2. Setting of the covers on the Pitot and static pressure probes, the engines and generators air inlets and the canvas on the windshield and windows of the pilot's cockpit A.
Fixture, Test and Support Equipment
B 096 360 N Cover of the Pitot nozzle (2 pcs) L 410.9537 Blind flanges of static pressure sensors (2 pcs) B 596 452 N Covers of the air inlet of the engine (2 pcs) B 596 798 N Canvas of the flight compartment windshield (1 pc) B 097 300 N Stairs (1 pc) B 596 580 N Covers of the air inlet of the generator (2 pcs) B 596 420 N Covers of toilette venting (1 pc)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
010.10.00.B Routine
E.
Procedures (1) In case of rain or snow fit onto the aircraft:
covers of Pitot nozzle
blind flanges of static pressure sensors
(2) In case of snowing fit onto the aircraft:
covers of the air inlets of the engine
covers of the air inlet of the generator
canvas of the flight compartment windshield
(3) In case of dust storm fit onto the aircraft parking covering as per points (1) and (2).
3. Securing of the aircraft control column by means of a blocking strut A.
Fixture, Test and Support Equipment
B 596 476 N Blocking strut
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
010.10.00.C Routine
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MAINTENANCE MANUAL E.
Procedures CAUTION:
THE BLOCKING STRUT B 596 476 N MAY BE USED UP TO THE MAX. WIND VELOCITY OF 65 KM/HOUR. FOR A STRONGER WIND, CONTROL SURFACES BLOCKINGS HAVE TO BE USED - SEE PARKING ON APRON INSTRUCTIONS.
(1) Open the lid between the left and right pedal of the foot control. (2) Tilt away the column of the control lever from the instrument panel. (3) Fit the blocking strut on the control lever and into the grooves on the levers of foot control pedals - see fig. 1. (4) Tighten manually the blocking strut nut so that the control column cannot be moved.
4. Installation of the devices on the aircraft for parking on the apron A.
Fixture, Test and Support Equipment
B 596 695 N Propeller blocking (2 pcs) L 410.9220 Ailerons and elevator blocking (4 pcs) B 596 790 N Rudder blocking (1 pc) B 596 452 N Covers of the air inlet of the engine (2 pcs) B 096 127 N (L/P) Exhaust covers (2+2 pcs) or exhaust cover canvas B 096 008 N (4 pcs) B 096 360 N Pitot tube cover (2 pcs) L 410M.9537 Blinds of the static pressure sensors (2 pcs) B 097 365 N Stairs (1 pc) B 596 580 N Covers of the air inlet of the generator (2 pcs) L 410.9250 (3 pcs) B 596 895 N (3 pcs) Wheel chocks
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
010.10.00.D Routine
E.
Procedures (1) When the control has been blocked by the control lever strut B 596 476 N, remove the strut. (2) Set the propeller blade to the lower position and slip on it the canvas cover of the propeller blocking - see fig. 2. Fix the cover with strip to the engine exhaust.
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MAINTENANCE MANUAL (3) Set the aileron to the neutral position and lock it by means of two locking clamps (3) - one locking clamp on the left and one on the right aileron. (4) Deflect the rudder as desired and lock it by means of locking clamps for rudder blocking (5). (5) Set the elevator to the neutral position and lock it by means of locking clamps for elevator blocking (4) - one on the left and one on the right elevator. (6) Air inlets to the engine cover with blinds (6). (7) Cover air inlets to the generator with blinds. (8) Set on the engine exhaust: in winter season - exhaust covers (7) - B 096 127 P, L In summer season – exhaust cover canvas (7) – B 096 008 N (9) Place covers (8) on the Pitot tubes. (10) Blind the openings of the static pressure sensors with blinds (9). (11) Underlay the aircraft wheels with the chock.
5. Aircraft grounding A.
Fixture, Test and Support Equipment
B 096 432 N Grounding cable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
010.10.00.E Routine
E.
Procedures (1) Prick the tip sharp terminal of the grounding into the ground (or put it into the grounding holes in the concrete area) near the nose landing gear. (2) Fix the grounding cable clamps to the pins of the leg of left and right main landing gear (pin for fixing of the landing gear in mechanical lock of left and right main landing gear).
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6. Fitting complete covers on the aircraft A.
Fixture, Test and Support Equipment
B 596 397 L ND Wing cover left (1 pc) B 096 076 L ND Wing-fuselage cover (1 pc) B 096 077 L ND Engine cover (1 pc) B 596 397 P ND Wing cover right (1 pc) B 096 076 P ND Wing fuselage cover right (1 pc) B 096 077 P ND Engine cover (1 pc) B 596 398 N ND Propeller blade cover (8 pcs) B 596 400 N ND Propeller cone cover (2 pcs) B 596 399 N ND Propeller blade cover with the strap (2 pcs) B 596 405 N ND Cabin cover (1 pc) B 096 078 N ND Fuselage rear section (1 pc) B 096 075 N ND Fuselage central section cover (1 pc) L 410M.9322.37 ND Antenna cover (2 pcs) B 096 080 L ND Tail plane cover left (1 pc) B 096 080 P ND Tail plane cover right (1 pc) B 096 081 N ND Fin cover (1 pc) B 596 396 L ND Cover of the left landing gear nacelle (1 pc) B 596 396 P D Cover of right landing gear nacelle (1 pc) B 096 072 N ND Nose landing gear cover (2 pcs) B 096 085 N ND Wheel cover (2 pcs) B 596 338 L ND Cover of terminal fuel tank left (1 pc) B 596 338 P ND Cover of terminal fuel tank right (1 pc) B 596 451 L ND Tip cover (1 pc) B 596 451 P ND Tip cover (1 pc) L 410.9615 ND Assembly bogie B 097 365 N ND Stairs (2 pcs) L 410.9620 ND Rear strut
B.
Materials
C. Tools
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Not applicable Not applicable
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MAINTENANCE MANUAL D. Referenced Information
010.10.00.F Routine
E.
Procedures (1) Before to putting on complete covers on the aircraft, carry out the operational maintenance of parking according to maintenance schedule for the aircraft. (2) Prepare near to the aircraft
The stairs B 097 365 N to the left, right wing - 2 pcs and to the tail planes (extension stairs may be used according to the airfield outfit )
The assembly bogie L410.9615 under fuselage
NOTE: If a mobile assembly equipment is available at the airfield, then it is possible to use the set of assembly platforms consisting of:
the assembly platform below the left and right wing (within the area of the engine nacelles)
from the left and right assembly platform, situated below the wing tips
from the assembly platforms to the tail planes. It is also possible to use high-lift hydraulic platforms
(3) Install the fuselage rear strut L410.9620 on the rear section of the fuselage as follows:
fix the strut in the jack point in the lower fin if the fuselage
remove the pin from the strut telescopic section and shift-out the telescopic section that the strut base touches the ground. Lock the telescopic section of the strut at required length with a pin
(4) Prepare near to the aircraft the complete set of clean and checked canvas covers being packed in six wrappers. (5) At the place of installation of static electricity discharges the cover must be placed to not damage the dischargers. (6) Fixing rubber strings of the fuselage, fin and rudder covers must always be placed on the aircraft left side. (7) Covers with the fixing holes must always be up (the overlapping of covers of the fin and the rear section of the fuselage). (8) Engine covers must overlap the propeller covers. NOTE: The fixing clips and rings of individual cover have been sewn sections. (9) Using the stairs, fit on the aircraft individual covers – see fig.3 in following sequence
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MAINTENANCE MANUAL (10) The left wing covers (B 596 397 L). After fixing and enveloping on the wing lower side clamp by means of clips and rings. (11) Tip cover (B 596 451 L) or the left cover of terminal fuel tank (B 596 338 L). After fixing and enveloping join together by means of clips and rings. NOTE:
Terminal fuel tank cover is to be fixed in case of installation of terminal fuel tank only.
(12) Wing cover left fuselage (B 096 076 L). After fixing and enveloping joint together with the help of clips and rings on the wing underside. (13) Right wing cover (B 526 397 P). After fixing and enveloping joint together by means of clips and rings on the wing bottom side. (14) Tip cover (B 596 451 N) or right cover of terminal fuel tank (B 596 338 P). After fixing and enveloping joint the cover together by means of clips and rings. NOTE:
Terminal fuel tank cover is to be fixed in case of installation of terminal fuel tank only.
(15) Cover of wing right fuselage (B 096 076 P). After fixing and enveloping joint together by means of clips and rings on wing bottom side. (16) Cover of the propeller blades (B 596 398 N) 8 pcs, 4 pcs for each propeller. After putting on, fix by means of twill strips (after setting the right and left propeller cone). (17) The cover of the propeller cone (B 596 400 N) 2 pcs, one piece on each propeller. After fixing, carry out locking by means of clips and rings and by the clips of left and right engine cover. (18) Cover of the propeller blades with the strap (B 596 399 N) 2pcs, 1pcs on each propeller. After fixing, lock and attach by two straps over the left and right exhaust of the left and right engine by means of dips and strips. (19) The left engine cover (B 096 077 L). After fixing and enveloping joint together on the bottom side by means of clips and rings. (20) The right engine cover (B 096 077 P). After fixing and enveloping joint together on the bottom side by means of clips and rings. (21) The flight compartment cover (B 596 405 N). After proper fixing and enveloping joint together on the fuselage left side by means of clips and rings. (22) The fuselage rear section cover (B 096 078 N). After proper fixing and enveloping the left and right fuselage side, join together by means of clips and rings. (23) Fuselage cover central section (B 096 075 N). After proper fixing and enveloping joint together on the fuselage left side by means of clips and rings. (24) Antenna cover (L410M.9322-37) 2 pcs. After proper fixing secure by means of clips and rings, sewn in the upper section of the cover for the fuselage rear section. (25) Left cover of the tail plane (B 096 080 L). Fixing – see point 27 EFFECTIVITY ALL
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MAINTENANCE MANUAL (26) Right cover of the tail plane (B 096 080 P). Fixing – see point 27 (27) Tail plane cover (B 096 081 N). After proper fixing and enveloping of the tail plane and the rudder, joint together on the fin left side by clips and rings. Further fix the cover to the fin together with the upper and lower section of the right and left tail plane covers and to the upper section of the fuselage rear section cover within the zone of the fin by interlacing the loops of the fuselage cover straps through the cover holes of the tail plane and by their interlacing within the upper and lower section. The ends are to be knotted or the last eyes of interlaced straps are to be passed through the locking strips of the fuselage and tail plane covers. (28) The cover of the right landing gear nacelle (B 596 396 P). After proper fixing and enveloping joint together on the fuselage bottom side means of straps inserted to the clips of the left nacelle cover (on the cover rings of the right nacelle), then lock the remaining overlapping strips of the left and right nacelle by means of clips and rings. This is to be done using the assembly bogie, placed under the fuselage. (29) Cover of the left landing gear nacelle (B 596 396 L). Fixing – see point 28 (30) Cover the nose landing gear (B 096 072 N). After proper fixing and enveloping joint together by means of clips and rings. (31) Wheel covers of the main landing gear (B 096 085 N). After proper fixing secure them against shifting by means of clips and rings. (30) Check the fixed covers on the aircraft. Remove found out defects. (31) Remove and store the rear strut of the aircraft. (32) Take away used fixtures (stairs, bogie from below the fuselage, etc.) to store.
7. Removal of the devices from the aircraft after parking A.
Fixture, Test and Support Equipment
B 097 365 N Stairs L410.9615 Assembly bogie L410.9620 Rear strut of the fuselage
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
010.10.00.G Routine
E.
Procedures (1) Prepare near to the aircraft:
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Stairs B 097 365 N to the left and right wing
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The assembly bogie L410.9615 under the fuselage
Stairs B 097 365 N to the tail planes (if available, also extension stairs according to the airfield outfit) may be used
NOTE:
If a mobile assembly equipment is available at the airfield, then it is possible to use the set of assembly platforms consisting of:
platforms below the left and right wing (within the zone of the engine nacelles) platforms below wing ends platforms for the tail planes Application of high- lift hydraulic platform is possible. (2) Set the rear fuselage strut L410.9620 on the rear fuselage section (3) During the cover removal care must be paid to the zone of installed static electricity dischargers to not damage them. (4) Sequence of technological operations assume the cover removal from all over the aircraft. If some covers and blockings hove not been installed on the aircraft, the relevant operation is to be omitted. (5) Remove the covers of the main landing gear wheels. (6) Remove the covers from the nose landing gear. (7) Remove the covers of the landing gear nacelles. (8) Release the cover of the fin from the covers of tail planes and fuselage rear section and take it away. (9) Remove the covers of tail planes. (10) Remove the cover from the antenna. (11) Remove the cover of fuselage centre section. (12) Remove the cover of fuselage rear section (13) Remove the flight compartment cover (14) Remove the cover of the right engine (15) Remove the cover of the left engine NOTE:
When the ambient temperature is below -20°C, the engines covers are only removed after engines are heated-up with hot air.
(16) Remove the cover of propeller cones (17) Remove the cover of propeller blades (18) Remove the wing – fuselage cover, right. (19) Remove the cover of the right tip or the cover of wing tip fuel tank, right. EFFECTIVITY ALL
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MAINTENANCE MANUAL (20) Remove the wing cover, right. (21) Remove the cover of wing – fuselage, left. (22) Remove the cover of the left tip or the cover of wing tip fuel tank, left. (23) Remove the cover of the left wing. (24) Remove the propeller blocking. (25) Remove the cover of air inlet to the engine. (26) Remove the exhaust covers. (27) Remove the Pitot tube covers. (28) Remove the blinds of static sensors covers. (29) Remove the locking clamps of the ailerons. (30) Remove the blocking of the elevator. (31) Remove the rudder blocking. (32) Remove the grounding cable from the nose landing gear. (33) Take away the stairs (assembly platforms) and the assembly bogie. (34) Dismantle the fuselage rear strut L410.9620 from the fuselage rear section. (35) Take away all canvas, cover and blocking devices, removed from the aircraft.
8. Removal of the blocking strut of the aircraft control column A.
Fixture, test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced Information
010.10.00.H Routine
E.
Procedures (1) Release the nut on the column of the blocking strut. (2) Remove the lower end of the strut from the grooves on the pedal levers and remove the strut from the control lever. (3) Check the free motion of rudder and aileron control. The control must operate without any jamming within the entire range of deviations. (4) Work close up (5) Close the lid between the left and right pedal. (6) Take away the blocking strut.
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MOORING DESCRIPTION AND OPERATION 1. General The aircraft mooring is to be carried out, when the wind with gusts exceeding 20 m/s (72 km/h) are assumed. For aircraft mooring the following versions of the mooring equipment are used: A.
Version (refer to the Fig. 1 and 2) No.
B.
Type (Dwg. No)
Qty
1.
Mooring device of nose wheel
B 596 671 N
1
2.
Mooring device for the wing
B 596 670 N
2
3.
Additional rear mooring device
B 596 673 N
2
4.
Additional front mooring device
B 596 672 N
2
5.
Mooring device of tail unit
B 596 674 N
1
6.
Mooring peg
LDN 6911
12
Version - B 598 938 N Mooring kit (refer to the Fig. 3 to 5) No.
Name
Type (Dwg. No)
Qty
1.
Mooring device for the wing
B 598 942 N
2
2.
Mooring device of main landing gear
B 598 950 N
2
3.
Mooring device of nose wheel
B 598 945 N
1
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Name
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MAINTENANCE MANUAL
FIG. 1
AIRCRAFT MOORING (A-VERSION) (1) Mooring device of nose wheel B 596 671 N; (2) Mooring device for the wing B 596 670 N; (3) Additional rear mooring device B 596 673 N; (4) Additional front mooring device B 596 672 N; (5) Mooring device of tail unit B 596 674 N
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FIG. 2
MOORING DEVICE (A-VERSION) (1) Mooring device of nose wheel B 596 671 N; (2) Mooring device for the wing B 596 670 N; (3) Additional rear mooring device B 596 673 N; (4) Additional front mooring device B 596 672 N; (5) Mooring device of tail unit B 596 674 N; (6) Cable; (7) Turnbuckle with chain; (8) Pin; (9) Pin; (10) Bracket; (11) Fork; (12) Screw; (13) Fork; (14) Side plate; (15) Nut; (16) Securing pin; (17) Pin; (18) Nut; (19) LDN 6911 mooring peg
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MAINTENANCE MANUAL
FIG. 3
AIRCRAFT MOORING (B-VERSION) - B 598 938 N MOORING KIT (1) Mooring device for the wing B 598 942 N; (2) Mooring device of main landing gear B 598 950 N; (3) Mooring device of nose wheel B 598 945 N
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MAINTENANCE MANUAL Legend for Fig. 4: (1) Mooring device for the wing B 598 942 N; (2) Mooring device of main landing gear B 598 950 N; (3) Mooring device of nose wheel B 598 945 N, (4) Mooring belt, (5) Bracket, (6) GN113.3-8-20 Securing pin, (7) 1.4x200 Cable, (8) GN113.3-10-35 Securing pin, (9) Mooring belt, (10) Bracket with the pulley, (11) Hook, (12) Pin, (13) Bracket, (14) Pin with eye, (15) Bush with eye, (16) Mooring belt, (17) GN113.3-10-40 Securing pin, (18) Shortening clamp A, B, C, D - Mooring points - refer to the Fig. 3
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FIG. 4
MOORING DEVICE (B-VERSION) - B 598 938 N MOORING KIT For Legend see previous page
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FIG. 5
MOORING POINTS (B-VERSION) - B 598 938 N MOORING KIT All dimensions in [mm] Mooring points / required loading capacity (breaking forces) Point A B C D
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Longitudinal [N]
Vertical [N]
Lateral [N]
Total [N]
5000 AFT
5000 UP
5000 LEFT / RIGHT
8660 25940
LEFT / RIGHT
18000 AFT
18000 UP
5000 LEFT / RIGHT
LEFT
5000 FWD / AFT
15000 UP
15000 LEFT / RIGHT
RIGHT
5000 FWD / AFT
15000 UP
15000 LEFT / RIGHT
LEFT / RIGHT
18000 FWD
18000 UP
5000 LEFT / RIGHT
56270 25240
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MOORING SERVICING 1. Aircraft mooring A.
Fixture, Test and Support Equipment
A-Version: B 596 671 N Mooring device of nose wheel (1 pc) B 596 670 N Mooring device for wing (2 pcs) B 596 673 N Additional rear mooring device (2 pcs) B 596 672 N Additional front mooring device (2 pcs) B 596 674 N Mooring device of tail unit (1 pc) LDN 6911 Mooring peg (12 pcs) B-Version: B 598 938 N Mooring kit
B.
Materials
Not applicable
C. Tools
Spanners of relevant size from the tool kit
D. Referenced Information
010.20.00.A Routine
E.
Procedures (1) A-Version (a) Make sure that the aircraft has been secured by chocks against displacement. (b) The installed mooring device must not be loosened. (c) Screw into the ground the mooring pegs acc. to dimension given in Fig. 1. (d) Install the bracket of the mooring device for wing (10) - see Fig. 2 - into mooring eyes on the wing flap suspension on wing near rib No. 15 and secure it by means of pins (9). Insert the mooring chain into the mooring peg and adjust the tension by means of the turnbuckle (7). Secure the turnbuckle by means of the eye. (e) Take the mooring device of nose wheel (1) apart to two sections pin (8). Insert journal of the mooring device into the hole of the nose landing gear leg shock absorber and after placing the second section of mooring device, secure it by means of pin. Insert the chain of the mooring device into mooring peg and adjust the right cable tension by means of turnbuckle (7). Secure the turnbuckle with the eye. (f)
Take the additional front mooring device (4) apart into two sections by removing the nut (15) and the side plate (14). Insert fork (13) into the hole of the main landing gear leg, install
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MAINTENANCE MANUAL side plate (14) and screw in the nut (15). Insert the chain of the mooring device into the mooring peg and adjust the right cable tension by means of the turnbuckle (7). Secure the turnbuckle with the eye. (g) Loosen the nut (18) and remove the screw (12) from the additional rear mooring device (3). Position fork (11) against the hole of the main landing gear leg shock absorber. Insert the screw (12) into the hole and tighten the nut (18). Insert the chain of the mooring device into the mooring peg and adjust the right cable tension by means of the turnbuckle (7). Secure the turnbuckle with the eye. (h) Take the mooring device of the tail unit (5) apart into two sections by removing the securing pin (16). Insert the pin (17) into the hole of the lower fin, install the second section of the mooring device and secure it with securing pin (16). Insert the chain of the mooring device into the mooring peg and adjust the right cable sensitivity by means of turnbuckle (7). Secure the turnbuckle with the eye. (2) B-Version B 598 938 N Mooring kit (a) Make sure that the aircraft has been secured by chocks against displacement. (b) The installed mooring device must not be loosened. (c) Prepare the mooring points according to the dimensions given in Fig. 3 and 5. (d) Install the bracket of the mooring device for wing (5) - see Fig. 4 - into mooring eyes on the wing flap suspension on wing near rib No. 15 and secure it by means of pins (6). Insert the mooring hook into the mooring point on the ground and adjust the belt (4) tension by means of the shortening clamp (18). (e) Dismount the mooring device of nose wheel (3) to the two sections by means of the pin (17). Insert the pin with the eye (14) of the mooring device into the hole of the nose landing gear leg shock absorber and after placing the second section of mooring device (and bush (15)), secure it by means of pin (17). Insert the mooring hook into the mooring point on the ground and adjust the belt (16) tension by means of the shortening clamp (18). (f)
Dismount the mooring device of the main landing gear (2) to the two sections by means of the pin (8). Insert pin (12) into the hole of the main landing gear leg. Install the bracket (13) into the fork of the pin and secure it by means the pin (8). Insert the mooring hook into the mooring point on the ground and adjust the belt (9) tension by means of the shortening clamp (18).
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2. Removal of the aircraft mooring device A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners of corresponding size from the tool kit
D. Referenced Information
010.20.00.B Routine
E.
Procedures (1) A-Version (a) Make sure that the aircraft has been secured with chocks against displacement. (b) Loosen the turnbuckle of the mooring device of the nose wheel (1) - see Fig. 2 and remove the chains from the mooring peg eyes. Remove the pin (8) from the journal of the mooring device and remove the journal from the hole of the nose landing gear leg shock absorber. Connect the removed mooring device and secure it with the pin. (c) Loosen the turnbuckle of the mooring device for the wing and remove chains from the mooring peg eyes. Remove the pin (9) and bracket (10) of the mooring device for the wing from the mooring eyes of the wing flap suspension. (d) Loosen the turnbuckle of the additional front mooring device (4) and remove chains from the mooring peg eyes. Loosen the nut (15) and remove the side plate (14) and detach the fork (13) from the hole of the main landing gear leg. Connect the removed mooring device again. (e) Loosen the turnbuckle of the additional rear mooring device (3) and remove chains from the mooring peg eyes. Loosen the nut (18), detach the screw (12) from the hole of the main landing gear shock absorber and detach the fork (11). Connect the removed mooring device again. (f)
Loosen the turnbuckle of the mooring device of the tail unit (5) and remove chains from the mooring peg eyes. Remove the securing pin (16) and detach the pin (17) from the hole of the lower fin.
(g) Remove all 12 pcs of mooring pegs from ground. (h) Take away the mooring pegs and the mooring device.
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MAINTENANCE MANUAL (2) B-Version B 598 938 N Mooring kit (a) Make sure that the aircraft has been secured with chocks against displacement. (b) Loosen the mooring belt (16) of the mooring device of the nose wheel (3) - see Fig. 4 - and remove the hook from the mooring point. Remove the pin (17) and remove the pin (14) from the hole of the nose landing gear leg shock absorber. Connect the removed mooring device and secure it with the pin (17). (c) Loosen the mooring belts (4) of the mooring device of the wing (1) - see Fig. 4 - and remove the hooks from the mooring points. Remove the pin (6) and remove the bracket (5) of the mooring device from the hole of the hinges of the wing flaps. (d) Loosen the mooring belt (9) of the mooring device of the main landing gear (2) - see Fig. 4 and remove the hook (11) from the mooring point. Remove the pin (8) and remove the pin (12) from the hole of the main landing gear leg. Connect the removed mooring device and secure it with the pin (8). (e) Take away the mooring pegs and the mooring device.
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CHAPTER
PLACARDS AND MARKINGS
MAINTENANCE MANUAL
CHAPTER 11 PLACARDS AND MARKINGS LIST OF EFFECTIVE PAGES Chapter, Section, Subject
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Contents
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CHAPTER 11 PLACARDS AND MARKINGS RECORD OF REVISIONS Rev. No.
Chapter, Section, Subject
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
MM is reissued on Nov 1/11. This contains revisions from No. 1 to No. 4 5
6
011-List of Effective Pages
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011-List of Revisions
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011-Contents
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011.20.00
1 to 4
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011.30.00
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011-List of Effective Pages
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011-List of Revisions
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011.20.00
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EFFECTIVITY: ALL
L410UVP-E/208d
Dec 10/14
L410UVP-E/225d
Mar 30/16
011-RECORD OF REVISIONS Page: 1 Mar 30/16
MAINTENANCE MANUAL
Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
011-RECORD OF REVISIONS Page: 2 Nov 1/11
MAINTENANCE MANUAL
Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
011-RECORD OF REVISIONS Page: 3 Nov 1/11
MAINTENANCE MANUAL
Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
011-RECORD OF REVISIONS Page: 4 Nov 1/11
MAINTENANCE MANUAL
CHAPTER 11 PLACARDS AND MARKINGS RECORD OF TEMPORARY REVISIONS Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
011-RECORD OF TEM. REVISIONS Page: 1 Nov 1/11
MAINTENANCE MANUAL
Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
011-RECORD OF TEM. REVISIONS Page: 2 Nov 1/11
MAINTENANCE MANUAL
CHAPTER 11 PLACARDS AND MARKINGS CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
EXTERIOR PLACARDS AND MARKINGS Description and Operation Markings
011.20.00
1 1 1
ALL
INTERIOR PLACARDS AND MARKINGS Description and Operation Placard and marking Identification of piping and hoses of individual assemblies Identification of hoses from the production and guarantee date point of view Identification of the PTFE hoses
011.30.00
1 1 1 3
ALL
EFFECTIVITY ALL
5 6
011-CONTENTS Page: 1 Dec 10/14
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
011-CONTENTS Page: 2 Nov 1/11
MAINTENANCE MANUAL
EXTERIOR PLACARDS AND MARKINGS DESCRIPTION AND OPERATION 1. MARKINGS Pos.
Fig. No.
1
1
TURN TWICE THROUGH 360 DEG TO RELEASE LOCKS (if used)
Concerns locks of covers for access to board batteries and el-radio equipment. Locks are releasable with a screwdriver with rounded edge
2
1
28 V 500 A
Ground electric installation socket
3
1, 2
OIL
Access to engine oil filter
4
1, 2
WATER INJECTION COMPRESSOR WASH
Access to three-way cock for “engine water injection” or “compressor wash”.
5
1
GROUND HYDR. SOURCE 14.7 MPa (2.132 PS) COMPRESSED AIR GROUND SOURCE 0.54 MPa (78 PSI) HYDRAULIC TANK GAUGE PRESSURE
Access to ground hydraulic source connection and ground pressure air connection for hydraulic tank pressurizing
6
1
Red cross or green cross
First-aid box location
7
1
CUT HERE TO BREAK IN
Area destined for forced aircraft entry (after emergency landing to break in)
8
1, 2
VHF AERIAL (if installed)
Marking of VHF antenna
9
1, 4
SUPPORT HERE
Supporting jack point for the rear strut
10
1
1. PUSH or 1. PUSH AND HOLD
Entrance (Main) door opening and shutting
11
1
2. TURN
Entrance (Main) door opening and shutting
12
1
CLOSED
Entrance (Main) door opening and shutting
13
1
OPEN
Entrance (Main) door opening and shutting
14
1
NITROGEN 1.47 MPa
Brakes accumulator filling
15
2, 3
DO NOT STEP HERE
Area not allowed to be stepped on by feet
16
1, 4
NITROGEN 4.9 MPa
Hydraulic accumulator filling with nitrogen
17
1, 2
Note
420
+30
kPa
Main wheel tyre pressure
+30
kPa
Nose wheel tyre pressure
18
1
420
19
1
INTERCOM (if installed)
Access for connection of ground personnel headphones
20
1, 4
FUEL DRAIN
Access to fuel tanks drain valves
21
1, 2
PRESS FIRE EXTINGUISHING BY GROUND Access for extinguishing with ground MEANS extinguishers
22
2
OPEN
Emergency exit door opening and shutting
23
2
TURN
Emergency exit door opening and shutting
24
2
CLOSED
Emergency exit door opening and shutting
EFFECTIVITY ALL
Inscription reading
011.20.00 Page: 1 Mar 30/16
MAINTENANCE MANUAL
25
1, 2
Red circle
Reference leveling point No. 2 (for calculation of the center of gravity position-see section 008.10.00)
26
2
DISTILLED WATER MAX. 10 l (2.6 US gall) or DISTILLED WATER MAX. 22.5 l (5.94 US gall)
Access to tank water filler for engine water injection
27
1, 2
JET FUEL
Fuel for engines
28
1, 2
FUEL 200 l(158 kg) (53 US gall) MAX.PRESS.0.39 MPa (56PSI)
Fuel for engines
4 kp/cm2 29
3
FUEL 628 l (496kg) (166 US gall)
Fuel for engines
MAX. PRESS. 0.39 MPa (56 PSI) 4 kp/cm2 30
3
kp/cm2)
Access to hydraulic fluid level checking neck
31
3
AIR 0.49 MPa (5
32
4
OIL DRAIN
Access to engine oil drain valve
33
4
DO NOT PRESS HERE
Covering of marked-off area is not allowed to be pressed in order not to cause its deformation
34
4
HYDRAULIC FLUID DRAINAGE AND FILLING
Access to hydraulic tank drain valve
35
1
Aircraft production number (if installed)
36
1, 2
1.PUSH AND HOLD (if installed)
Emergency exits opening and shutting
37
1, 2
2.TURN (if installed)
Emergency exits opening and shutting
38
1, 2
3.PULL (if installed)
Emergency exits opening and shutting
39
1
Identification label (if installed)
Identification label denotes imatriculation sign. type production No. of the aircraft.
40
1
ELT (if installed)
41
1
HYDRAULIC TANK GAUGE PRESSURE
Location of hydraulic gauge
42
2
DANGER-PROPELLER (if used)
Front emergency
43
1, 2
Red edging (if used)
Marking zone anti-ice belt
44
1
BEFORE CLOSING THE DOOR UNLOCK THE GAS SPRING
At the Main door (if gas strut is installed)
EFFECTIVITY ALL
HYDRAULIC LIQUID
Access to the connection for checking of leading edges pneumatic deicing device
011.20.00 Page: 2 Dec 10/14
MAINTENANCE MANUAL
FIG. 1
MARKINGS ON THE AIRCRAFT-LEFT-HAND SIDE A - transition skin between the wing and fuselage B - passenger compartment emergency exit C - entrance (main) door
EFFECTIVITY ALL
011.20.00 Page: 3 Dec 10/14
MAINTENANCE MANUAL
FIG. 2
MARKINGS ON THE AIRCRAFT-RIGHT-HAND SIDE A - right - hand engine nacelle-view from the fuselage side B - transition skin between the wing and the fuselage C - passenger compartment emergency exit door D - pilot's cockpit emergency exit door NOTE:
The Pos. 15 is valid only for L410 UVP-E airplane version without of the emergency exits in passenger’s cabin.
EFFECTIVITY ALL
011.20.00 Page: 4 Dec 10/14
MAINTENANCE MANUAL
FIG. 3
MARKINGS ON THE AIRCRAFT – TOP VIEW
EFFECTIVITY ALL
011.20.00 Page: 5 Nov 1/11
MAINTENANCE MANUAL
FIG. 4
MARKINGS ON THE AIRCRAFT – BOTTOM VIEW
EFFECTIVITY ALL
011.20.00 Page: 6 Nov 1/11
MAINTENANCE MANUAL LANGUAGE MUTATIONS CONVERSION TABLES
Abbreviation meaning is as Follows: En-English; Cz-Czech; Ru-Russian; De-German; Hu-Hungarian; Es-Spanish; Fr-French; Pl-Polish; Pt-Portuguese Pos.
Mutation
INSCRIPTION READING
1
En
TURN TWICE THROUGH 360 DEG TO RELEASE LOCKS
Cz
ZÁMKY UVOLŇOVAT OTOČENÍM O 2x360°
Ru
ЗАМКИ ОТКРЫВАТЬ ПОВОРОТОМ НА 2х360°
De
SCHNELLVERSCHLÜSSE ÖFFNEN 2x360°
Hu
A GYORSZÁRAKAT 2x360° ÉLFORGATÁSSAL NYISSUK
Es
PARA SOLTAR LOS CIERRES GIRAR 2 VECES 360°
Fr
SERRURES A DÉBLOQUER PAR TOURNER 2x360°
Pl
OTWIERAĆ ZAMKI OBRÓCIĆ O 2x360°
Pt
SOLTAR A FECHADURA GIRAR 2-VEZES 360°
En
28V 500A
Cz
28V 500A
Ru
28V 500A
De
28V 500A
Hu
28V 500A
Es
28V 500A
Fr
28V 500A
Pl
28V 500A
Pt
28V 500A
En
OIL
Cz
OLEJ
Ru
МАСЛО
De
SS
Hu
OLAJ
Es
ACEITE
Fr
HUILE
Pl
OLEJ
Pt
ÓLEO
2
3
EFFECTIVITY ALL
011.20.00 Page: 7 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
4
En
WATER INJECTION COMPRESSOR WASH
Cz
VSTŘIK VODY DO PROMÍVÁNÍ
Ru
ВПРЫСК ВОДЫ ПРОМЫВКА
De
SPULUNG WASSEREINSPRITZUNG
Hu
VÍZBEFECSKENDEZÉS KOMPRESSZOR ÁTMOSÁS
Es
INYECCION DE AGUA PARA LAVADO DEL COMPRESOR
Fr
INJECTION D’EAU LAVAGE
Pl
WTRYSK WODY PŁUKANIE
Pt
INJECẬO DE ÁQUA LAVAGEM
En
GROUND HYDR. SOURCE 14,7MPa (2,132 psi) COMPRESSED AIR GROUND SOURCE 0,54 MPa (78 psi)
5
Cz
Ru
De
Hu
Es
PŘÍPOJKA VNĚJŠÍHO ZDROJE HYDRAULIKY 14,7 MPa (150 kp/cm2) PŘÍPOJKA VNĚJŠÍHO ZDORJE VZDUCHU 0,54 MPa (5,5 kp/cm2) АЕРОДРОМНОЕ ПИТАНИЕ ГИДРОЖИДКОСТИ 14,7Мпа (150 кг/см2) АЕРОДРОМНОЕ ПИТАНИЕ ВОЗДУХА 0,54 МПа (5,5 кг/см2) HYDRAULIKAUSSENBORDANSCHLUSS 14,7 MPa (150 kp/cm2) LUFTAUSSENBORD ANSCHLUSS 0,54 MPa (5,5 kp/cm2) FÖLDI HYDRAULIKA TÁPLÁLÁS 14,7 MPa (150kp/cm2) SÜR. LEV. FÖLDI TÁPLÁLÁS 0,54 MPa (5,5 kp/cm2) FUENTE HIDRAULICA EN TIERRA 150 kp/cm2 (14,7 MPa) (2,132 psi) FUENTE DE AIRE COMPRIMIDO EN TIERRA 5,5 kp/cm2 (0,54 MPa) (78 psi) BRANCHEMENT A SOURCE AU SOL LIQUIDE HYDRAULIQUE 14,7 MPa
Fr
(150 kp/cm2) BRANCHEMENT A SOURCE AU SOL D’AIR 0,54 MPa (5,5 kp/cm2)
Pl
7
EFFECTIVITY ALL
ZASILANIE HYDRAULICZNE ZEWNETRZNE LOTNISKOWE 14,7 MPa (150 kp/cm2) ZASILANIE LOTNISKOWE ZEWNETRZNE CIŚNIENIE POWIETRZA 0,54 MPa
Pt
JUNCẬO DA FONTE DE FORA AR 0,54 MPa/ 5,5 kP/cm2
En
CUT HERE TO BREAK IN
Cz
MÍSTO PRO NÁSILNÉ VNIKNUTÍ
Ru
ВСКРЫВАТЬ В ЕТОЙ ЗОНЕ
De
IM NOTFALL ZONE EINDRÜCKEN
Hu
VÉSZHELYZEBTEN ITT BETÖRNI
Es
CORTAR AQUI PARA INGRESAR
Fr
ZONE DE PÉNÉTRATION
Pl
CIAĆ W TYM MIEJSCU
Pt
CORTE AQUI PARA ACESSO INTERNO EM EMERGÉNCIA
011.20.00 Page: 8 Mar 30/16
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
8
En
VHF AERIAL
Cz
ANTÉNA UKV
Ru
АНТЕННА УКВ
De
-
Hu
URH ANTENNA
Es
ANTENA VHF
Fr
AÉRIEN VHF
Pl
ANTENA UKF
Pt
ANTENA UHF
En
SUPPORT HERE
Cz
ZDE PODEPŘÍT
Ru
ТОЧКА ОПОРЫ
De
AUFBOCKPUNKT
Hu
ALÁTÁMASZTÁSI PONT
Es
APOYAR AQUI
Fr
SUPPORTER ICI
Pl
TU PODPIERAC
Pt
APOIAR AQUI
En
1.PUSH
Cz
1.STISKNOUT
Ru
1.НАЖАТЬ
De
-
Hu
1.NYOMNI
Es
1.PRESIONAR
Fr
SERRER 1x
Pl
1.NACISKAC
Pt
1.APERTAR
En
2.TURN
Cz
2.OTOČIT
Ru
2.ПОВЕРНУТЬ
De
2.DREHEN
Hu
2.FORDÍTSA EL
Es
2-GIRAR
Fr
TOURNER 2x
Pl
2.PRZEKRECIC
Pt
2-GIRE
9
10
11
EFFECTIVITY ALL
011.20.00 Page: 9 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
12
En
CLOSED
Cz
ZAVŘENO
Ru
ЗАКПЫТО
De
ZU
Hu
ZÁRVA
Es
CERRADO
Fr
FERMÉ
Pl
ZAMKNIETE
Pt
FECHADA
En
OPEN
Cz
OTEVŘENO
Ru
ОТКРЫТО
De
AUF
Hu
NYITVA
Es
ABIERTO
Fr
OUVERT
Pl
OTWARTE
Pt
ABERTA
En
NITROGEN 1,47 MPa (213 psi)
Cz
DUSÍK 1,47 MPa (15 kp/cm2)
Ru
АЗОТ 1,47 МПа (15кГ/см2)
De
N2 1,47 MPa (15 kp/cm2)
Hu
NITROGÉN 1,47 MPa (15 kp/cm2)
Es
NITROGENO 15 kp/cm2 (1,47 MPa) (213 psi)
Fr
NITROGÉNE 1,47 MPa (15 kp/cm2)
Pl
CIŚNIENIE AZOTU 1,47 MPa
Pt
NITROGỆNIO 1,47MPa (15 kp/cm2)
En
DO NOT STEP HERE
Cz
ZDE NEVSTUPOVAT
Ru
НЕ НАСТУПАТЬ
De
NICHT BETRETEN
Hu
RÁLÉPNI TILOS
Es
NO PISAR AQUI
Fr
NE PAS MONTER ICI
Pl
TU NIE STAWAČ
Pt
NẬO PISE AQUI
13
14
15
EFFECTIVITY ALL
011.20.00 Page: 10 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
16
En
NITROGEN 4,9 MPa (710 psi)
Cz
DUSÍK 4,9 MPa (50 kp/cm2)
Ru
АЗОТ 4,9 МПа (50 кГ/см2)
De
N2 4,9 MPa (50 kp/cm2)
Hu
NITROGÉN 4,9 MPa (50 kp/cm2)
Es
NITROGENO 50 kp/cm2 (4,9 MPa) (710 psi)
Fr
NITROGÉNE 4,9 MPa (50 kp/cm2)
Pl
CIŚNIENIE AZOTU 4,9 MPa
Pt
NITROGỆNIO 4,9 MPa (50 kp/cm2)
En
420+30 kPa (61 +4,4 psi)
Cz
420+30 kPa
Ru
420+30 кПа (4,3-0,3 кГ/см2)
De
420+30 kPa
Hu
420+30 kPa
Es
420+30 kPa (61 +4,4 psi)
Fr
420+30 kPa
Pl
420+30 kPa
Pt
420+30 kPa
En
INTERCOM
Cz
PALUBNÍ TELEFON
Ru
-
De
-
Hu
INTERCOM TELEFON
Es
INTERCOMUNICADOR
Fr
APPAREIL D’ INTERCOMMUNICATION
Pl
POKŁADOWY TELEFON
Pt
INTERCOMUNICADOR
En
FUEL DRAIN
Cz
VÝPUST PALIVA
Ru
СЛИВ ТОПЛИВА
De
KS-ABLASS
Hu
TÜZELOANYAG LEERESZTÉS
Es
DRENAJE DE COMBUSTIBLE
Fr
VIDANGE DE COMBUSTIBLE
Pl
SPUST PALIWA
Pt
DRENO DE COMBUSTÍVEL
17, 18
19
20
EFFECTIVITY ALL
011.20.00 Page: 11 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
21
En
PRESS FIRE EXTINGUISHING BY GROUND MEANS
Cz
TLAČIT HAŠENÍ POZEMNÍMI PROSTŘEDKY
Ru
НАЖИМАТЬ ОГНЕТУШЕНИЕ ОТ НАЗЕМНЫХ СРЕДСТВ
De
DRUCKEN LOSCHEN MIT BODENMITTELN
Hu
TOLNI TUZOLTÁS FÖLDI BERENDEZÉSEKKEL
Es
EMPLEAR MEDIO EXTERIORES PARA EXTINCION DE INCENDIO
Fr
PRESSER EXTINCTION PAR MOVENS AU SOL
Pl
NACISKAĆ GASZENIE Z NAZIEMNYCH URZADZEŃ
Pt
EMPURRE ACESSO P/COMBATER FOGO
En
OPEN
Cz
OTEVŘENO
Ru
ОТКРЫТО
De
AUF
Hu
NYITVA
Es
ABIERTO
Fr
OUVERT
Pl
OTWARTE
Pt
ABERTA
En
TURN
Cz
OTOČIT
Ru
ПОВЕРНУТЬ
De
DREHEN
Hu
FORDÍTSA EL
Es
GIRAR
Fr
TOURNER
Pl
PRZEKRECIC
Pt
GIRE
En
CLOSED
Cz
ZAVŘENO
Ru
ЗАКПЫТО
De
ZU
Hu
ZÁRVA
Es
CERRADO
Fr
FERMÉ
Pl
ZAMKNIETE
Pt
FECHADA
22
23
24
EFFECTIVITY ALL
011.20.00 Page: 12 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
26a
En
DISTILLED WATER MAX. 10 l (2.6 U.S. gal)
Cz
DESTILOVANÁ VODA NEJVÝŠE 10 l
Ru
ДИСТИЛЛ. ВОДА НЕ БОЛЕЕ 10 л
De
DEST. H2O MAX. 10 l
Hu
DESZTILLÁLT VÍZ MAX. 10 l
Es
AGUA DESTILADA MAX 10 LITROS (2,6 U.S. gal)
Fr
EAU DISTILLÉE MAXIMUM 10l
Pl
WODA DESTYLOWANA MAKS. 10l
Pt
A´GUA DESTILADA MÁXIMO 10 LITROS
En
DISTILLED WATER MAX. 22.5 l (5.94 U.S. gal)
Cz
DESTILOVANÁ VODA NEJVÝŠE 22.5 l
Ru
ДИСТИЛЛ. ВОДА НЕ БОЛЕЕ 22.5 л
De
DEST. H2O MAX. 22.5 l
Hu
DESZTILLÁLT VÍZ MAX. 22.5 l
Es
AGUA DESTILADA MAX 22.5 LITROS (5.94 U.S. gal)
Fr
EAU DISTILLÉE MAXIMUM 22.5l
Pl
WODA DESTYLOWANA MAKS. 22.5l
Pt
A´GUA DESTILADA MÁXIMO 22.5 LITROS
En
JET FUEL
Cz
LETECKÝ PETROLEJ
Ru
КЕРОСИН
De
KEROSIN
Hu
KEROZIN
Es
COMBUSTIBLE
Fr
KÉROSÉNE AÉRIEN
Pl
PALIWO
Pt
QUEROSENE DE AVIACẴO JET-A-1
En
FUEL 200 l (53 U.S. gal) (158 kg) 348 lb
Cz
PALIVO 200 l (158 kg)
Ru
ТОПЛИВО 200 л (158 кг)
De
KS 200 l (158 kg)
Hu
TÜZELOANYAG 200 liter (158 kg)
Es
COMBUSTIBLE 200 l (53 U.S.gal)
Fr
COMBUSTIBLE 200 (158 kg)
Pl
PALIWO 200 l (158 kg)
Pt
COMBUSTÍVEL: 200 l (158 kg)
26b
27
28
EFFECTIVITY ALL
011.20.00 Page: 13 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
29
En
Cz
Ru
De
Hu
Es
INSCRIPTION READING FUEL 628 l (166 U.S. gal) (496 kg) (1,094 lb) MAX. PRESS. 0.39 MPa (56 psi) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 PALIVO 628 l (496 kg) PLNÍCÍ TLAK MAX. 0,39 MPa (4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 ТОПЛИВО 628 л (496 кГ) ДАВЛЕНИЕ ПО Т.3. НЕ БОЛЕЕ 0,39 МПа (4 кГ/см2) Т-1, ТС-1, РТ, ПЛ6,ПЛ7,ЙЕТ А, ЙЕТ А-1, ПСМ 2 KS 628 l (496 kg) FULLDRUCK MAX. 0,39 MPa (4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 TÜZELOANYAG 628 LITER (496 kg) TŐLTONYOMÁS MAX. 0,39 MPa (4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 COMBUSTIBLE 628 l (166 U.S. gal) PRESION MAXIMA 4 kp/cm2 (0,39 MPa) (56 psi) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 COMBUSTIBLE 628 l (496 kg) PRESSION D’ADMISSION MAXIMUM 0,39 MPa
Fr
(4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2
Pl
Pt 30
31
EFFECTIVITY ALL
PALIWO 628 l (496 kg) CIŚNIENIE MAKSYMALNE 0,39 MPa (4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2 COMBUSTÍVEL: 628 l PRESSẴO MÁXIMA 0,39 MPa (4 kp/cm2) T-1, TS-1, RT, PL-6, PL-7, JET A, JET A-1, PSM 2
En
HYDRAULIC FLUID
Cz
HYDRAULICKÁ KAPALINA
Ru
ГИДРОЖИДКОСТ
De
HYDRAULIKOL
Hu
HIDRULIKUS FOLYADÉK
Es
LIQUIDO HIDRAULICO
Fr
LIQUIDE HYDRAULIQUE
Pl
PŁYN HYDRAULICZNY
Pt
FLUIDOS HYDRÁULICOS
En
AIR 0.49 MPa (71 psi)
Cz
VZDUCH 0,49 MPa (5 kp/cm2)
Ru
ВОЗДУХ 0,49 МПа (5 кГ/см2)
De
-
Hu
LEVEGO 0,49 Mpa
Es
AIRE 5 kp/cm2 (0,49 MPa) (71 psi)
Fr
AIR 0,49 MPa (5 kp/cm2)
Pl
CIŚNIENIE POWIETRZA 0,49 MPa
Pt
AR 0,49 MPa (5 kp/cm2)
011.20.00 Page: 14 Nov 1/11
MAINTENANCE MANUAL
Pos.
Mutation
INSCRIPTION READING
32
En
OIL DRAIN
Cz
VÝPUST OLEJE
Ru
СЛИВ МАСЛА
De
SS-ABLASS
Hu
OLAJLEERESZTÉS
Es
DRENAJE DE ACEITE
Fr
VIDANDE D’HUILE
Pl
SPUST OLEJU
Pt
DRENO DE ÓLEO
En
DO NOT PRESS HERE
Cz
ZDE NETLAČIT
Ru
ЗДЕСЬ НЕ НАЖИМАТЬ
De
NICHT DRuCKEN
Hu
ITT TOLNI TILOS
Es
NO EMPUJAR AQUI
Fr
NE PAS PRESSER ICI
Pl
TU NIE NACISKAĆ
Pt
NẴO PRIMA AQUI
En
HYDRAULIC FLUID DRAINAGE AND FILLING
Cz
VÝPUSŤ A PLNĚNÍ HYRAULIKY
Ru
СЛИВ И ЗАПРАВКА ГИДРОЖИДКОСТИ
De
AUSSENBORDANSCHLUSS
Hu
LEERESZTÉS ÉS FEL TŐLTÉS HIDR FOLYADÉKKAL
Es
DRENAJE Y LLENADO DE FLUIDO HIDRAULICO
Fr
VIDANGE ET REMPLISSAGE DE LIQUIDE HYDRAULIQUE
Pl
ZLEWANIE / NAPEŁNIANIE PŁYN HYDRAULICZNY
Pt
DRENAR PRESSẴO HIDRÁULICA
En
1. PUSH AND HOLD
Cz
1. STISKNOUT A DRŽET
Ru
-
De
1.DRUCKEN UND HALTEN
Hu
-
Es
1-PRESIONAR Y MANTENER
Fr
-
Pl
1.NACISNĄĆ I PRZYTRZYMAĆ
Pt
1. APERTE E MENTENHA
33
34
36
EFFECTIVITY ALL
011.20.00 Page: 15 Nov 1/11
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Pos.
Mutation
INSCRIPTION READING
37
En
2.TURN
Cz
2.OTOČIT
Ru
2.ПОВЕРНУТЬ
De
2.DREHEN
Hu
2.FORDÍTSA EL
Es
2.GIRAR
Fr
TOURNER 2x
Pl
2.PRZEKRECIC
Pt
2.GIRE
En
3. PULL
Cz
3. TÁHNOUT
Ru
-
De
3. ZIEHEN
Hu
-
Es
3.TIRAR
Fr
-
Pl
POCIĄGNĄĆ
Pt
3.PUXAR-PUXE
En
E.L.T.
Cz
NOUZOVÝ POLOHOVÝ RADIOMAJÁK
Ru
АВАРИЙНЫЙ РАДИОМАЯК МЕСТОНАХОЖДЕНИЯ
De
NOTFUNKBAKE DER LAGE P
Hu
VÉSZRÁDIÓ
Es Fr
E.L.T. E.L.T.
Pl
E.L.T.
Pt
E.L.T.
En
HYDRAULIC TANK GAUGE PRESSURE
Cz
PŘETLAK V HYDRAULICKÉ NÁDRŽI
Ru
ИЗБЫТ ДАВЛЮ В ГИДРОБАКЕ
De
UBERDRUCK IM HYDRAULIK
Hu
TÚLNYOMÁS A HIDRAULIKA TARTÁLYBAN
Es
SOBREPRESION EN TANQUE HIDRAULICO
Fr
SURPRAESSION DANS RESERVOIR HYDRAULIQUE
Pl
NADCIŚNIENIE W HYDRAULICZNYM BAKU
Pt
INDICADOR DE PRESSẴO HIDRÁULICA DO RESERVATÓRIO HIDRÁULICO
38
40
41
EFFECTIVITY ALL
011.20.00 Page: 16 Nov 1/11
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Pos.
Mutation
INSCRIPTION READING
42
En
DANGER-PROPELLER
Cz
NEBEZPEČÍ VRTULE
Ru
-
De
-
Hu
-
Es
PELIGRO-HÉLICE
Fr
-
Pl
-
Pt
PERIGO-HÉLICE
EFFECTIVITY ALL
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INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
011.20.00 Page: 18 Nov 1/11
MAINTENANCE MANUAL
INTERIOR PLACARDS AND MARKINGS DESCRIPTION AND OPERATION 1. Placard and marking Location
Reading
Note OPEN
Between 6th and 7th frames-at the door handle of the emergency exit
Serigraphy on upholstery panel
CLOSED Between 7th and 8th frames-at the door handle of the emergency exit Serigraphy on upholstery panel
Serigraphy on upholstery panel
OPEN All emergency exit handle covers
REMOVE
Between 7th and 8th frames near the emergency exit door
EXIT
Between 7th and 8th frames above emergency exit door 7th frame on the controls cover 21st frame 7th frame on the controls cover and on LH,RH side before the first seat row and on the front side of rest of each passenger seat
DO NOT EXIT IF PROPELLER IS ROTATING NO SMOKING LIFE-VEST UNDER YOUR SEAT
Organic glass printing (serigraphy) lighting inscription Made of red color on light yellow ground Organic glass printing (serigraphy) Label (serigraphy)
On 7th frame on controls cover
FASTEN SEAT BELTS
On 7th frame on controls cover
AXE
Organic glass printing (serigraphy)
PUSH TO CALL CREW
Organic glass printing (serigraphy) red letters on white material
Between 10th and 11th and 13th and 14th frames-upper right
16th frame-the main door FIRE EXTINGUISHER
Between 13th and 14th frames on LH and RH side above emergency exit door Above the main door
EFFECTIVITY ALL
Red color on ABS white material
EXIT
Lighted transparency
Red color (serigraphy) on the upholstery panel
Lighted transparency
(if installed) EXIT
Organic glass printing (serigraphy) lifting inscription
011.30.00 Page: 1 Nov 1/11
MAINTENANCE MANUAL
Location
Reading
Note CLOSED
Main door
Organic glass printing (serigraphy), coated with luminous material
OPEN PRESS
Cover on the main door Left rear side of Fuselage
Organic glass printing (serigraphy), coated with luminous material
Identification label denotes imatriculation sing, type and production No. of the aircraft (if installed) OXYGEN
19th frame
Metal label (serigraphy)
Organic glass printing (serigraphy)
On the ceiling opposite the rear baggage compartment
Label (serigraphy)
ELT LOCATED HERE In the rear baggage compartment
TOP SECTION LIMIT LOAD 60 kg BOTTOM SECTION LIMIT LOAD 90 kg
First-aid box cover
Metal printing (serigraphy)
Serigraphy on the box cover PULL
Side of baggage compartment
PULL
WC OCCUPIED or LAVATORY OCCUPIED (if installed) RETURN TO YOUR SEAR
Between 19th and 20th frames-on the ceiling in front of WC
(if installed)
21st frame WC door
Organic glass printing (serigraphy) lighting inscription
Acrylon printing (serigraphy) lighting inscription White organic glass printing with black color (serigraphy)
or LAVATORY (if installed) Passengers seat rear side (if installed)
1 4 7 10 13 or
On the entry door and all emergency exits
EFFECTIVITY ALL
2 5 8 11 14 16 18
3 6 9 12 15 17 19
(front seats)
Siphoflexe printing (engraved)
(rear seats) (rear seats) */
*/ if installed
LOCKED UNLOCKED
Organic glass printing (serigraphy) coated with luminous material
011.30.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL
Location
Reading
At emergency exits between frames No.13 and 14 on both sides of fuselage
CLOSED OPEN 1. REMOVE 2. PUSH AND HOLD 3. TURN 4. PUSH
Note Organic glass printing (serigraphy), coated with luminous material
(if installed)
NOTE:
Inscriptions and pilot-sign-labels in the flight compartment are indicated in the Airplane Flight Manual (AFM).
2. Identification of piping and hoses of individual assemblies To facilitate the assembly, dismantling and repairs of individual assembly groups of the aircraft, piping and hoses are marked with sticking color tapes. On the tapes, there are beside the colors also black painted geometrical symbols of individual assembly sort according to the table, shown below. On pipings, exposed to higher temperatures (where the tape would be not sticking properly), the identification is made with a paint. Piping system
Identification with self-sticking tape (normal temperature range)
Identification with paint (Raised temperatures)
light blue
light blue
chrome yellow
medium chrome yellow
Hydraulic system rings flow direction flow direction (black arrow in white field)
cherish red cherish red/rays
Fuel system
four stars low direction flow direction
EFFECTIVITY ALL
011.30.00 Page: 3 Nov 1/11
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Piping system
Identification with self-sticking tape (normal temperature range)
Identification with paint (Raised temperatures)
medium chrome yellow
medium chrome yellow Oil system
alternating squares
coffee brown
coffee brown
Fire extinguishing system rhombuses
Total and static pressure system: Pressure probe piping
light red light gray zip-sag line
Static pressure piping
light red light grey zip-sag line
Total pressure piping
light red light grey zip-sag line
Air-conditioning (heating)
EFFECTIVITY ALL
coffee brown light grey
011.30.00 Page: 4 Nov 1/11
MAINTENANCE MANUAL
3. Identification of hoses from the production and guarantee date point of view A.
The airframe manufacturer indicates on the hoses ail numbers with white paint according to standard ONL 3950 - see fig. 1. Assembly date of the hose on the aircraft (3) is carried out prior the proper hose assembly on the aircraft.
FIG.1
IDENTIFICATION OF HIGH PRESSURE HOSES (1) Date of production hose-tubing without connections; (2) Passport of the hose production series; (3) Date of the hose assembly on the aircraft; (4) Marking on the sleeve
B.
Beside the identification made by the airframe manufacturer, the hose is also indicated with the symbols of the hose material manufacturer, containing for example:
The hose according to the standard PND 21/432-83, CSN 635369 or CSN 635387: OPTIMIT
8/18.5
PND 21/432-83
3-81
Manufacturer
ID and OD
Standard number
Month and year of production
Pressure hoses-sort 62792401: 013
10
7/62
Hose sort
Manufacturer
ID
Month and year of production
Soviet made pressure hoses: 21 G6-150
k
247
8/78
Drawing number
Manufacturer
Series No.
Month and year of production
EFFECTIVITY ALL
62792401
011.30.00 Page: 5 Nov 1/11
MAINTENANCE MANUAL
C. Marking the hoses on the sleeves On the sleeves (armoring) of the hoses there are engraved the drawing number of the hose and the symbol corresponding to that of the assembly drawing, in which the hose is used. Engraved numbers on the sleeves are filled with red paint.
4. Identification of the PTFE hoses The hose manufacturer indicates on the PTFE hoses following information:
FIG.2
IDENTIFICATION OF PTFE HOSES MEDIUM
Mark about the type and direction of flowing medium – refer to the para 2 in this section
ID TAG
Mark on permanent tag: THT OSTRAVA CZ – Hose Manufacturer THT XXXXXX-X – Hose Manufacturer’s Dwg Number Customer P/N – Airplane Manufacturer’s Dwg Number PT (Mo and Year) – Date of Hose Material Production ASSY DATE (Qtr and Year) – Date of the hose assembling TSO C-75 IIIB-S/P – Hose Specification TSO number Pressure information - Operational Pressure
NOTE:
EFFECTIVITY ALL
Work procedure for check of the PFTE hoses is mentioned in section 012.10.00.
011.30.00 Page: 6 Dec 10/14
CHAPTER
SERVICING
MAINTENANCE MANUAL
CHAPTER 12 SERVICING LIST OF EFFECTIVE PAGES Chapter, Section, Subject
Page
Date
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Page
Date
Title page
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012-LIST OF EFFECTIVE PAGES Page: 2 Nov 20/15
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012-LIST OF EFFECTIVE PAGES Page: 4 Nov 1/11
MAINTENANCE MANUAL CHAPTER 12 SERVICING RECORD OF REVISIONS Rev. No.
Chapter, Section, Subject
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
MM is reissued on Nov 1/11. This contains revisions from No. 1 to No. 9 10
11
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L410UVP-E/145d
May 31/12
L410UVP-E/170d
Apr 5/13
L410UVP-E/196d
May 30/14
012-RECORD OF REVISIONS Page: 1 May 30/14
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Date of Revision
L410UVP-E/208d
Dec 10/14
L410UVP-E/212d
Apr 15/15
L410UVP-E/220d
Nov 20/15
012-RECORD OF REVISIONS Page: 2 Nov 20/15
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Rev. No.
Chapter, Section, Subject
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Rev. No.
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012-RECORD OF REVISIONS Page: 4 Nov 1/11
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CHAPTER 12 SERVICING RECORD OF TEMPORARY REVISIONS Rev. No.
Chapter, Section, Subject
EFFECTIVITY: ALL
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012-RECORD OF TEM. REVISIONS Page: 1 Nov 1/11
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Rev. No.
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012-RECORD OF TEM. REVISIONS Page: 2 Nov 1/11
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CHAPTER 12 SERVICING CONTENTS Subject
Chapter, Section, Subject
SERVICING (GENERAL) 012.00.00 Description and Operation General Review of materials for Operation Review of holes for servicing and checking Scheme of areas, prohibited to be stepped on. Scheme of places which cannot be pressed Scheme of the access to the fuel tanks Dangerous area around the aircraft when the engines are running Review of airfield servicing means of general purpose application Scheme of the location of the airfield servicing means Servicing and maintenance ground support equipment Servicing Taking over the aircraft from the crew Taking over the report about aircraft technical conditions from the crew Aircraft inspection Aircraft final inspection Engines start-up observation Connection of electric ground source Main door opening and boarding steps placing Removal and fitting of safety pins (if installed) Boarding steps removing and closing of main doors Checking of control elements and switches in the pilot cockpit Closing and locking doors Aircraft exterior inspection Door control and steps installation Checking of control elements and switches in the pilot cockpit
Page
Effectivity
1 1 1 2 4 14
ALL
16 16 18 19 20 301 301 301 302 302 304 304 305 306 307 307 308 308 310 312
TOOLS Description and Operation General
012.00.01
1 1 1
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GROUND EQUIPMENT Description and Operation General
012.00.02
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MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
TEST FIXTURES Description and Operation General
012.00.03
1 1 1
ALL
FREE PARTS General List of free parts
012.00.04
1 1 1
ALL
1 1 1 301 301 308 309 310 312
ALL
REPLENISHING 012.10.00 Description and Operation General Servicing Fuel filling Drain of the fuel tanks Drain of the fuel cleaners Fuel discharging Shut-off fuel outlets of fuel tanks during repairs fuel system Hydraulic liquid filling Hydraulic liquid discharging Tyre inflation Wash disposal from toilet Wash-basin box installation and re-filling water into wash basin tank and toilet tank Oil filling Oil discharging Water injection system attendance Check of the PTFE (Teflon) hoses SCHEDULED SERVICING Description and Operation General Review of modifications according to dropping temperatures Review of modifications according to raising temperatures Limitations for Operation
012.20.00
UNSCHEDULED 012.30.00 Description and Operation General Servicing Penetration into the aircraft and passengers rescue on the board Extinguishing the on-fire aircraft on the ground Aircraft removal after landing with the landing gear up Aircraft lifting with-one side landing gear retracted Ice accretion removal from the aircraft on the ground Preheating of pilot cabin and landing gear by hot air
EFFECTIVITY ALL
312 315 315 315 318 320 321 321 322 1 1 1 1
ALL
3 3 1 1 1 301 301
ALL
302 303 305 307 309
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MAINTENANCE MANUAL
AIRFIELD SERVICING DESCRIPTION AND OPERATION 1. General This section includes following instructions and information concerning the aircraft servicing on the airfield: •
review of materials for operation
•
review of holes for servicing and inspection
•
scheme of areas, prohibited to be stepped or pressed on
•
scheme of places which cannot be pressed
•
scheme of the access to the tanks
•
dangerous area around the aircraft, when the engines are running
•
review of airfield servicing means of general purpose application
•
scheme of the location of the airfield servicing means
•
servicing and maintenance ground support equipment
•
taking over the aircraft from the crew
•
taking over the report about the aircraft technical conditions from the crew
•
aircraft inspection
•
aircraft final inspection
•
engines start-up observation
•
connection of electric ground source
•
main door opening and boarding steps placing
•
removal and fitting of safety pins
•
boarding steps removing and closing of main doors
•
checking of control elements
EFFECTIVITY ALL
012.00.00 Page: 1 Nov 20/15
MAINTENANCE MANUAL
2. Review of materials for operation Fuel
T-1
(GOST 10227-86)
TS-1
(CSN 656520 )
RT
(GOST 10227-86 or CSN 656520)
PL-6
(PND 25005-76)
PL-7
(PND 25005-92)
JET A
(ASTMD 1655-89)
JET A1
(ASTM D 1655-78T or DERD 2494)
PSM2
(PN-86/C-96026)
The mixing of the above fuels is permitted. CAUTION ANTICORROSION AND LUBRICITY FUEL ADDITIVES AS WELL AS ADDITIVES TO INCREASE ELECTRIC CONDUCTIVITY ANDO TO BIND FREE WATER MAY BE USED IN COMPLIANCE WITH A REGULATION OF THE ADDITIVE MANUFACTURER, PROVIDED THAT THEY ARE APPROVED BY THE APPROPRIATE AUTHORITY FOR USE IN AVIATION. Oil
a) AERO SHELL TURBINE OIL 500 (MIL-L 233 699 C) AERO SHELL TURBINE OIL 555 (MIL-L 233 699 C) AERO SHELL TURBINE OIL 560 (MIL-L 233 699 C) MOBILE JET OIL II EXXON TURBO OIL 2380 CASTROL 599 b) B-3V (TU-38-101 295-72)
CAUTION THE MUTUAL MIXING OF THE OILS GROUPS LISTED IN ABOVE MENTIONED ITEMS IS NOT PERMITTED Preserving oils for M601 type engines:
a) KONKOR 101 (OK-2A) – (PND 23-11-66) KONKOR 103 (OK-5A) – (PND 23-11-66) Mk – 8 – (GOST 6457-66) b) Equivalents of this preserving oils: Shell Oil Ensis L Shell Storage Oil 3
EFFECTIVITY ALL
012.00.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL Hydraulic liquid and the liquid for the shock - MIL - H - 5606: absorber of main nose landing gear
AERO SHELL FLUID 4 AERO SHELL FLUID 41 - AMG - 10 (GOST 6794 - 75) - NYCO HYDRAUNYCOIL FH51
CAUTION THE FOLLOWING MEASURES MUST BE TAKEN FOR THESE AIRCRAFTS USING THE AMG-10 HYDRAULIC FLUID WHEN THIS FLUID IS MIXED WITH OR REPLACE BY A DIFFERENT HYDRAULIC FLUID: A)
AIRCRAFTS HAVING ACCUMULATED LESS THAN 500 FLIGHT HOURS AFTER THE CHANGE OR REPLENISHMENT OF HYDRAULIC FLUID, THE FILTER ELEMENTS MUST BE INSPECTED AFTER EVERY 30 FLIGHT HOURS, FOR A PERIOD OF 120 FLIGHT HOURS. IF BACK DEPOSIT IS FOUND ON THE FILTER ELEMENT, THE HYDRAULIC FLUID MUST BY PURIFIED BY MEANS OF THE SOG EQUIPMENT (OR ANOTHER EQUIVALENT EQUIPMENT), AND THE FILTER ELEMENTS REPLACED BY NEW ONES. IF NO DEPOSIT ARE FOUND ON THE FILTER ELEMENTS AFTER 1200 FLIGHT HOURS, THE AIRCRAFT CAN BE OPERATED WHITOUT ANY LIMITATIONS.
B)
AIRCRAFTS HAVING ACCUMULATED MORE THAN 500 FLIGHT HOURS AFTER THE CHANGE OR REPLACEMENT OF HYDRAULIC FLUID, THE AIRCRAFT CAN BE OPERATED FOR A PERIOD OF 30 FLIGHT HOURS. AFTER THAT TIME, THE HYDRAULIC FLUID MUST BY PURIFIED BY MEANS OF THE SOG EQUIPMENT (OR ANOTHER EQUIVALENT EQUIPMENT), AND THE FILTER ELEMENTS REPLACED BY NEW ONES. FOR FURTHER OPERATION OF THE AIRCRAFT, THE INSTRUCTIONS IN PARA A) APPLY.
Liquid for engine injection
Deionized water
(PND 31-1151- 65)
Distilled water
(CSN 684063, IS 1070 - 1960, BN-716191-95, B.S. 3978:1966, GOST 6709-72)
Deodorant liquid for the toilette
EFFECTIVITY ALL
-
012.00.00 Page: 3 Nov 20/15
MAINTENANCE MANUAL Greases: •
bearing of landing gear wheels Grease
Specification
Applicable
NK 50
GOST 5573 - 67
to - 25°C
Mixture 75 % NK 50 + 25 % CIATIM 201
GOST 5573 - 67 GOST 6267 - 74
below - 25°C
VNIINP - 261
TU 38.401341 - 81
all the year round application
Aeroshell Grease 22
MIL - G 81322 (E)
all the year round application
Aeroshell Grease 22 C
MIL - G 81322 (E)
all the year round application
Mobil Grease 28
MIL - G 81322 (E)
all the year round application
Braycote 622
MIL - G 81322 (E)
all the year round application
Nycogrease 22
MIL - G 81322 (E)
all the year round application
Ekvivalent specification DOD - G - 24508; AIR 4222; DEF STAN 91 - 51; NT - 10006; G - 382
• all lubricated joints of the aircraft
CIATIM 201 (GOST 6267 - 59) CIATIM 221 MOLYKA (PND 33 - 053 - 62) or VNIINP 212 OKB 122 - 16
Oils for lubrication of airframe parts
OKB 132 - 08 (GOST 1875 - 73)
3. Review of holes for servicing and checking The following review comprises the holes, enabling the access to the maintenance and checking points and for dismantling of certain aircraft parts. The numbers, intended for carrying out the routine maintenance have been squared in the review. For example:
10.
Individual hole covers are divided according to the way of opening as follows: I
- A cover with a compression closure (can be opened without using any tool)
II - A tilting cover for opening of which a screwdriver is needed III - Screw fixed covers IV - A cover fixed with the help of rotary closing locks; releasing of these locks is carried out by turning of the lock trunnion with the help of a screwdriver with the rounded edge by 1.5-2 revolutions to the left. When assembled, tightening is made as that on the normal screws. NOTE:
In case that during the tightening the trunnion falls out after releasing the pressure of the screwdriver, it is necessary to turn the trunnion backward, to the left till the noticeable stop and then carry out new tightening by turning the trunnion to the right.
EFFECTIVITY ALL
012.00.00 Page: 4 Nov 1/11
MAINTENANCE MANUAL
Ser. No.
Intended for
Fig. No.
1.
Access to the fuel meter and assembly of the fuel tank
III.
1
2.
Access to the fuel meter and assembly of the fuel tank
III.
1
3.
Access to the engine control, control of the wing flaps and ailerons
III.
1
4.
Access to the mud collector for interconnection of fuel tanks and to the electric installation
III.
1
5.
Assembly of the fuel tank and air bleeding outlet
III.
1
6.
Access to the control of the wing flaps, to the fuel system and electric installation
III.
1
7.
Access to the fuel meter and assembly of the fuel tank
III.
1
8.
Assembly of the fuel tank
III.
1
9.
Access to the engine control, the control and the electric installation
III.
1
10.
Access to the neck for checking the level of the hydraulic liquid (small lid)
II.
1
Assembly of hydraulic liquid tank (outer lid)
III.
-
Access to the filling neck of the fuel tank (small lid)
II.
1
Access to the fuel meter (larger lid)
III.
-
Access to the fuel tank filling neck (small lid)
II.
1
Assembly of the fuel tank (large lid)
III.
1, 2
Access to the position light
III.
1, 2
Check and assembly of the wing flaps and ailerons control, electric installation, deicing of leading edges and the engine control cables
I.
2
Access to the oil filling neck in the engine
I.
3, 4
The assembly of electric installation and fuel system behind the wing rear spar (ports are in the wing shroud)
III.
1
27.
Access to the electro-mechanical strut of the aileron trim tab.
II.
2
28.
Access to the searchlights
III.
1, 2
29.
Access to the front baggage compartment
I.
1, 3
30.
Access to the front baggage compartment
I.
1, 4
31.
Access to the wing connection with the fuselage to the work cylinder of the wing flaps
III.
1, 4
32.
Access to the wing connection with the fuselage
III.
1, 3
33.
Access to the hydraulic system, aileron control, socket connection of the electric installation and to the connection for connecting the air pressure to the system of the pneumatic deicing
III.
1
34.
Access to the suspensions of the elevator
III.
1, 2
35.
Socket of the outer source for the electric installation
I.
3
36.
Access to the cockpit battery
IV.
3
37.
Access to the fuselage rear section and the wing tip position lamp
III.
3, 4
38.
Inspection of the left engine, fuel cleaner
II.
2, 3
39.
Pressure checking in the fire extinguisher of the left-hand engine
I.
3
11.
12.
13. 14. to 22. 23. 24. to 26.
EFFECTIVITY ALL
Cover type
012.00.00 Page: 5 Nov 1/11
MAINTENANCE MANUAL
Ser. No.
Intended for
Fig. No.
40.
Access to the instruments behind the front fire wall, discharge of the hydraulic liquid, to the connection of the external source of the hydraulic system, hydraulic cleaner, battery filling, replenishing of hydraulic liquid
IV.
2, 3
41.
Access to the propeller controller of the left hand engine
III.
1, 3
42.
Access to the engine, to the suspensions of the left-hand engine bed
III.
1, 3
43.
Access to the engine control, starter-generator of the left-hand engine
III.
3
44.
Access to the unions for blowing of engine fire extinguishers
III.
2, 3
45.
Access to the radio equipment and condensate sump of the pitot-system. The cover is divided into two halves. For routine maintenance only the upper half is to be removed.
IV.
4
46.
Access to the radio-electro equipment and the condensate sump of the pitot-system
IV.
4
47.
Access to the propeller controller of the right-hand engine
III.
1, 4
48.
Access to the engine and the suspension of the engine mount of the right-hand engine
III.
1, 4
49.
Access to the engine control, starter-generator of the right-hand engine
III.
4
50.
Access to the instruments behind the front fire wall
IV.
2, 4
51.
Access to the unions for blowing of engine fire extinguishers
III.
2, 4
52.
Inspection of the right-hand engine, fuel cleaner
II.
2, 4
53.
Pressure checking in the fire extinguisher of the right-hand engine
I.
4
54.
Access to the VHF antenna (if installed)
III.
3, 4
55.
Access to the tail plane suspensions, the fin, electric installation
III.
3, 4
56.
Access to the elevator control
III.
3, 4
57.
Access to the control details of the rudder trim tab
III.
3, 4
58.
Access to the control of the elevator trim tab
III.
1
59.
Access to the drums of the rope control of the elevator trim tab
III.
2
60.
Access to the landing gear hydraulic system
III.
2, 3, 5
61.
Access to the landing gear hydraulic system
III.
3, 5
62.
Access to the space of the landing gear left-hand nacelle
III.
2, 3, 5
63.
Door of the left-hand landing gear controlled with the landing gear
-
2, 3, 5
64.
-
-
-
65.
Access to the space of the landing gear left-hand nacelle
III.
2
66.
Access to the left-hand supporting dish for aircraft lifting
III.
2
67.
Access to the space of the landing gear right-hand nacelle
III.
2, 4, 5
68.
Door of the right-hand landing gear controlled with the landing gear
-
2, 4, 5
69.
-
-
-
70.
Access to the water injection in the engine system (tank, pump, etc.)
III.
2, 4, 5
71.
Access to the landing gear hydraulic system
III.
2
72.
Access to the space of the landing gear right-hand nacelle
III.
2
EFFECTIVITY ALL
Cover type
012.00.00 Page: 6 Nov 1/11
MAINTENANCE MANUAL
Ser. No.
Intended for
Cover type
Fig. No.
III.
2
73.
Access to the right-hand supporting dish for aircraft lifting
74.
-
-
-
75.
-
-
-
76.
Access to the mud removing and fuel discharging valve
I.
3
77.
Access to the mud removing and fuel discharging valve
I.
4
78.
Access to the fuel pumps
III.
3
79.
Access to the fuel pumps
III.
4
80.
Access to the devices behind the fire wall
-
-
81.
Access to the devices behind the fire wall
III.
1, 4
82.
Access to the mixing chamber, damper of the heating system
IV.
3
83.
Access to the piping for heating and venting
III.
5
84.
Access to the three-way cock for the compressor washing and the water injection in the engine
I.
3, 4
85.
Access to the pedal control
III.
5
86.
Access to the adjusting elements of the control pull rods and ropes
III.
5
87.
Access to the connections of the hydraulic system
III.
5
88.
Access to the filling neck of the water injection tank in the engine
III.
5
89.
Access to the rope stretching of the trim tabs
III.
5
90.
Assembly of hand operated hydraulic pump
III.
5
91.
Access to the adjusting elements of the control pull rods and ropes
III.
5
92.
Access to the control levers
III.
5
93.
Rope stretching of the trim tabs
III.
5
94.
-
-
-
95.
Access to the antenna of the marker receiver
III.
5
96.
Access to the connection of heating piping
III.
5
97.
Access to the connection of heating piping
III.
5
98.
Access to the loop frame of the radio-compass
III.
5
99.
Access to the connections of the hydraulic system
III.
5
100.
Access to the connections of the hydraulic system
III.
5
101.
Access to the fuselage rear section
IV.
5
CAUTION: WHEN WORKING IN THE REAR SECTION OF THE FUSELAGE (BEHIND THE 21 TH BULKHEAD), USE THE ASSEMBLY BOARD B 596 331 N TO COVER THE SPACE ABOVE THE ANTENNA OF THE RADIO ALTIMETER (BETWEEN THE 21 TH AND 22 ND BULKHEAD) AND COVER THE CONTROL ROPES OF THE ELEVATOR TRIM TAB NOT TO DAMAGE THE CABLE TO THE ANTENNA OF THE RADIO ALTIMETER AND THE ROPE OF ELEVATOR TRIM TAB CONTROL. ON FINISHING WORK REMOVE THE ASSEMBLY BOARD.
EFFECTIVITY ALL
012.00.00 Page: 7 Nov 1/11
MAINTENANCE MANUAL
Ser. No.
Intended for
Fig. No.
III.
5
102.
Access to the seats suspensions
103.
-
-
-
104.
-
-
-
105.
Covers of landing gears, controlled by landing gear
-
2
106.
Access to the lock of the nose landing gear
III.
2
107.
Access to the landing gear hydraulic system
III.
5
108.
Access to the control pull rods and ropes for controlling the engines and for controlling the elevator trim tab.
III.
5
109.
Access to the control locking with the help of the blocking strut
I.
5
110.
Inspection of the wing bottom skin
III.
5
111.
Access to the operation cylinder of the ABC tab
I.
2
112.
Access for assembly of the socket of the outer source and the static pressure sensor
III.
3
113.
Assembly of fire extinguishing system, operation cylinder and the control of the interceptor and hydraulic system
III.
1
114.
Access to the adjustment of the pump stage for water injection in the engine
I.
2
115.
Access to the discharge valve of water injection system in the engine
I.
2
116.
Access to the mud removal of piping of the stall speed probe
I.
5
117.
Access to the mud removing and discharge valve
I.
2
118.
Inspection of the floor and fuselage skin
III.
5
119.
-
-
-
120.
Access to the lock on the pull rod for closing the front covers of the nose landing gear
I.
2
121.
Air pressure check in the hydraulic tank pressurizing system
I.
3
122.
Access to the door guide
III.
5
123.
Access to the filling neck of wing tip fuel tank
II.
1
124.
Access to the fuel meter of wing tip fuel tank
III.
1
125.
Fuel piping assembly
III.
1
126.
Assembly of banking plane
III.
1
127.
Assembly of control cylinder for banking plane and installation of electro-magnetic valves on fuel piping to terminal fuel tank
III.
1
128.
Access to discharging washing the toilet (if installed)
ll.
4
129.
Access to the filling neck single - point fuelling (if installed)
III.
4
NOTE:
EFFECTIVITY ALL
Cover type
Beside the above covers, there are removable upholstered panels in the passenger compartment, which are fixed by means of screws.
012.00.00 Page: 8 Nov 1/11
MAINTENANCE MANUAL
FIG. 1
REVIEW OF HOLES FOR SERVICING (TOP VIEW)
EFFECTIVITY ALL
012.00.00 Page: 9 Nov 1/11
MAINTENANCE MANUAL
FIG. 2
REVIEW OF HOLES FOR SERVICING (BOTTOM VIEW) I
EFFECTIVITY ALL
- Right-hand landing gear nacelle (from the bottom)
012.00.00 Page: 10 Nov 1/11
MAINTENANCE MANUAL
FIG. 3
REVIEW OF HOLES FOR SERVICING (LEFT-HAND SIDE) I
- Left side of left-hand engine nacelle
II
- Right side of left-hand engine nacelle
EFFECTIVITY ALL
012.00.00 Page: 11 Nov 1/11
MAINTENANCE MANUAL
FIG. 4
REVIEW OF HOLES FOR SERVICING (RIGHT-HAND SIDE) I
- Left side of right-hand engine nacelle
II - Right side of right-hand engine nacelle
EFFECTIVITY ALL
012.00.00 Page: 12 Nov 1/11
MAINTENANCE MANUAL
FIG. 5
REVIEW OF HOLES FOR SERVICING (PASSENGER COMPARTMENT FLOOR AND LANDING GEAR NACELLES)
EFFECTIVITY ALL
012.00.00 Page: 13 Nov 1/11
MAINTENANCE MANUAL
4. Scheme of the areas, not allowed to be stepped on. Scheme of the places which cannot be pressed.
FIG. 6
AREA NOT ALLOWED TO BE STEPPED ON
EFFECTIVITY ALL
012.00.00 Page: 14 Nov 1/11
MAINTENANCE MANUAL
FIG. 7 PLACES WHICH CANNOT BE PRESSED (BOTTOM VIEW)
EFFECTIVITY ALL
012.00.00 Page: 15 Nov 1/11
MAINTENANCE MANUAL
5. Scheme of the access to the fuel tanks Diagram of tanks location with inflammable matters is shown on fig. 2, section 012.30.00.
6. Dangerous area around the aircraft when the engines are running
FIG. 8
SCHEME OF DANGEROUS AREA AROUND THE AIRCRAFT WHEN ENGINES ARE RUNNING (IDLING RUN)
EFFECTIVITY ALL
012.00.00 Page: 16 Nov 1/11
MAINTENANCE MANUAL
FIG. 9
SCHEME OF DANGEROUS AREA AROUND THE AIRCRAFT WHEN ENGINES ARE RUNNING ON MAX: TAKE-OFF REGIME
EFFECTIVITY ALL
012.00.00 Page: 17 Nov 1/11
MAINTENANCE MANUAL 7. Review of airfield servicing means of general purpose application Item No.
Specification
1.
Road tanker
Fuelling gun, ND 38 mm
2.
Ground source of power supply
Characteristics as per GOST 19705-74, outlet voltage 28/29 V, permissible load 700 A, ShRAP 500
3.
The car for spraying the aircraft with antifreezing liquid
Not specified
4.
General purpose heating car, engine driven
OD of heating hose outlet hole is 200 mm
5.
Mobile oxygen filling station
Connecting union thread: 21.8 x 1/14" pipe thread
6.
Aggregate VZA for filling the system of distilled water Not specified injection
EFFECTIVITY ALL
Characteristics, connection dimensions of nozzles and reducers
012.00.00 Page: 18 Nov 1/11
MAINTENANCE MANUAL 8. Scheme of the location of the airfield servicing means
FIG. 10
SCHEME OF THE LOCATION OF THE AIRFIELD SERVICING MEANS (1) Road tanker; (2) Ground source of power supply; (3) Car for oil filling; (4) Hydraulic truck
EFFECTIVITY ALL
012.00.00 Page: 19 Nov 1/11
MAINTENANCE MANUAL
9. Servicing and maintenance ground support equipment NOTE:
The tooling shown in this manual is the recommended one. An equivalent tooling may be used instead.
Servicing and maintenance ground equipment consist from: M1.
Basic set of ground equipment delivered with each airplane •
M2.
Recommended equipment for regions with temperatures below -25°C
Sets of recommended support equipment for servicing airplane: M2.1.
Ground support equipment
M2.2.
Sets of tools for operational and periodic maintenance
M3 (P2) Testing equipment Together with the M2 Sets form the Set of ground support and testing equipment up to P2 periodic check M3 (R1) Full set of ground support and testing equipment 1.1.
Recommended equipment
1.2.
Sets of tools
1.3.
Optional equipment
EFFECTIVITY ALL
012.00.00 Page: 20 Nov 20/15
MAINTENANCE MANUAL M1. Basic set of ground equipment delivered with each airplane Pos. No.
Name and figure
Type (Ord. No.)
Note
1.
Left exhaust cover - nonmetallic (2 pcs)
B598732L
For exhaust covering
2.
Right exhaust cover - nonmetallic (2 pcs)
B598732P
For exhaust covering
3.
Air inlet cover of the engine and starter generator - nonmetallic (2 pcs)
B598733N
Blinding of air inlet to the engine and starter generator
4.
Bag for nonmetallic covers (1 pc)
B598759N
Bag for nonmetallic covers (pos. no. 1 to 3)
Not illustrated 5.
Wheel chock (3 pcs)
B596895N
Securing airplane against any motion
6.
Propeller blocking element (2 pc)
B596695N
-
EFFECTIVITY ALL
012.00.00 Page: 21 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Type (Ord. No.)
Note
7.
Pitot cover (2 pcs)
B598919N
Used for covering of Pitot tube
8.
Blind flange of static pressure (2 pcs)
B953322N or L410M.9537
Blinding of static pressure sensors
9.
Aileron and elevator blocking element (4 pc)
B922150N or XL410.9220
Locking of elevator and ailerons in strong wind
10.
Steering wheel blocking element (1 pc)
B596476N
Locking of control wheel and pedals
11.
Rudder blocking element (1 pc)
B596790N (valid for airplane with the M601 Turboprop engines) or
Locking of rudder in strong wind
B098698N (valid for airplane with the H80-200 Turboprop engines) 12.
Toilet ventilation cover (1 pc)
EFFECTIVITY ALL
B596420N
-
012.00.00 Page: 22 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Type (Ord. No.)
Note
13.
Stall speed hole plug (1 pc)
B097490N
Serves for sealing of stall speed hole
14.
Steps (1 pc)
B596281N
For airplane entry (if installed))
15.
Hand towing equipment (1 pc)
B952053N or L410.9521
Towing the airplane on smooth surface
Set of anchor device (1 set):
B598938N
16.
Anchor device for the wing (2 pc)
B598942N
Airplane mooring (refer to the Chapter 10)
17.
Anchor device of main landing gear (2 pc)
B598950N
18.
Anchor device of nose landing gear (1 pc)
B598945N
Not illustrated
19.
20.
HRZ 4/550/S Hydraulic jack + support
Extending ladder to be transported in airplane (1 pc)
EFFECTIVITY ALL
B599355N
For lifting of airplane
B598935N
Gravity fuelling and access to the wing
012.00.00 Page: 23 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Type (Ord. No.)
Note
21.
Universal tools kit (1 pc)
B598973N
-
22.
Bag for documentation (7 pcs)
B098515N
Accompanying documentation
Not illustrated 23.
Wing tip LH
B524590L
Airplane operated without wing tip fuel tanks (WTT)
24.
Wing tip RH
B524590P
Airplane operated without wing tip fuel tanks (WTT)
25.
Blinding cap for WTT (2 pc)
B098600N
Serves for sealing venting of the wing tip tanks on the bottom of the wing tip tank
26.
Mud discharge connection (1 pc)
B596560N
Wingtip tank mud discharge
27.
Connection of fuel mud removal (1 pc)
B096591N
Main fuel tank mud discharge
28.
Emergency door blocking element (3 pcs)
B596575N
-
LUN 7743-7 (95077437)
Suction connection
LUN 7744-7 (95077447)
Filling (pressure) connection
Not illustrated 29.
Connection for hydraulic trolley Not illustrated
30.
Connection for hydraulic trolley Not illustrated
EFFECTIVITY ALL
012.00.00 Page: 24 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Type (Ord. No.)
Note
31.
Special tool (1 pc) (includes B598626N , B598627N , B598628N)
B598625N
-
32.
6-pin to Dual G/A Cable Adapter for BOSE A20 headset
BOSE Ord. No. 47693 (90018728)
(for BOSE A20 headset only)
Airplane without central refueling system Pos. No. 33.
Name and figure Blinder (4 pcs)
EFFECTIVITY ALL
Type (Ord. No.) 10 ONL 3996.4 (32143410)
Note -
012.00.00 Page: 25 Nov 20/15
MAINTENANCE MANUAL
Recommended equipment for regions with temperatures below -25°C Pos. No.
Name and figure
Type (Ord. No.)
Note
34.
Winter cover of the cooler, front part (2 pcs)
B596570N
Covering of oil cooler
35.
Winter cover of the cooler, rear part (2 pcs)
B596571N
Covering of oil cooler
36.
Oil cooler insulation (2 pcs)
B596572N
Covering of oil cooler
37.
Blinder (4 pcs)
16 ONL 3996.4 (32143416)
-
Operation at the lower ambient temperature – valid for airplane with the oil-to-fuel heaters Pos. No.
Name and figure
Note
38.
Connecting piping for oil-to-fuel heater at the disconnecting of the oil cooler
B596568L
-
39.
Connecting piping for oil-to-fuel heater at the disconnecting of the oil cooler
B596568P
-
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 26 Nov 20/15
MAINTENANCE MANUAL
Airplane with the central refueling system Pos. No.
Name and figure
Note
40.
Blinder (2 pcs)
10 ONL 3996.4 (32143410)
-
41.
Blinder (2 pcs)
14 ONL 3996.4 (32143414)
-
42.
Blinder (2 pcs)
6 ONL 3996.4 (32143406)
-
43.
Blinder (2 pcs)
4 ONL 3996.4 (32143404)
-
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 27 Nov 20/15
MAINTENANCE MANUAL
Sets of tools supplied with each airplane B598973N Universal tools kit – column A B598625N Special tools and fixtures contents of the: •
B598626N - case No. 1 – column B
•
B598627N - case No. 2 – column C
•
B598628N - case No. 3 – column D Figure
Type (Ord. No.)
Name
A
B
C
D
B914081N
Modified screwdriver
•
-
-
-
75287304
Flat screwdriver 4
•
-
-
-
75287306
Flat screwdriver 6.5
•
-
-
-
PH1x80
Phillips/cross-point screwdriver
•
-
-
-
Phillips/cross-point screwdriver
•
-
-
-
75287308
Kennedy KEN5583900K
Safety wire twisting pliers
•
-
-
-
75319828
Cutting pliers
•
-
-
-
75260006
Handle 14”/116 DIN 3124-A6,3
•
-
-
-
75259104
STAHLWILLE Adapter DIN 3124-B6,3 – 2 pc
•
-
-
-
75258012
Socket wrench 12 DIN 3124-S
•
-
-
-
92510935
STEATHLITE 2410 LED Portable light
•
-
-
-
95221968
AA Battery – 4 pcs
•
-
-
-
75287307
PH2x100
75366101
EFFECTIVITY ALL
012.00.00 Page: 28 Nov 20/15
MAINTENANCE MANUAL
Figure
Type (Ord. No.)
A
B
C
D
•
-
-
-
5.5x7 DIN 3110 ISO 3318 74925707
•
-
-
-
8x9 DIN 3110 ISO 3318 74925709
•
-
-
-
10x11 DIN 3110 ISO 3318 74925711
•
-
-
-
12x13 DIN 3110 ISO 3318 74925713
•
-
-
-
14x15 DIN 3110 ISO 3318 74925715
•
-
-
-
14x17 DIN 3110 ISO 3318 74925717
•
-
-
-
16x18 DIN 3110 ISO 3318 74925718
•
-
-
•
19x22 DIN 3110 ISO 3318 74925722
•
-
-
-
24x27 DIN 3110 ISO 3318 74925727
•
-
-
•
36x41 DIN 3110 ISO 3318 74925741
•
-
-
-
30x32 DIN 3110 ISO 3318 74925732
•
-
-
-
B914062N or L410.9144-10
-
-
•
-
Phillips/cross-point screwdriver shorter
•
-
-
-
4x30 75287309
Flat screwdriver shorter
•
-
-
-
75287402
Hexagonal screwdriver 2.5
•
-
-
-
75287403
Hexagonal screwdriver 3
•
-
-
-
75287404
Hexagonal screwdriver 4
•
-
-
-
75287408
Hexagonal screwdriver 8
•
-
-
-
75319853
Circlip pliers
•
-
-
-
75319830
Pliers wrench 250
•
-
-
•
75300149
Combination pliers
•
-
-
-
4x5 DIN 3110 ISO 3318 74925705
PH1x30 75289307
EFFECTIVITY ALL
Name Double-ended spanner
012.00.00 Page: 29 Nov 20/15
MAINTENANCE MANUAL
Figure
Type (Ord. No.)
ALL
A
B
C
D
75479250
Hammer 300 DIN 1041
•
-
-
-
75656014
885400 NAREX Telescopic magnetic extractor
•
-
-
-
75650008
Inspect mirror 50mm
•
-
-
-
B096113N
Special socket wrench
-
•
-
-
B096120N
-
•
-
-
B914055N or L410.9143-02
-
•
-
-
B914057N or L410.9143-04
-
•
-
-
B914058N or L410.9143-05
-
•
-
-
B914060N or L410.9143-07
-
•
-
-
-
•
-
-
8x9 DIN 896B 75071808
-
-
•
-
10x11 DIN 896B 75071810
-
-
•
-
12x13 DIN 896B 75071812
-
-
-
•
27x32 DIN 896B 75071827
-
-
•
-
36x41 DIN896B 75071836
EFFECTIVITY
Name
Socket wrench
B971051N or L410.9712 T5-2002-101-00
Dynamometer kit
-
•
-
-
B914065N or L410.9144-02 (2 pcs)
Open end wrench
-
•
-
-
B914066N or L410.9144-03 (2 pcs)
Open end wrench
-
•
-
-
B914056N or L410.9143-03
Open end wrench
-
•
-
-
B096111N
-
•
-
-
B096121N
-
•
-
-
012.00.00 Page: 30 Nov 20/15
MAINTENANCE MANUAL
Figure
w/o
Type (Ord. No.)
Name
C
D
Hook
-
•
-
-
B914084N or L410.9146-04
Special screwdriver
-
•
-
-
B911320N or L410.9110-02
Pliers for assembly of tail units
-
•
-
-
02065972
Handle 6 CR
-
•
•
-
02065973
Handle 8 CR
-
•
-
•
75260009
Handle 18x500 CR DIN 900
-
•
-
-
02065976
Handle 16 CR
-
-
•
-
75260010
Handle 3/4”, length 510 DIN 3122-A 20
-
•
-
-
75258055
Socket wrench 55 3/4" DIN 3124-S
-
•
-
-
87168223
PE-bag 220x320x0.1
-
•
•
•
B096320N
Open end wrench
-
-
•
-
-
-
•
-
-
-
•
-
-
-
•
-
B097408N
Wrench
B097409N
ALL
B
B096266N
B096321N
EFFECTIVITY
A
B596634N
Screwdriver
-
-
•
-
B914051N or L410.914102 (2 pcs)
Assembly pin 8mm
-
-
•
-
B098703N (2 pcs)
Assembly pin 6mm
-
-
•
-
012.00.00 Page: 31 Nov 20/15
MAINTENANCE MANUAL
Figure
Type (Ord. No.)
Name
A
B
C
D
Open end wrench
-
-
•
-
41 DIN 894 74933041
-
-
•
-
50 DIN 894 74933050
-
-
•
-
OK 42 B914067N or L410.9144-04
-
-
•
-
6 DIN 894 74933006 (2 pcs)
EFFECTIVITY ALL
B598785N
Open end wrench for stop cocks
-
-
-
•
OK17 B914068N or L410.9144-05
Open end wrench
-
-
•
-
OK19 B914069N or L410.9144-06
-
-
•
-
OK22 B914070N or L410.9144-07
-
-
•
-
B096106N
Wrench for control column
-
-
-
•
B914052N or L410.9141-03
Screwdriver
-
-
-
•
39914001 (No. 10)
Glass magnifying
-
-
-
•
03167051
Gap gauge 0.05 – 1/10
-
-
-
•
B098684N (2 pcs)
Fixtures for securing the control cables against turning
-
-
-
•
B098706N
Wrench 27 for pressure switches in wing
-
-
-
•
012.00.00 Page: 32 Nov 20/15
MAINTENANCE MANUAL
Figure
EFFECTIVITY ALL
Type (Ord. No.)
Name
A
B
C
D
B098705N (2 pcs)
Secure screw for securing of the elevator trim tab control cables in the drums
-
-
-
•
B098704N
Fixtures for securing the control cables against turning
-
-
-
•
B598975N
Blocking of the elevator trim tab control cables (if is autopilot installed)
-
-
-
•
012.00.00 Page: 33 Nov 20/15
MAINTENANCE MANUAL M2. Sets of recommended support equipment for servicing airplane M2.1.
Ground support equipment
Pos. No.
Name and figure
Note
1.
Cockpit canvas (1 pc)
B596798N
-
2.
Exhaust canvas (4 pcs)
B096008N
-
3.
Wheel block (3 pc)
B925028N or XL410.9250
Securing airplane against any motion
4.
Wheel check extension (2 pcs)
B928265N or L410.9280
Securing airplane against motion (for engine test)
5.
Control lever blocking
B965282N or L410.9650
Securing of control lever
B596331N
Working in the fuselage rear section
Not illustrated 6.
Assembly floor board (1 pc)
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 34 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Note
7.
Breaking piece (4 pcs)
B067345N
Intended for securing the closing valve of fire extinguisher bottle
8.
Nose cover strut
B596546N
For nose cover fixing
9.
Fuel discharge hose (1 pc)
B096116N
Discharging fuel from the main fuel tanks
10.
Oil discharge hose (1 pc)
B954095N or L410.9544
Discharging oil from the engine
11.
Hydraulic liquid drain hose (1 pc)
B954089N or XL410.9543
Drainage of hydraulic fluid
12.
Grounding device of the airplane (1 pc)
B096432N
Grounding the airplane
13.
Tractor towing equipment (1 pc)
B097581N (Ø 40mm)
Towing the airplane by means of tractor
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 35 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Note
14.
Rear support small (1 pc)
B596340N
Supporting of fuselage rear section when lifting the airplane by front jack
15.
Vessel for kerosene (1 pc)
B955933N or L410.9558-03
Removal preserving agent and washing of engine components
16.
Distilled water funnel (1 pc)
B096243N
For water filling (only if the water injection system is installed)
17.
Oil filling funnel (1 pc)
B096242N
Replenishing engine oil
18.
Hose (2 pcs)
B964201N or L410.9643
Brake system bleeding and flushing
19.
Vessel for venting of hydraulic pumps (1 pc)
B097480N
Hydraulic system venting
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 36 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Note
20.
Hose for hydraulic pumps venting (1 pc)
B097485N
Hydraulic system venting
21.
Kit for fuel drain (1 pc)
B097441N
Drain of fuel filter
22.
Stairs of engine (1 pc)
B097300N
Engine servicing
23.
500 CSN 231462 Lever press (1 pc)
95273405
Forced lubrication of lubrication points provided with grease nipples
1000 CSN 231492.3 Lubrication hose (1 pc)
95273417
For forced lubrication (to be connected to the lever press)
24.
Smart cable + PCMCI card for EGPWS update
951-0386-001 (B503704N)
(If installed the EGPWS Honeywell MARK VI)
25.
Testing cable for EGPWS
704-2617-001 (B503705N)
(If installed the EGPWS Honeywell MARK VI)
26.
Configuration cable for PS 578A
B598891N
(If installed TCAS II Honeywell CAS67A/B)
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 37 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Note
27.
Testing cable for TCAS
B598893N
(If installed TCAS II Honeywell CAS67A/B)
28.
Testing cable for KRA 405B Radar Altimeter
B598892N
-
29.
Kennedy KEN-503-7300K Assembly boogie (1 pc)
75650070
-
30.
Air filling device (1 pc)
B096690N
Pressurizing the hydraulic system
31.
Filling device of hydraulic fluid (1 pc)
HYDROMA HA-5881-15 (95277006)
Filling of hydraulic fluid into airplane hydraulic system
32.
Wheel remover of the nose wheel (1 pc)
B097550N
Facilitating the nose wheel removal
33.
Ring remover of the nose wheel bearing (1 pc)
B097592N
Replacement of nose wheel removal
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 38 Nov 20/15
MAINTENANCE MANUAL
Pos. No.
Name and figure
Type (Ord. No.)
34.
Wheel remover of the main wheel (1 pc)
B097560N
Facilitating the main landing gear wheel removal
35.
Ring remover of the main wheel bearing (1 pc)
B097586N
Replacement of main wheel removal
36.
Lock washer pin remover of the main landing gear (1 pc)
B097327N
-
37.
Hydraulic jack (1 pc)
B097700L
Lifting of airplane during leveling and functional test (landing gear, flaps)
38.
Hydraulic jack (2 pcs)
B097700P
Lifting of airplane during leveling and functional test (landing gear, flaps)
B598700N
(M14x1)x(9/16-18)-Oxygen (AVOX-SCOTT)
Figure – see Pos. No. 37 39.
Reducer (1 pc)
40.
Ladder for wing servicing and/or fuel filling B097343N or (1 pc) B596558N
EFFECTIVITY ALL
Note
For works on wing surface
012.00.00 Page: 39 Nov 20/15
MAINTENANCE MANUAL
M2.2.
Sets of tools for operational and periodic maintenance
Ser. No.
Name and figure
Note
1.
Tools for propeller and engine (1 pc)
B598992N
-
2.
Tools for the landing gear and hydraulic system (1 pc)
B596333N
-
3.
Tools for el. equipment engineer (1 pc)
B096477N
-
4.
Tools for the aircrew (1 pc)
B096470N
-
EFFECTIVITY ALL
Type (Dwg. No.)
012.00.00 Page: 40 Nov 20/15
MAINTENANCE MANUAL
Sets of tools for operational and periodic maintenance B598992N Tools for propeller and engine – column E B596333N Tools for the landing gear and hydraulic system – column F B096477N Tools for el. equipment engineer – column G B096470N Tools for the aircrew – column H Figure
w/o
EFFECTIVITY ALL
Type (Ord. No.)
Name
E
F
G
H
02063808
22 Open & ring end spanner
•
-
-
-
E101107N AM-63A-01
Auxiliary pin 3mm dia
•
-
-
-
E101108N 145-PM 30
Spanner
•
-
-
-
E101109N 146-PM 2001
Auxiliary pin 5mm dia
•
-
-
-
E101110N 145-PM 22
Puller for removing the engine fuel pump filter
•
-
-
-
E101112N M601-9020.7
Engine oil drainage adapter
•
-
-
-
E101113N 146-PM160
Square socket spanner s=3mm
•
-
-
-
E101114N 146-PM161
Square socket spanner s=4mm
•
-
-
-
E101115N 146-PM162
Square socket spanner s=5mm
•
-
-
-
E101105N M601-915.9 (2 pcs)
Engine fuel system drainage adapter
•
-
-
-
E101123N M601-903.7 (2 pcs)
Reduction gearbox drainage adapter
•
-
-
-
E101164N M601-9028.7
Remover of engine pressure reducing valve; shaft packing ring
•
-
-
-
012.00.00 Page: 41 Nov 20/15
MAINTENANCE MANUAL
Figure
w/o
EFFECTIVITY ALL
Type (Ord. No.)
Name
E
F
G
H
E101118N 145-PM 2037
Puller for removing the engine fuel pump lid
•
-
-
-
068-8110 E101165N
Breaker bar to remove the mounting bolts/nuts and blade clamp nuts of the propeller
•
-
-
-
TH MDL 200ADJ 75190110
Toque wrench to tighten and torque the mounting bolts of propeller
•
-
-
-
75190115
Socket 19 mm (3/4 inch)
•
-
-
-
75190118
Socket 22 mm (7/8 inch)
•
-
-
-
75190112
Hexagon key wrench
•
-
-
-
E101116N M601-9019.7
Adapter for engine preservation and de-preservation
•
-
-
-
E101154N 152 99 400
Ball joint spanner for propeller governor installation
•
-
-
-
03167051
Gap gauge 0.05 – 1/10 for clearance check in engine controls
•
-
-
-
E101145N M601-913.9
Mirror for compressor blades inspection
•
-
-
-
E101147N M601-919.4
Ratchet spanner for gas generator manual turning
•
-
-
-
012.00.00 Page: 42 Nov 20/15
MAINTENANCE MANUAL
Figure
w/o
Type (Ord. No.)
Name
E
F
G
H
B096040N
Spanner of fuel cleaner hose
•
-
-
-
B096320N
Open end wrench
•
-
-
-
OMK 10 02072110
Toque wrench 9.86 to 98.6 Nm
•
-
-
-
17 DIN 894 74933017
Open end wrench
-
•
-
-
P 10 95214346
Pressure gauge
-
•
-
-
Kennedy KEN5583920K
Safety wire twisting pliers
-
•
-
-
B955940N or L410.9559
Main wheel disc spanner
-
•
-
-
B096322N
Spanner of lock safety pin of landing gear
-
•
-
-
B097341N
Socket wrench
-
•
-
-
B097730N
Spanner for air filter
-
•
-
-
75287301
Flat screwdriver 8x175
-
•
-
-
75287302
Flat screwdriver 2.5x75
-
-
•
-
75287303
Flat screwdriver 3.5x100
-
-
•
-
75366102
EFFECTIVITY ALL
012.00.00 Page: 43 Nov 20/15
MAINTENANCE MANUAL
Figure
EFFECTIVITY ALL
Type (Ord. No.)
Name
E
F
G
H
75258001
Socket wrench 10 3/8" DIN 3124
-
•
-
-
75258002
Socket wrench 12 3/8" DIN 3124
-
•
-
-
75258003
Socket wrench 13 3/8" DIN 3124
-
•
-
-
75258017
Socket wrench 17 3/8" DIN 3124
-
•
-
-
75258019
Socket wrench 19 3/8" DIN 3124
-
•
-
-
75258012
Socket wrench 12 DIN 3124-S
-
-
-
•
75258013
Socket wrench 7/16”
-
-
-
•
75259107
STAHLWILLE Adapter 3/8"x125 DIN 3123-B610
-
•
-
-
75259104
STAHLWILLE Adapter 1/4"x355 DIN 3123-B6,3
-
-
-
•
75259105
GARANT Adapter 1/4"x100
-
-
-
•
75259106
GARANT Adapter 1/4"x150
-
-
-
•
75260008
Ratchet spanner 3/8"
-
•
-
-
75260007
Ratchet spanner 1/4"
-
-
-
•
96279910 (K 20-7100)
Fixture for tyre dismantling
-
•
-
-
02065974
Handle 10 CR
-
•
-
-
02065976
Handle 16 CR
-
•
-
-
B096018N
Special spanner
-
-
•
-
B596668N
Special screwdriver
-
-
•
-
012.00.00 Page: 44 Nov 20/15
MAINTENANCE MANUAL
Figure
EFFECTIVITY ALL
Type (Ord. No.)
Name
E
F
G
H
B096480N
Modified screwdriver
-
-
•
-
B914082N or L410.9141-05
Special screwdriver
-
-
•
•
ETP5 125W/230V 00900009
Soldering gun
-
-
•
-
42035720
Soldering wire
-
-
•
-
74801016
Needle file 160
-
-
•
-
75287500
Hexagonal screwdriver 3/32”
-
-
•
•
75239031
Hexagonal screwdriver 7/64”
-
-
-
•
75633001 100-NH-1A
Pocked knife
-
-
•
•
75650124
Clamp
-
-
•
-
3x145 75650300
Flat end tweezers
-
-
•
-
LYON 8 89012208
Brush for collector cleaning
-
-
•
-
95227409 or 95227411
Multimeter EXTECH
-
-
•
-
012.00.00 Page: 45 Nov 20/15
MAINTENANCE MANUAL
Figure
Type (Ord. No.)
E
F
G
H
-
-
-
•
D901061N or Z37.9110-02
-
-
-
•
D901062N or Z37.9110-03
-
-
-
•
D901060N or Z37.9110-01
EFFECTIVITY ALL
Name Dural mandrel
D901088N or Z37.9110-10
Modified screwdriver
-
-
-
•
75539704
Centre punch
-
-
-
•
75639526
Metal sheet snears
-
-
-
•
012.00.00 Page: 46 Nov 20/15
MAINTENANCE MANUAL M3 (P2) Set of ground support and testing equipment up to P2 periodic check (consists from the М2 - Sets of recommended support equipment for servicing airplane and Testing equipment as mentioned follows) Testing equipment Ser. No.
Name and figure
Note
1.
Rear support (1 pc)
B962140N or XL410.9620
For supporting of fuselage rear section
2.
Vessel for oil (1 pc)
B955932N or L410.9558-01
Replenishing engine oil
3.
Vat (1 pc)
B961805N or L410.9617
Cleaning of engine and laying of small components
4.
Stairs (1 pc)
B097365N
Stabilizers and wingtip tanks servicing
5.
Hydraulic truck
HYDROCOM MA-801-03 (95277003)
For functional tests of airplane hydraulic systems
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 47 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
6.
Filter washing device (1 pc)
B953401N or L410.9539
Washing of hydraulic fluid filters
7.
Filter checking device (1 pc)
B954251N or L410.9540
Checking of hydraulic fluid filter clogging
8.
Test clamp (1 pc)
B096221N
Check for clearance of nose land. gear servo
9.
Checking and filling device of damper (1 pc)
B955091N or XL410.9551
Checking and filling of land. gear shock absorbers and hydraulic accumulators
10.
Connection set of Air Data Tester
B598984N
For connection of the BARFIELD 1811D A0A Air Data Tester to the Pitot-static system of aircraft
11.
Air Data Tester
BARFIELD 1811D A0A (98110925)
For checking of Pitot system Airspeed indicators, LUN 1108.XX-8 Airspeed indicator, LUN 1173.XX-8 Air-speed signaler, Altimeters, Vertical speed indicators, LUN 1492.XX-8, LUN 1496.XX-8 Pressure switches
12.
Digital multimeter with temp. probe and Insulation tester
EXTECH MG302 (95227412)
-
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 48 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
13.
BR07 Resistance decade + 2RMT14 KPN 4G1V1 Socket
90910110 + 91721430
Check of the correct operation of the TER-1M thermoregulators
14.
Battery charger/Analyzer
RF 80-K CE (95224216)
Maintenance of the on board battery of airplane
15.
NiCd/NiMH battery charger + B598991N Connecting Cable
Voltcraft ALC8500 EXPERT (95224213) + B598991N
Maintenance of the battery of emergency lighting
16.
Blocking of the elevator trim tab control cables
B598975N
Blocking of the elevator trim tab control cables (if is autopilot installed)
17.
Boroscope HDV640W
B598990N
-
18.
Service trolley (1 pc)
B968051N or L410.9682
Laying of tools and components
19.
Dynamometer
EXTECH 475044 (95216982)
-
20.
Testing cable for ESI 2000 Electronic Standby Indicator (if installed)
Y348432N
For battery calibration procedure of the ESI-2000 in the testing room
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 49 Nov 20/15
MAINTENANCE MANUAL M3 (R1) Full set of ground support and testing equipment up to R1 inspection check 1.1. Recommended equipment Ser. No.
Name and figure
Type (Ord. No.)
1.
Cockpit canvas (1 pc)
B596798N
-
2.
Exhaust canvas (4 pcs)
B096008N
-
3.
Hydraulic jack (1 pc)
B097700L
Lifting of airplane during leveling and functional test (landing gear, flaps)
4.
Hydraulic jack (2 pcs)
B097700P
Lifting of airplane during leveling and functional test (landing gear, flaps)
Figure – see Pos. No. 3. 5.
Wheel block (3 pc)
B925028N or L410.9250
Securing airplane against any motion
6.
Wheel check extension (2 pcs)
B928265N or XL410.9280
Securing airplane against motion (for engine test of airplane)
EFFECTIVITY ALL
Note
012.00.00 Page: 50 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
7.
Rear support (1 pc)
B962140N or XL410.9620
For supporting of fuselage rear section
8.
Rear support small (1 pc)
B596340N
Supporting of fuselage rear section when lifting the airplane by front jack
9.
Vessel for oil (1 pc)
B955932N or L410.9558-01
Replenishing engine oil
10.
Stairs (1 pc)
B097365N
Tail unit and wingtip tanks servicing
11.
Kennedy KEN-503-7300K Assembly boogie (1 pc)
75650070
-
12.
Connection for hydraulic trolley
LUN 7743-7 (95077437)
Suction connection
LUN 7744-7 (95077447)
Filling (pressure) connection
Not illustrated 13.
Connection for hydraulic trolley Not illustrated
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 51 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
14.
Hydraulic truck
HYDROCOM MA-801-03 (95277003)
For functional tests of airplane hydraulic systems
15.
Filling device of hydraulic fluid
B596200N or HYDROMA HA-5881-15 (95277006)
Filling of hydraulic fluid into airplane hydraulic system
16.
Wheel remover of the nose wheel (1 pc)
B097550N
Facilitating the nose wheel removal
17.
Ring remover of the nose wheel bearing (1 pc)
B097592N
Replacement of nose wheel removal
18.
Wheel remover of the main wheel (1 pc)
B097560N
Facilitating the main landing gear wheel removal
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 52 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
19.
Ring remover of the main wheel bearing (1 pc)
B097586N
Replacement of main wheel removal
20.
Lock washer pin remover of the main landing gear (1 pc)
B097327N
-
21.
Angle meter for the measurement of ailerons and elevator deviation
B596301N
Used for max. angle measurement
22.
Filter washing device (1 pc)
B953401N or L410.9539
Washing of hydraulic fluid filters
23.
Filter checking device (1 pc)
B954251N or L410.9540
Checking of hydraulic fluid filter clogging
24.
Dynamometer
EXTECH 475044 (95216982)
-
25.
Test clamp (1 pc)
B096221N
Check for clearance of nose land. gear servo
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 53 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
26.
Checking and filling device of damper (1 pc)
B955091N or XL 410.9551
Checking and filling of land. gear shock absorbers and hydraulic accumulators
27.
Air filling device (1 pc)
B096690N
Pressurizing the hydraulic system
28.
Connection set of Air Data Tester
B598984N
For connection of the BARFIELD 1811D A0A Air Data Tester to the Pitot-static system of aircraft
29.
Air Data Tester
BARFIELD 1811D A0A (98110925)
For checking of Pitot system Airspeed indicators, LUN 1108.XX-8 Airspeed indicator, LUN 1173.XX-8 Air-speed signaler, Altimeters, Vertical speed indicators, LUN 1492.XX-8, LUN 1496.XX-8 Pressure switches
30.
DME, ATC + TCAS, ADC Tester
IFR 6000 95216988 (XPNDR SET) 95216989 (OPT2)
For checking of DME, ATC + TCAS, ADC
31.
VOR /ILS /MKR /AP + Beacon Tester
IFR 4000 (95216986)
For checking of VOR/ILS/MKR/AP + Beacon
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 54 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
32.
Calibrating аnd testing device
Z8001 (98111010)
Testing and calibration of: LUN 1476-8 Torque limiter pressure switch, LUN 1539.XX-8 Torque indicator, LUN 1540.XX-8 Torque sensor, LUN 3280 Pressure switch of automat. feathering, 0.012K LUN 1492.01-8 Pressure switch, 0.02K LUN 1492.01-8 Pressure switch, 1.25K LUN 1469.32-8 Pressure switch, LUN 1558-8 Inductive pressure switch, LUN 1559-8 Inductive pressure switch, LUN 1371-8 and LUN 1377-8 Temperature transmitters
33.
Fire simulator (1 pc)
B097852N
Testing of the fire extinguishing detection system
34.
Calibrating source of speed; with transmitter and ; testing cable
1790-230 (95216959); LUN 1333.12B-8 (95013333); B574620N
LUN 1347.XX Generator speed indicator, LUN 1348.XX Propeller speed indicator
35.
Testing equipment ROSE (Read Out Support Equipment) Version 3.9a (17TES0321) (for FA 2200) + CICC/3 Computer Interface Communication Cable / 2 17TES0075 and CAT 5 E Crossover Cable to Ethernet Port 024-98-00386
17ТЕS0321 (95236059); CAT 5e Crossover cable 024-98-00386 (95236065) ;+ 17ТЕS0075 (95236066)
Maintenance, Testing and calibration of FDR
36.
Rotating table + Reduction base
IDEAL & AEROSMITH Model 1310-1-L-90 (95216964); + B599000N
Positioning of the gyro source
37.
Extender cable for AHRS
B598959N
-
EFFECTIVITY ALL
Type (Ord. No.)
Note
012.00.00 Page: 55 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Type (Ord. No.)
Note
38.
Check Template for elevator
B096981N
-
39.
Fixture for rudder and rudder trim tab angle measuring
B598887N (valid for airplane with the M601 Turboprop engines) or
valid for airplane with the M601 Turboprop engines
B098758N (valid for airplane with the H80-200 Turboprop engines) 40.
Adjusting fixtures kit for nose landing gear (1 pc)
B096674N
Check of the function of MANUAL and PEDAL nose landing gear steering
41.
Testing Cable (1 pc)
Z 921 (98110275)
LUN 3192-8 Hydraulic thermo switch
42.
Multifunction Calibrator
FLUKE 724 (95216979)
Accurate calibration source for Thermocouple, mA, mV, V and Frequency devices
or EXTECH 422123 (95216980)
43.
Testing Cable -
Z 920 (98110280)
Testing cable for ITT and LUN 1370
44.
Programmable DC Power Supply (2 pc)
EXTECH 382280 (95216981)
-
EFFECTIVITY ALL
012.00.00 Page: 56 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
45.
NiCd/NiMH battery charger + B598991N Connecting Cable
Voltcraft ALC8500 EXPERT (95224213) + B598991N
Maintenance of the battery of emergency lighting
46.
Digital multimeter with temp. probe and Insulation tester (2 pc)
EXTECH MG302 (95227412)
-
47.
Microohmmeter
EXTECH 380462 (220V) (95216984)
Portable Milliohm meter provides resolution to 100µOhm
48.
BR07 Resistance decade + 2RMT14 KPN 4G1V1 Socket
90910110 + 91721430
Check of the correct operation of the TER-1M thermoregulators
49.
Battery charger/Analyzer
RF 80-K CE (95224216)
Maintenance of the on board battery of airplane
50.
Smart cable + PCMCI card for EGPWS update
951-0386-001 (B503704N)
If installed the EGPWS Honeywell MARK VI
51.
Testing cable for EGPWS
704-2617-001 (B503705N)
If installed the EGPWS Honeywell MARK VI
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 57 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
52.
Assembly floor board (1 pc)
B596331N
Working in the fuselage rear section
53.
Breaking piece (4 pcs)
B067345N
Intended for securing the closing valve of fire extinguisher bottle
54.
Nose cover strut
B596546N
For nose cover fixing
55.
Oil discharge hose (1 pc)
B954095N or L410.9544
Discharging oil from the engine
56.
Grounding device of the airplane (1 pc)
B096432N
Grounding the airplane
57.
Tractor towing equipment (1 pc)
B097581N (Ø 40mm)
Towing the airplane by means of tractor
58.
Oil filling funnel (1 pc)
B096242N
Replenishing engine oil
59.
Hose (2 pcs)
B964201N or L410.9643
Brake system bleeding and flushing
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 58 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
60.
Vessel for venting of hydraulic pumps (1 pc)
B097480N
Hydraulic system venting
61.
Hose for hydraulic pumps venting (1 pc)
B097485N
Hydraulic system venting
62.
Kit for fuel drain (1 pc)
B097441N
Drain of fuel filter
63.
Stairs of engine (1 pc)
B097300N
Engine servicing
64.
500 CSN 231462 Lever press (1 pc)
95273405
Forced lubrication of lubrication points provided with grease nipples
1000 CSN 231492.3 Lubrication hose (1 pc)
95273417
For forced lubrication (to be connected to the lever press)
65.
Configuration cable for PS 578A
B598891N
If installed TCAS II Honeywell CAS67A/B
66.
Testing cable for TCAS
B598893N
If installed TCAS II Honeywell CAS67A/B
67.
RS-232 Software update and Configuration cable for connection PC with GTX 3000 Transponder
B098761N
If installed Garmin GTX 3000 Transponder
68.
Cable for connection PC with GTS 8000 processor and/or Wx Radar GWX 70
91671491
If installed GTS 8000 processor and /or Garmin GWX 70 Wx Radar
69.
Testing cable for ESI 2000 Electronic Standby Indicator (if installed)
Y348432N
For battery calibration procedure of the ESI-2000 (if installed) in the testing room
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 59 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
72.
Testing cable for KRA 405B Radar Altimeter
B598892N
-
73.
Fuel discharge hose (1 pc)
B096116N
Discharging fuel from the main fuel tanks
74.
Hydraulic liquid drain hose (1 pc)
B954089N or XL410.9543
Drainage of hydraulic fluid
75.
Blocking of the elevator trim tab control cables (2 pcs)
B598975N
if is autopilot installed
76.
P/N T1134610 Enviro belt tensioning tool P/N FDK-10 Wagner spring scale
95225872 95225873
if is the ENVIRO Air condition system installed
77.
Service trolley (1 pc)
B968051N or L410.9682
Laying of tools and components
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 60 Nov 20/15
MAINTENANCE MANUAL
1.2. Sets of tools Ser. No.
Name and figure
Note
1.
Universal tools kit (1 pc)
B598973N
-
2.
Tools for propeller and engine (1 pc)
B598992N
-
3.
Tools for the landing gear and hydraulic system (1 pc)
B596333N
-
4.
Tools for el. equipment engineer (1 pc)
B096477N
-
5.
Tools for the aircrew (1 pc)
B096470N
-
6.
Special tool (1 pc) (includes B598626N , B598627N , B598628N)
B598625N
-
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 61 Nov 20/15
MAINTENANCE MANUAL
1.3. Optional equipment Ser. No.
Name and figure
Note
1.
Device for washing the compressor
B959801N or L410.9591
2.
Rubber wheel
B963125N or L410.9631
For the repair of rubber deicers
3.
Knurled wheel
B963135N or L410.9632
For the repair of rubber deicers
4.
Reduction piece
B596525N
Reducer for filling of extinguisher
5.
Guidance spine for NLG
B097534N
Installation and removal of nose landing gear
6.
Blinder
B851020N or L410.8510-6
-
7.
Engine suspension (1 pc)
B967051N (XL410M.9671)
Engine removal
8.
Trolley for engine (1 pc)
B968101N (L410M.9681)
Engine accommodation and transport
EFFECTIVITY ALL
Type (Ord. No.)
-
012.00.00 Page: 62 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
9.
Propeller suspension (1 pc)
B596430N
Propeller lifting during its installation and removal
10.
V510 and/or AV-725 Propeller stand (1 pc)
B966119N (XL 410.9660)
Propeller accommodation and transport
11.
Calibrated vessel for distilled water (1 pc)
B598602N
Filling the water tank of the water injection system (only if the water injection system is installed)
12.
Winter cover of the cooler, front part (2 pcs)
B596570N
Covering of oil cooler
13.
Winter cover of the cooler, rear part (2 pcs)
B596571N
Covering of oil cooler
14.
Oil cooler insulation (2 pcs)
B596572N
Covering of oil cooler
15.
SOEHNLE Professional 3030 Weighing equipment
B598960N
Airplane weighing
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 63 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Note
16.
Boroscope HDV640W
B598990N
-
17.
17TES0065 Testing equipment for CVR
95236063
-
18.
17TES0078 CVR download cable
95236068
-
19.
Testing equipment for LUN 3170
B596455N
-
20.
Mounting device (1 pc)
B096024N
Windshield wiper installation
21.
Cable for battery charging of MCI4300-4XX Electric Attitude Indicator (if installed)
B598989N
-
22.
Guidance spine for stabilizer (1 pc)
B960095N or XL410.9600-02
Stabilizer installation and removal
23.
Guidance spine for fin (1 pc)
B960316N or L410.9600-06
Removal of bolts connecting fin to the fuselage
24.
Guidance spine for wing (1 pc)
B960581N L410.9600-08
Locating wing pins
25.
Guidance spine for fin (1 pc)
B096025N
Installation of fin pins
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 64 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Type (Ord. No.)
Note
26.
Puller (1 pc)
B960097N or XL.410.9600-04
Removing wing pins
27.
Reducer (1 pc)
B598700N
(M14x1)x(9/16-18)-Oxygen (SCOTT / AVOX ZODIAC)
28.
Testing equipment for leakage test of fuel system (1 set)
HA-5011-13 (95216910)
Leakage test of fuel system
29.
Three-points Internal Micrometer (Mitutoyo 368-165) – 1 set
71042046
Hole test of the connection Wing to Fuselage 17H7 (front and rear connecting points)
30.
Gauge ,diam 10H7mm, 12H7mm, 13H7mm, 17H7mm (1 set)
10H7 = 72131007
They are calibers for hole test of the connection:
12H7 = 72131207 13H7 = 72131307 17H7 = 72131707
Fuselage to Horizontal Stabilizer 10H7 (front and rear connecting points) Fuselage to Vertical Stabilizer 12H7 (front connecting point) Fuselage to Vertical Stabilizer 13H7 (rear connecting point) Wing to Fuselage 17H7 (front and rear connecting points)
31.
Wing supporting stand (4 pcs)
112-610-1800B (PV112-610-1800B)
Support of the wing
32.
Micrometer 0-25 (Mitutoyo Digimatic 293-240)
70389306
-
33.
Control pins (3 pcs/ 1 set)
112-316-16269 (PV112-316-16269)
Tools use for reaming procedure of Wing to Fuselage hinges
34.
Assembly pins (16 pcs/ 1 set)
12-610-2988 (PV12-610-2988)
Tools use for reaming procedure of Wing to Fuselage hinges
35.
Reamer (6 pcs/ 1 set)
112-246-14104 (PV112-246-14104)
Tools use for reaming procedure of Wing to Fuselage hinges
36.
Reverse Countersink (4 pcs/ 1 set)
12-254-3730 (PV12-254-3730)
Tools use for reaming procedure of Wing to Fuselage hinges
37.
Puller (1 pc)
112-523-16333 (PV112-523-16333)
Tools use for reaming procedure of Wing to Fuselage hinges
EFFECTIVITY ALL
012.00.00 Page: 65 Nov 20/15
MAINTENANCE MANUAL
Ser. No.
Name and figure
Type (Ord. No.)
Note
38.
Ground Power Unit (1 pc)
GPU 600 (95250035)
-
39.
Check Template for Rudder and Rudder trim tab (1 pc)
B098571N
Measuring rudder and rudder trim tab deflections
Base plate (1 pc)
B098595N
Base plate for B098571N check template
Check Template for Ailerons (rib No. 25)
12-164-1714
-
40.
1.4. Set of Software Ser. No.
Name and figure
Note
1.
GWx 7x Install Tool
006-A0436-00
If installed Garmin GWX 70 Wx Radar
2.
GTS Install Tool
006-A0242-10
If installed GTS 8000 processor and /or Garmin GWX 70 Wx Radar
3.
GTX 3000 Install Tool
006-A0249-00
If installed Garmin GTX 3000 Transponder
4.
Trilogy Configuration Tool
576-6217-01 (95219741)
If installed ESI-2000 Electronic Standby Trilogy Instrument
EFFECTIVITY ALL
Type (Ord. No.)
012.00.00 Page: 66 Nov 20/15
MAINTENANCE MANUAL
AIRFIELD SERVICING SERVICING 1. Taking over the aircraft from the crew A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.A Routine
E.
Procedures (1) Work site - apron (2) Take over from the crew: • the log book • the aircraft keys (3) Check the flight compartment and passenger's area including the toilet room and luggage compartments that no foreign objects have been left in the aircraft. Check at the same time, that no objects of the outfit are missing (as safety belts, box with spare fuses, portable lamp, earphones with microphone, axe, extinguishers, seat covers, rescue waistcoat, first aid boxes and portable oxygen apparatuses). (4) Check in the crew cabin that the window is closed and the aircraft has been parked by the parking brake. (5) When leaving the aircraft, remove the embarkation steps and close and lock the entrance door.
2. Taking over the report about aircraft technical conditions from the crew A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.B Routine
E.
Procedures (1) Work site - apron
EFFECTIVITY ALL
012.00.00 Page: 301 Nov 1/11
MAINTENANCE MANUAL (2) Find out the aircraft technical condition from the direct information of the crew and according to the records in the log book.
3. Aircraft inspection A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.C Routine
E.
Procedures (1) Work site - apron (2) Check the aircraft and make sure that no mechanical damages are apparent on the aircraft; when taking over the aircraft; when taking over the aircraft from the crew, this check is advantageous. (3) When the temperature is over +30°C: cool the brakes of main landing gear wheels with water after aborted take off and during training (repeated) landings.
4. Aircraft final inspection A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.D Routine
E.
Procedures (1) Check (according the diagram of the aircraft inspection route) the left wing, left-hand engine nacelle. Fuselage rear section, tail planes, right wing, right-hand engine nacelle, fuselage front section, undercarriage nacelles, main and nose landing gear. Make sure, that: •
skin fuselage, wings, flaps, ailerons, tail planes is not damage
•
the fuel is not spilled, nor the oil and hydraulic liquid in the places of tanks sealing, piping and aircrafts assemblies
•
all assembly lids are closed
•
blocking struts from control areas have been removed.
EFFECTIVITY ALL
012.00.00 Page: 302 Nov 1/11
MAINTENANCE MANUAL (2) Check (from the ground) the function of aircraft control surface (rudders, ailerons) when the crew is doing the inspection. Rudders and ailerons during the movement must not squeal and touch the aircraft construction elements. (3) Check the anti-collision beacons and position lights (in the night or at limited visibility). Anti-collision beacons must product regular light signals and the position lights must be on. (4) Make sure that within aircraft expected movement no foreign objects are present.
FIG. 301
AIRCRAFT INSPECTION ROUTE A – Inspection starting point
EFFECTIVITY ALL
012.00.00 Page: 303 Nov 1/11
MAINTENANCE MANUAL
5. Engines start-up observation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.E Routine
E.
Procedures (1) Either transparent gas stream of greyish shade of transparent fume must be discharged from engine exhaust pipes. (2) Make sure that no fuel or oil is leaking in the engine nacelles zone. (3) No backfiring of the engine is allowed during the engine start-up or heating operation. (4) If procedures 1, 2 and 3 are not met, immediate signal has to be given to the crew to stop engine start-up operation.
6. Connection of electric ground source A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Electric ground source
D. Referenced information
-
E.
Procedures (1) Work site - apron (2) Connect the electric ground source to the aircraft via the socket of external source type SHRAP 500 located on the left-hand side of fuselage front section under the lid and provided with the marking: 28V, 500A
EFFECTIVITY ALL
012.00.00 Page: 304 Nov 1/11
MAINTENANCE MANUAL
FIG. 302
EXTERNAL SOURCE SOCKET
7. Main door opening and boarding steps placing A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C.
Tools
Not applicable
D.
Referenced information
012.00.00.F Routine
E.
Procedures (1) Work site - apron (2) Unlock and open the main door. Release the steps fastened on passenger compartment by releasing the belt on the floor of passangers compartment or release the steps fastened in the case in front of the toilet or on the left hand side. Turn partially the pawl on the beam of steps upper fastening, take the steps out and placed it into the holes of main door threshold.
EFFECTIVITY ALL
012.00.00 Page: 305 Nov 1/11
MAINTENANCE MANUAL
8. Removal and fitting of safety pins (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.G Routine
E.
Procedures CAUTION:
THE SAFETY PINS ARE TO BE REMOVED BEFORE EACH FLIGHT AND PUT BACK AFTER THE FLIGHT HAS BEEN FINISHED.
(1) Remove the cap 1 covering the pushbutton 3 – see Fig.303 (2) Remove the safety pin 2 provide with a flag from the hole in the pushbutton 3. Put the safety pin into a pocket on the RH side of the cockpit. (3) Proceed in the opposite sequence to put the safety pin back.
FIG. 303
REMOVAL AND FITTING OF SAFETY PINS (1) Cap, (2) Safety pin with flag, (3) Push button
EFFECTIVITY ALL
012.00.00 Page: 306 Nov 1/11
MAINTENANCE MANUAL
9. Boarding steps removing and closing of main doors A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.H Routine
E.
Procedures (1) Work site – apron (2) Take out the steps from the holes in main door treshold and fasten it on the passangers compartment (tighten and secure the belt on passengers compartment floor and turning the pawl on steps upper beam). Or take out the steps from the holes in the main door threshold and fasten it into the case in front of the toilet on left - hand side. (3) Close and lock the main doors.
10. Checking of control elements and switches in the pilot cockpit A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.I Routine
E.
Procedures (1) Work site – apron (2) Check if all switches and circuit breakers installed in overhead panel are in OFF position (3) Check: •
If the control lever of landing gear is in position DOWN
•
If the control levers of fuel closing cock are in position FUEL-CLOSED
•
If the parking brake lever is in position STOP
•
If the windows are closed
EFFECTIVITY ALL
012.00.00 Page: 307 Nov 1/11
MAINTENANCE MANUAL
11. Closing and locking doors A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.J Routine
E.
Procedures (1) Work site – apron (2) After concluding the works on the aircraft remove the embarkation steps and put it inside the aircraft. Close the door of emergency exit and secure it inside by turning the bar. Check the seal of the emergency exit. (3) Close and lock the entry door.
12. Aircraft exterior inspection A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.K Routine
E.
Procedures (1) Check (according to the diagram of the aircraft inspection route) the left wing, left-hand engine nacelle, fuselage rear section, tail planes, right wing, right-hand engine nacelle, fuselage front section, undercarriage nacelles, main and nose landing gear. Make sure, that: •
skin of fuselage, wings, flaps, ailerons, tail planes is not damaged;
•
the fuel is not spilled, nor the oil and hydraulic liquid in the places of tanks sealing, piping and aircrafts assemblies;
•
there are not fuel leakage from drain piping or from drain holes on the lower side of the lefthand and right-hand wings at fuel tanks locations
•
EFFECTIVITY ALL
all assembly lids are closed; blocking struts from control areas have been removed
012.00.00 Page: 308 Nov 1/11
MAINTENANCE MANUAL (2) Check (from the ground) the function of aircraft control surfaces (rudder, ailerons) when the crew is doing the inspection. Rudder and ailerons during the movement must not squeal and touch the aircraft construction elements. (3) If installed, check (from the ground) the surfaces of the glued deicing sections on leading edges of the wing, stabilizer and fin. The following defects are not permitted: •
surface contamination of deicers with oil from the engine or by the exhaust gases
•
cracks in the deicing sections
•
peeling of the protective paint
•
any releasing of deicers within the edges (Detailed description of defects is in section 030.10.00)
(4) Inspect the aircraft from a distance of 10 – 15 m and determine, if the aircraft is not banked (the aim of this evaluation is the rough estimation of equal compression of main landing gear shock absorbers). Check visually, if the shock absorber piston rods of the main and nose landing gear are not compressed fully. (5) Clean the surface of shock absorber piston rods of main and nose landing gear and be sure that no leakage and un-tightness of sealing for the hydraulic liquid either in form streams or drops of hydraulic liquid are on shock absorber piston rods. A film of hydraulic liquid on shock absorber piston rods is allowed. In case of defects see pages 401 – 4XX of the section 032.10.00 or 032.20.00. (6) Inspect the condition of tires of main and nose landing gear and be sure, that the tires are not damaged. Check the inflation of tires as per compression - if in doubt; check the inflation of tires with the pressure gauge. (7) Inspect the cylinder of the nose landing gear wheel servo control. Dripping of the hydraulic liquid max. 5 drops / hour is allowed. In case of defects the servo control cylinder must be replaced. (8) Inspect the laminate cover carefully and make sure whether there are not soiling, ruptures, occurrence of pulverizing, un-sticking, ruptured part of laminate layer and laminate broken through or else very damaged laminate cover. (9) Inspect if there are not foreign objects or dust in the air intake channels of the left-hand and right-hand engine nacelle lower cowls. During the inspection propellers must be blocked. (10) Check the function of the anti-collision beacons and position lights (in the night or at limited visibility). Anti-collision beacons must product regular light signals and the position lights must be on. (11) Make sure, that within aircraft expected movement no foreign objects are present.
EFFECTIVITY ALL
012.00.00 Page: 309 Apr 5/13
MAINTENANCE MANUAL
FIG. 304
AIRCRAFT INSPECTION ROUTE A – Inspection starting point
13. Door control and steps installation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.L Routine
E.
Procedures (1) Work site – apron (2) BEFORE FLIGHT (a) Main door opening and boarding steps placing.
EFFECTIVITY ALL
012.00.00 Page: 310 Nov 1/11
MAINTENANCE MANUAL •
Unlock and open the main door
•
Release the steps fastened in the passenger compartment by releasing the belt on the floor of the passenger compartment or release the steps fastened in the case in front of the toilet or on the left hand side.
•
Turn partially the pawl on the beam of steps upper fastening, take the steps out and place it into the holes of the main door threshold.
(b) Removal and fitting of emergency exit safety pins (if installed) CAUTION:
THE SAFETY PINS MUST BE REMOVED BEFORE EACH FLIGHT.
•
Remove the cap (1) covering the pushbutton (3) – see Fig. 305.
•
Remove the safety pin (2) provided with a flag from the hole in the pushbutton (3). Put the safety pin into a pocket on the RH side of the cockpit.
FIG. 305
REMOVAL AND FITTING OF SAFETY PINS (1) Cap, (2) Safety pin with flag, (3) Push button (3) AFTER FLIGHT (a) Installation of emergency exit safety pins (if installed) CAUTION: •
THE SAFETY PINS MUST BE INSTALLED AFTER EACH FLIGHT.
Remove the safety pin (2) provided with a flag from the pocket on the RH side of the cockpit. Push in the safety pin into the hole in the pushbutton (3) - see Fig. 305.
•
Set the cap (1) covering the pushbutton (3) on the place.
(b) Boarding steps removing and main door closing •
Take out the steps from the holes in the main door threshold and fasten it on the passenger compartment (tighten and secure the belt on passengers compartment floor and turning the pawl on steps upper beam). Or take out the steps from the holes in the main door threshold and fasten it into the case in front of the toilet on left - hand side
EFFECTIVITY ALL
012.00.00 Page: 311 Nov 1/11
MAINTENANCE MANUAL •
Close and lock the main door.
14. Checking of control elements and switches in the pilot cockpit A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
012.00.00.M Routine
E.
Procedures (1) Work site – apron (2) Safety precaution •
Check if BATTERY I and II switches on the overhead panel are switched OFF
(3) Check of switches and circuit breakers on the overhead panel and control elements in pilot’s cabin. Technical requirements are specified in articles 4, 5 (4) Check if all switches and circuit breakers installed on the overhead panel are in the OFF position. If not, switch off the switches and circuit breakers. NOTE:
The position “SWITCHED OFF” is labeled on the overhead panel.
(5) Check if: •
the control lever of the landing gear is in the DOWN position
•
the control levers of the fuel closing cocks are in the FUEL-CLOSED position
•
the parking brake lever is in the STOP position
•
the windows are closed
If not, set the appropriate control element to the required position.
EFFECTIVITY ALL
012.00.00 Page: 312 Nov 1/11
MAINTENANCE MANUAL
TOOLS DESCRIPTION AND OPERATION 1. General NOTE:
The tooling shown in section 012.00.00 is the recommended one. An equivalent tooling may be used instead.
EFFECTIVITY ALL
012.00.01 Page: 1 Nov 20/15
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
012.00.01 Page: 2 Nov 20/15
MAINTENANCE MANUAL
GROUND EQUIPMENT DESCRIPTION AND OPERATION 1. General Following section comprises figures and descriptions of those ground equipment components, which need more detailed description.
A.
Hydraulic truck No.0406 02220 (6999 AF) Hydraulic truck serves for testing, filling and washing of hydraulic system. Frame of the truck, welded from steel sheets is placed on three wheels. The truck is provided with towing device enabling towing by car-dismountable towing bar is provided for this purpose. The pressure source is piston pump with pressure control NP 34-27 driven by petrol engine, two-stroke, two-cylinder air cooled, type ZB8. Hand operated pump RGK mounted on the truck serves for tank filling of aircraft hydraulic system. Hydraulic truck operating instructions are indicated on the hydraulic truck plate.
EFFECTIVITY ALL
012.00.02 Page: 1 Nov 20/15
MAINTENANCE MANUAL
FIG. 1
HYDRAULIC TRUCK NO.0406 02220 (6999 AF) (1) Body; (2) Frame; (3) Engine mount (4) Drive; (5) Filter bracket; (6) Exhaust damper; (7) Cock; (8) Cooler; (9) Discharge nozzle; (10) Tank; (11) Pump PN 34-2T; (12) Filter FG 11-18; (13) Valve 652000; (14) Optical filter; (15) Pump RGK; (16) Pressure gauge MG 250; (17) Safety valve GA-89; (18) Valve 8 LUN 7373; (19) Distributor; (20) Tank
EFFECTIVITY ALL
012.00.02 Page: 2 Nov 20/15
MAINTENANCE MANUAL B. HYDROCOM - MA-801-03 Hydraulic truck Mobile pressure source for functional tests of hydraulic systems for airplane. Aggregate description The drive itself is placed on a carriage; it is compound of an electromotor (12) - see fig. 2 -and a (10), a filter (13), a relief valve (15), a back-pressure valve (16), a hydraulic accumulator (20) and a throttle valve (26). There is a globe shut-off valve (25) and a quick coupling plug socket (31), to which hoses (30) are attached with a male plug of the quick coupling (31). On the second end of the hose there is a reducing piece of a screw fitting. Suction is performed with a hose (32) by means of a screw fitting reducing piece and quick couplings (33). Function description As soon as the electromotor is running, at first the hydraulic accumulator (20) is filled up and when the operation pressure in the circuit is achieved, the relief valve (13) is opened and oil is drained to the pump suction. With pressure oil bleeding in the airplane circuit the relief valve is automatically closed. For pressure indication there is a manometer (27) inserted in the circuit. For possible reduction of the oil flow rate to the circuit there is the throttle valve (26) in the pressure branch, which bleeds a portion of oil back to the pump suction. Hydraulic power unit parameters Hydraulic power unit type •
Volume delivered
Q = 9dm3.min-1
•
Operating pressure
p = 150bar
•
Pump
OT200 P06D/G 28 P2 standard 1/2
•
Electric motor
1LA7107-4AA11,3/3,45kW
•
Main electric motor power demand
P = 3kW
•
Main electric motor revolutions
n = 1420min-1
•
Electric motor voltage
400/230V; 50Hz
•
Hydraulic fluid
mineral oil Aeroshell Fluid 41
•
Operating temperature
25 to 55°C
•
Filtration
minimal class of purity 9 acc. to NAS1638
•
Weight
75kg
•
Proportions
890x365x970mm
•
Noise
6
440
290
-
12 13
3.1355 (AlCuMg2)
2024 (2024) 2024-ISO
42 4253.62
0.2-2.5 2.5-10
400 420
260 270
-
13 11
DIN 1745
Alclad 2024 2024-ISO
42 4400.00
6-63
100
-
-
(16)
3.2318 (AlMgSi1)
6061 (6082) 6082-ISO
Z42 4201.01
-
max. 290
-
-
-
3.1325 (AlCuMg1)
2014(2014A 2017A-ISO
Z42 4203.62
0.2-10
440
295
-
13
3.1355 (AlCuMg2)
2024 (2024) 2024-ISO
Z42 4253.11
0.2-10
max. 240
-
-
12
DIN 1745
Alclad 2024 2024-ISO
Z42 4400.15
0.2-10
110-150
50-80
(18)
15
3.2318 (AlNgSi1)
6061 (6082) 6082-ISO
Z42 4400.62
0.2-10
200
120
(17)
15
3.2318 (AlMgSi1)
6061 (6082) 6082-ISO
Z42 4412.15
0.2-10
160-200
65
(18)
15
3.3523 (AlMg2Mn0.3)
5052 (5251) 5052-ISO
Z42 4412.25
0.2-6
200-250
120
(9)
8
3.3523 (AlMg2Mn0.3)
5052 (5251) 5052-ISO
Z42 4415.11
0.5-6
245
-
-
19
3.3555 (AlMg4Mn)
5086 (5003) 5086-ISO
Z42 4418.15
1.6-10
310
155
-
15
-
-
Z42 4432.14
0.2-6
100-150
-
(22)
20
3.0515 (AlMN1)
3003 (3103) 3003-ISO
Z42 4432.25
0.2-3
150
100
(8)
6
3.0515 (AlMni)
3003 (3103) 3003-ISO
1
D16AM
0.5-1.9
150-225
-
-
10
DIN 1745
Alclad 2024 2024-ISO
D16AT
0.5-1.9
407
270
-
13
DIN 1745
Alclad 2024 2024-ISO
D16AMO
0.5-1.9
225
-
-
10
DIN 1745
Alclad 2024 2024-ISO
D16 ATV
0.5-1.9
407 390
270 340
-
13 5
DIN 1745
Alclad 2024 2024- ISO
EFFECTIVITY ALL
020.10.00 Page: 808 Nov 1/11
MAINTENANCE MANUAL
1
2
3
4
5
6
7
8
D1S
11-40
390
255
-
8
DIN 1745
Alclad 2024 2024-ISO
AMCAM
0.5-30
98-150
-
-
22
3.0515 (AlMni)
3003(3103) 3003-ISO
AMG 6 BM
0.6-10
310
160
15
-
-
-
AMG 5M
0.6-4.5
275
150
-
15
3.3555 (AlMg4Mn)
5086 5086-ISO
APSM
0.8
78
-
-
18
-
-
MA8M
8.0-3.0 3.1-10
225 215
137 127
-
14 12
-
-
Aluminum-clad metal sheets (4 to 6 par cent or the sheet thickness). Silumin-clad metal sheet (Si 11 to 12.5 per cent. Mg 0.05 per cent max., Al-the rest) 3 to 12 percent of the sheet thickness
Magnesium alloy
Metals, Non-Ferrous, Light 1
Tubes
2
3
4
5
6
7
8
-
60-90
-
(30)
28
3.0255 (Al99.5)
1050(1050A) 1060-ISO
22 22
410-430
250 290
11
14 10
3.1355 (AlCuMg2)
2024 2024-ISO
42 4400.60
-
200
-
-
-
3.2318 (AlMgSi1)
6061(6082) 6061-ISO
42 4412.11
-
150-210
-
18
16
42 4432.11
-
90-150
-
18
16
3.0515 (AlMn1)
3003 3003-ISO
Z42 4203.61
-
440
315
11
10
3.1355 (AlCuMg2)
2024 2024ISO
Z42 4203.11
-
180-260
80-155
14
12
3.1355 (AlCuMg2)
2024 2024ISO
Z42 4400.61
-
200
100
17
15
3.2318 (AlMgS11)
6061(6082) 6061-ISO
Z42 4412.11
-
150-220
-
18
16
3.3523 5052 (5251) (AlMg3Mn0.3) 5052-ISO
Z42 4412.21
6-150
210
120
7
6
3.3523 5052 (5251) (AlMg3Mn0.3) 5052-ISO
42 4005.11 42 43.61
EFFECTIVITY ALL
3.3523 5052(5251) (AlMg2Mn0.3) 5052-ISO
020.10.00 Page: 809 Nov 1/11
MAINTENANCE MANUAL
1
2
3
4
5
6
7
8
Z42 4432.11
-
90-150
-
18
16
3.0515 (AlMn1)
3003 3003-ISO
Z42 4432.21
6-150
150
80
7
6
3.0515 (AlMn1)
3003 3003-ISO
AMG 2M
-
155-220
-
-
15
AMG 6M
-
315
145
-
15
-
-
Metal, Non-Ferrous, Light 1
3.3523 5052(5251) (AlMg2Mn0.3) 5052-ISO
Profiles
2
3
4
5
6
7
8
42 4203.61
10
410
290
12
11
3.1355 (AlCuMg2)
2024 2024ISO
Z42 4441.61
20
290
150
11
10
3.4335 (AlZn4Mg1)
7005 (7020) 7005-ISO
Z42 4441.71
20
320
275
9
8
3.4335 (AlZn4Mg1)
7005 (7020) 7005-ISO
Z42 4203.11
-
180-260
90-155
14
12
3.1355 (AlCuMg2)
2024 2024-ISO
Z42 4203.61
2 2
440 450
325 335
12 11
11 10
3.1355 (AlCuMg2)
2024 2024-ISO
016T
5
400
305
-
10
1.1355 (AlCuMg2)
2024 2024-ISO
016M
5
max. 245
-
-
12
3.1355 (AlCuMg2)
2024 2024-ISO
Metal, Non-Ferrous, Light 1
Bars
2
3
4
5
6
7
8
42 005.11
-
60-90
-
30
28
3.0255 (Al99.5)
1060(1050A) 1050-ISO
42 4005.21
-
90-140
-
6
5.5
3.0255 (Al99.5)
1060(1050A) 1060-ISO
42 4400.71
8-100 t 40
270
195
11
9
3.2318 (AlMgS11)
6061(6082) 6061-ISO
42 4412.11
-
160-220
-
18
16
42 4432.11
-
90-140
-
18
16
3.0515 (AlMn1)
3003 3003-ISO
Z42 4203.01
-
210
-
11
10
3.1355 (AlCuMg2)
2024 2024-ISO
Z42 4203.61
10 10-63
460-470
320-335
8
7
3.1355 (AlCuMg2)
2024 2024-ISO
EFFECTIVITY ALL
3.3523 5052(5251) (AlMg2Mn0.3) 5052-ISO
020.10.00 Page: 810 Nov 1/11
MAINTENANCE MANUAL
1
2
3
4
5
6
7
8
Z42 4400.71
10-22 22-63
280 290
230 240
10 9
8 8
3.2318 (AlMgSi1)
6062 (6082) 6061-ISO
Z42 4418.11
-
310-390
150
16
13
-
-
Z42 4432.11
-
100-160
-
20
18
3.0515 (AlMn1)
3003 3003-ISO
Z42 4432.21
12 12-40
150
80
78
56
3.0515 (AlMn1)
3003 3003-ISO
D16T
do 10 10-70
450 460
315 325
-
8
3.1355 (AlCuMg2)
2024 2024-ISO
5-300
314
157
-
15-
-
AMG 6M
Metal, Non-Ferrous, Light 1
Wires
2
3
4
5
6
7
8
42 4004.11
-
max. 100
-
-
-
3.0255 (Al99.5)
1350
42 4005.11
-
max. 100
-
-
-
3.0255 (Al99.5)
1060(1050A) 1060-ISO
42 4203.61
2.65 3.75
440
-
260
+)
-
3.1355 (AlCuMg2)
2024 2024-ISO
42 4204.61
-
-
-
190
+)
-
AlCu2.5Mg0.5
2117
+) shear strength Metal, Non-Ferrous, Light 1
Foils
2
3
4
5
6
7
8
42 4005.11
0.2-0.4 0.5-10
60-100
-
-
25
3.0255 (Al99.5)
1060(1050A) 1060-ISO
42 4005.31
0.2-0.4 0.5-3.5
140
-
-
3
3.0255 (A199.5)
1060(1050A) 1060-ISO
EFFECTIVITY ALL
020.10.00 Page: 811 Nov 1/11
MAINTENANCE MANUAL
NON-FERROUS METAL IDENTIFICATION Identification number schema
Supplementary digit meaning: The meaning of the first and the second supplementary digit is given in the following Table: Material designation incl. supplementary digits
Product quality Hot formed products
42 ++++.00
commercial grade hot formed
.01
annealed, guaranteed quality Gold formed products
42 ++++.11 .14
without guaranteed Rp 0.2 guaranteed quality soft
.15
deep-drawing, quarantined quality with quarantined Rp 0.2 quarantined quality
.21
without quarantined Rp 0.2, quarantined quality 1/2 hard
.25 42 ++++.31
with quarantined Rp 0.2 quarantined quality hard
without quarantined Rp 0.2, quarantined quality
Cold formed products 42 ++++.41
hardness as for spring mat quarantined quality -
.51
double hardness as for spring material quarantined quality Hot or cold formed cold hardened products
42 +++.60
cold hardened quarantined quality
61
cold hardened, with quarantined Rp0.2
62
plug equalized
quarantined quality
Hot or gold formed, hot hardened products 42 +++.71
EFFECTIVITY ALL
hot hardened, with guaranteed Rp0.2
quarantined quality
020.10.00 Page: 812 Nov 1/11
MAINTENANCE MANUAL
Welding and soldering material Information properties
Material designation
Approximate equivalent +)
Rm MPa
++)
B-Sn 30 Pb 250/185
260-300
-
min. 31
DIN 1707 BS 219
B-Sn 40 Pb 225/185
230-270
-
min. 32
DIN 1707 BS 219
B-Sn 50 Pb 215/185
220-265
-
min. 35
DIN 1707 BS 219
B-Sn 60 Pb 190/185
200-240
-
min. 40
DIN 1707 BS 219
B-PbAg2Cu 325/300
330-380
-
min. 20
DIN 1707
B-Cu6OZnSi 900/880
min. 240
min. 100
920-950
DIN 8513 Blatt 1
min. 150
min. 100
B-AlSi12 590/575
600-640
60-65
60-65
Pb48Sn3281 (Plumbia 6) B-Ag50CuZnCd 740/630
ASTM B 260 DIN 8512 BS 1845
130
ASTM B 260 -
min. 300
min. 100
min. 170
min. 80
750-790
-
E 434 B 110.20 E4343 B 10
(H) ISO 2560 DIN 1913
E-B 121
-
440-540
A5 26%
E-B 223
-
1030-1180
-
E-B 420 (E-B 419)
-
540
A5 20%
G A1-Si5
Rp 0.2 50 MPa
110
A5 6%
G 102
-
373
A5 15%
G1 00 45
DIN 8554 (G 38) RG AWS/ASME SFA-5.2
G1 420 (G 419)
-
580
A5 30%
SGX5 CrNiNb199 ER 347
DIN 8556 (Cr420) ASW/ASME SFA5-9
G 421
-
550-650
A5 30%
GX 12CrNiMo ER 308 Mo
1910 DIN 8556 AWS/ASME SFA-5.9
650
min. 108
A5(16%)
3.0515 (DIN) 3003 (USA)
Rp0.2 8O MPa
min. 190
-
3.3555 (DIN) 5086 (USA)
42 4432.10(11) (MnA1-Mn) AMG5 (G-AlMg5)
E 19.9 Nb B20I E 19.9 Nb B20
ISO 3581 DIN 8556(1.4551) -
Wolfram +) Working temperature (°C) ++) Strenght in skid Rma (MPa) For this solder is validity value:
in first line for material in second line for material.
EFFECTIVITY ALL
020.10.00 Page: 813 Nov 1/11
MAINTENANCE MANUAL
(c) Material group: Bearings Place an order with the manufacturer, or ask for specifications and use the home products of the comparable quality. (d) Material group: Conductors Place an order with the manufacturer, or ask for specifications and use the home products of the comparable quality. (e) Material group: Paints Place an order with the manufacturer, or replace it with products of highest quality used for the aircraft products in your country. There are coating products used by AI in the table. It is possible to use coatings same characteristics of other manufacturers in case of unavailability of them. Some examples of possible equivalents are shown in the table: Equivalents Coatings used AI PPG
AkzoNobel
Du Pont
Glasurit
Epoxy primer S 2318
PR 143
Alumigrip 4144
R 1020
801-1871
Polyurethane primer U 2008
PAC 33
Wash primer S 2008
PAC 99
Topcoat
CA 8800
EFFECTIVITY ALL
820 R Alumigrip 4200
Imron 700
182-18
020.10.00 Page: 814 Nov 15/13
MAINTENANCE MANUAL (f)
Replacing rivets
Rivets Figure
Standard
Material-Surface conditioning
CSN 02 2301.3
42 4005
CSN 02 2302.0
42 4204.6 elox anodizing
.1
42 4005.2
.3
424432.1
.5
424208.7 elox anodizing
.7
11 343.1 Zn zineing
CSN 02 2304.0 .1
42 4005.2
.2
42 4415.1 elox anodizing
.3
42 4432.1
.5
42 4208.7 elox anodizing
CSN 02 2311.1
11 343.1
.7
42 3005
.9
17 023.6
CSN 02 2320.0
EFFECTIVITY ALL
42 4204.6 elox anodizing
42 4204.6 elox anodizing
.1
42 4205.2
.2
42 4415.1 elox anodizing
.5
42 4208.7 elox anoodizing
Approximate equivalent DIN 660 DIN 124 NAS 1242 MS 20470 F
DIN 660 (D) DIN 663 NAS 1242 ("h") MS 20470 F
DIN 674 NAS 1242 MS 20470F DIN L 177
DIN 664 NAS 1241 MS 20426 (for repair work only: BAC R15DS) DIN 662 NAS 1241 MS 20426 DIN L 175
020.10.00 Page: 815 Nov 15/13
MAINTENANCE MANUAL
Rivets Figure
Standard
Material-Surface conditioning
CSN 02 2379.13
42 3213.11 tin plating
CSN 02 2379.19
42 3213.11 Cd
CSN 02 2380.11
42 3213.11
DIN 7340
CSN 02 2382.14
12 011.1
DIN 7340 DIN L 97
CSN 02 2039.01
11 300.0 Ni
replacement CSN 02 2387
EFFECTIVITY ALL
Approximate equivalent DIN 7339 DIN L 97
DIN 101 ASA B 18.1-1965 ASA B 18.4-1960
3548A
AMg5 elox anodizing
NAS 1241, MS 20426
3549A
D 18P elox anodizing
NAS 1241, MS 20426
3501A
V 65 elox anodizing
NAS 1242, MS 20470F
1651 S 52
D 18P elox anodizing
MS 27130
020.10.00 Page: 816 Nov 15/13
MAINTENANCE MANUAL
Rivets Figure
Standard LeN 3363
Material-Surface conditioning 42 4204.61 elox anodizing
Approximate equivalent DIN 7337
(g) Replacing screws When replacing screw and pin materials, proceed as follows:
If a drawing part is involved, substitute the material as shown in the conversion table adhering to the minimum tensile strength.
In the case of standard parts, ask the manufacturer to inform you about the material strength, or order the complete standard part, or the respective standard. Replace the part according to the conversion table adhering to the strength.
In the extreme case, perform the Rockwell or Vickers hardness test, and then select the steel material according to the measured value.
(h) Replacing chemical products Gasoline and petroleum spirit - select a product of sufficient purity so as to avoid attacking the basic material of the aircraft Grease - see Maintenance Schedule of high quality used currently for other aviation material in your country. Hoses - place an order with the manufacturer, or ask for specifications and use the home products of the comparable quality. Fabric - replace the tall unit fabric covering with fabric covering of higher quality used in your country for tail units. In all other cases, place an order with the manufacturer.
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SEALANTS AND ADHESIVES 1. Preparation of three-components putty U-30 M (for application with a spatula) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Sealing paste U-30 .…. 100 g Vulcanizing paste No. 9 ..… 5 - 9 g Diphenylgiguanidin 0.1 - 0.5 g (as per MRTU 38-5-6061-65)
C. Tools
Ceramic or Dural dish Stirring paddle Rubber gloves
D. Referenced information E.
-
Procedures (1) Mix individual components in the sequence specified in the column “Materials”. Mix until the homogenous material is obtained. (2) If longer putty life time is required, select the amount of diphenylguanidin specified in the mixing formula, nearer to the lower limit. WARNING:
PUTTY PREPARATION MUST BE CARRIED OUT IN WELL VENTILATED ROOM WITH FORCED AIR CIRCULATION. WHEN PREPARING THE PUTTY AND HANDLING IT, USE RUBBER GLOVES.
2. Preparation of five-components putty U-30 M (for application with a brush) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Sealing paste U-30M ... 100 g Vulcanizing paste No. 9 ..5 - 9 g Acetone .... 30 g Ethylacetate ....200 g Diphenylguanidin 0.1 - 0.5 g Items 1, 2, 5 according MRTU 38-5-6061-65
C. Tools
Ceramic of Dural dish Stirring paddle Rubber gloves
D. Referenced information EFFECTIVITY ALL
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MAINTENANCE MANUAL E.
Procedures (1) Mix the individual components in the sequence specified in the column “Material”. Mix until homogenous material is obtained. (2) If a longer putty life time is required, selected the amount of diphenylguanidin, specified in the mixing formula, nearer the lower limit. WARNING:
PUTTY PREPARATION HAS TO BE CARRIED OUT IN WELL VENTILATED ROOM WITH FORCED AIR CIRCULATION. WHEN PREPARING THE BINDER AND HANDLING IT, USE RUBBER GLOVES.
3. Preparation of five-component putty U-30M (for application with a spatula) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Sealing paste U-30M ... 30 g Vulcanizing paste No. 9 ... 9 g Desmodur RF ... 70 gr Aerosil ... 20 g Diphenylguanidin … 0.3 g Items 1,2,5 according to MRTU 38-5-6061-65
C. Tools
Ceramic or Dural dish Stirring paddle Rubber cloves
D. Referenced information E.
-
Procedures (1) Mix the individual components in the sequence specified in the column “Materials”. Mix until the homogenous material is obtained. (2) If a longer putty life time is required, select the amount of diphenylguanidin, specified in the mixing formula, nearer the lower limit. WARNING:
PUTTY PREPARATION HAS TO BE CARRIED OUT IN WELL VENTILATED ROOM WITH FORCED AIR CIRCULATION. WHEN PREPARING THE BINDER AND HANDLING II, USE RUBBER GLOVES.
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6. Processing of PRC sealing compounds (hermetics) A.
Fixture, Test and Support Equipment
PE or duralaluminium; Wooden or PVC spatula; Stirring device (for amount larger than 0.5 kg); Rubber gloves
B.
Materials
PR 1422 A2 (Ord. No. 82177702) Fuel Tank Sealant; PR 1440 A2 (Ord. No. 82177708) Fuel Tank Sealant; PR 1422 B2 (Ord. No. 82177703) Fuel Tank Sealant; PR 1425 B2 (Ord. No. 82177705) Windshield and Canopy Sealant; PR 1770 C8 (Ord. No. 82177716) Faying Surface Sealant; PR 1435 (Ord. No. 82177721) Quick Repair Fuel Tank Sealant; Diluting agents: Acetone (Ord. No. 82177721); Ethylacetate TPD 101074-58 (Ord. No. 82109021), Toluene (Ord. No. 82105212) Fillers: AEROSIL® 200 - Synthetic Amorphous Silica (Ord. No. 82178301);
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures NOTE:
Hermetic PR with
"A" letter means - with brush "B" letter means - with spatula
Number 2 behing the letter means lifetime of the mixture is 2 hours and the number ½ means lifetime ½ hour at temperature 25°C. Before using the any Sealing Compounds, it is important that relevant safety and technical data sheet(s), have been read and understood. The safety data sheet(s) will advise on all precautions, safety equipment and procedures necessary in the safe use and disposal of the product.
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MAINTENANCE MANUAL (1) Hermetic PR 1422 class A Hermetic PR 1422 class A is two-part sealant putty applied with a brush as airplane integral fuel tank sealant. This sealant was especially developed for use over a temperature range of 55°C to + 135°C and with outstanding resistance to airplane fuels, oils and hydraulic liquids. (a) Mixing ratio of base and accelerator is 10 : 1 w. p. Hermetic is supplied in next three variants: PR 1422 A1/2, PR 1422 A2, PR 1422 A4 Base has biscuit colour, accelerator has black colour. (b) Hermetic application time and cure time values see below: Application time (hours)
Tack-free time (hours)
Max. interval to 35 Shore
1/2
10
48
PR 1422 A2
2
24
72
PR 1422 A4
4
36
100
Hermetic type PR 1422 A1/2
Hardening interval lasts 14 days at temperature 25°C or 3 days at temperature 25°C plus 8 hours at temperature 50°C. Hermetic has an excellent adhesion features; after the 7 samples have been immersed in bath, alluminium peel strength on surface was 3.9 N/mm and stainless steel peel strength was 4.3 N/mm. Hermetic properties are to be tested according to the MIL-S-8802 E. (2) Hermetic PR 1440 Hermetic PR 1440 is two-part polysulfide sealant (putty) designed for fillet sealing of fuel tanks and other airplane fuselage sealing applications. The sealant has the same properties as PR 1422 A sealant. It should be used as a second layer within the hermetization process. (a) Mixing ratio of base and accelerator is 10 : 1 w.p. Hermetic PR 1440 is to be supplied in next variants: PR 1440 A1/2, PR 1440 A2 Base compound has white colour and accelerator has black colour. (b) Hermetic application time and cure time values see below: Hermetic PR 1440 A1/2 PR 1440 A2
Application time (hours)
Tack-free time (hours)
Max. interval
1/2
10
40
2
40
72
to 35 Shore
Hermetic cure time and resistence against the environment is the same as for PR 1422 A hermetic.
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MAINTENANCE MANUAL Hermetic adhesion after 7-day exposition of an airplane liquids is on aluminium 7.9 N/mm, on stainless steel 7.3 N/mm and on titan is 7.7 N/mm. (3) Hermetic PR 1422 class B Hermetic PR 1422 class B is two-part polysulfide sealant (putty) applied for sealing of fillets with outstanding resistance to airplane fuels, oils and hydraulic liquids. The mixture is a highly thixotropic paste, that may be applied with an spatula or an extrusion gun. The mixture needs to be hardened at the room temperature, without volume shrinkage and perfect adhesion on aluminium, titan, steel and other materials. (a) Mixing ratio of the base and the accelerator is 7.5 : 1 w.p. Hermetic is to be supplied in three variants: PR 1422 B1/2, PR 1422 B2, PR 1422 B4 Base has biscuit colour and accelerator has black colour. (b) Hermetic application time and cure time values see below: Application time (hours)
Tack-free time (hours)
Max. interval to 35 Shore
1/2
10
48
PR 1422 B2
2
24
72
PR 1422 B4
4
36
100
Hermetic type PR 1422 B1/2
Hardening interval lasts 14 days at temperature 25°C. The longer hardening interval the better the hermetic properties. Usually the maximal value is attained after 30 to 60 days. PR 1422 class B Hermetic hardness value after the hardening process is 56 Sh. Adhesion of cured hermetic after 7-day immersion in the TT-8-705 fuel or in the solution of salt water + hydrocarbons is very strong. The adhesion value on aluminium surface is 6.4 N/mm, on steel is 7.0 N/mm, on titan is 6.4 N/mm. It has a service (resistence) temperature range from 55 °C to +135 °C. Hermetic properties are to be tested according to the MIL-S-8802 class B standard. The complete hardening time interval is 14 days at temperature 25 °C. Maximal values are (4) Hermetic PR 1425 Hermetic PR 1425 is two-part polysulfide sealant (putty) specially developed for an airplane windshield, canopy and optic devices sealing. The mixed compound is a thixotropic paste, which does not from vertical or overhead surfaces. (a) Mixing ratio of the base and the accelerator is 10 : 1 w.p. Hermetic PR 1425 is to be supplied in next two variants: PR 1425 1/2, PR 1425 2 Both the base and the accelerator have black colour.
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MAINTENANCE MANUAL (b) Hermetic pot-life and hardening time values see below: Hermetic
Application time (hours)
Tack-free time (hours)
Max. interval
1/2
12
24
2
24
48
PR 1425 1/2 PR 1425 2
to 35 Shore
Hermetic ultimate cure hardness value is 53 Shore. Strong adhesion to the basic material: Adhesion value on aluminium surface is 7.0 N/mm, glass 7.0 N/mm, acryl 7.1 N/mm and PVB 6.4 N/mm. It has a service temperature range from 55 °C to +135 °C. The sealant exhibits excellent resistence to water, alcohols, crude oils, synthetic oil, hydraulic liquid and the fuels. (5) Hermetic PR 1770 PR-1770C is a two-part, manganese dioxide cured Permapol P-5 polysulfide compound. This sealant is determined for sealing inside the rivet connections (the Russian equivalent is U30 MES-5 (H) Sealant). Hermetics PR 1770 C8 and PR 1770 C12 should be applied with gun or spatula. (a) Mixing ratio of the base and the accelerator is: PR 1770 C8
10 : 1
w.p. (weight portions)
PR 1770 C12
10 : 1
w.p.
Base has light grey colour, accelerator has black colour. Application time (hours)
Assembly time (hours)
Cure time in faing surface (Days)
PR 1770 C8
8
20
14
PR 1770 C12
12
20
14
Hermetic
Hardening time is 14 days at temperature 25°C. (6) Hermetic PR 1435 PR-1435 is a two-part, dichromate cured polysulfide compound. This material is designed for repair of sealing of fuel tanks and other aircraft fuselage sealing applications. The uncured material is suitable for application by extrusion gun or brush. (a) Mixing ratio of the Part A : Part B: By weight
13.3 : 100
w.p. (weight portions)
Part A has black colour, Part B has white colour. (Mix has Olive Green colour) Hermetic PR 1435
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Application at temperature
Tack-free time (hours)
Cure time To 30 A Durometer (hours)
25°C
0 .............. The control surface is statically underbalanced (heavy on the trailing edge) (7) A general-purpose balancing device (Fig. 604) can be used to check and adjust the mass balance of the control surfaces. However, special attachment fittings are needed to fit the control surfaces (elevator, rudder, aileron) in the balancing device. EFFECTIVITY ALL
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MAINTENANCE MANUAL It is recommended to have the mass balance of the control surfaces checked and adjusted in a special repair shop equipped with special devices.
Fig. 604
GENERAL – PURPOSE BALANCING DEVICED (1) Frame; (2) Adjustable clamps with arms for suspension of control surface; (3) Control surface; (4) Locking of trim tab with self-adhesive tape (on elevator); (5) Special attachment fitting
(8) Check and adjustment of mass balance of elevator. Each half of the elevator must be mass balanced separately so that the center of gravity of the balanced elevator lies within. + 4.3 < σe (% Ce) < + 4.7 which is with Ce = 0.431 m : 18.5 < Xe (mm) < 20.3
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FIG. 605
(9) Check of elevator mass balance by calculation (without balancing device). NOTE:
This method can only be used if there is a Balance Record for the elevator showing its condition before the repair. If such Balance Record (usually S/N 1) is not included in the aircraft documentation, the mass balance of the elevator is to be checked and/or adjusted in compliance with para (2) subpara (b). This method is applicable for small repair (e.g. repair of elevator fabric covering by patches) when additional mass (
GR) and perpendicular distance of its C.G. from the
elevator axis of rotation (XR) can be reliably determined by calculation and/or weighing. Procedure: (a) Before the repair, weight the complete elevator and compare the weight with the value of Ge (bal) (kg) indicated in point 5 of the Balance Record for the elevator before the repair. If the two values are not coincident, check and/or adjust the mass balance of the elevator in compliance with para (2) subpara (b). (b) If the two weights are coincident, read the value of mass balance σe (% Ce) indicated in point 3 of the Balance Record for the elevator before the repair. NOTE:
This value is only applicable if the value indicated in point 4 of the Balance Record is
G1 = 0.
If the value indicated in point 4 of the Balance Record is G1 ≠ 0, then σe = + 4.5 (% Ce) EFFECTIVITY ALL
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(c) Determine the following values: GR (kg) ..... increase + or decrease - of elevator weight ("additional mass") XR (m) .......... perpendicular distance of additional mass C.G. (
GR) from the axis of rotation
(d) Calculate the new weight and the value of mass balance of the repaired elevator using the following formulas: Ge (R) (kg) = Ge (bal) + ∆GR ..... the resultant weight of one elevator half after the repair (without adjustment of mass balance)
G e (bal) . σ e + σ e (R) [% C e (bal)] =
GR . X R .
100
Ce
G e (R)
………the resultant value of mass
balance of one elevator half after the repair, without any change in the mass balance NOTE:
Ce = 0.431 m
If the condition + 4.3 σe(R) < (%e) + 4.7 is met, no change in the mass balance is to be done. A new Balance Record is to be made out (marked with the next ordinal number) which must indicate (in the "Notes") the description of the executed repair and the resulting changes in the weight characteristics of the repaired elevator: GR (kg), XR (m), Ge (R) (kg), and σe (R) (% Ce). This new Balance Record will supersede the original and/or preceding Balance Record - see para (3). If the above stated condition is not met, adjustment of the mass balance (which actually means new mass balancing) is to be done in compliance with para (2) subpara (b) and a new Balance Record made out to supersede the preceding one. (10) Check of mass balance of repaired elevator by means of balancing device. The check of mass balance is to be made. (a) if it is not possible to determine the distribution of additional masses, their centers of gravity, and arms relative to the elevator axis of rotation (b) whenever the trim tab is replaced (c) when a new paint coat is applied on the elevator, or when a major repair of the paint coat is made (d) when a new paint coat is applied on the elevator trim tab
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MAINTENANCE MANUAL (11) Check and/or adjustment of rudder mass balance The rudder must be statically balanced (σr = 0). If the rudder is overbalanced ("heavy on the leading edge"), this will not affect aeroelastic characteristics but it means an unnecessary extra weight. Since the procedure for rudder mass balancing is very simple, it is recommended to check and adjust the mass balance by means of the balancing device after any repair of the rudder, including execution of a new Balance Record (as per para (2) subpara (b), para (3), para (5). (12) Check and/or adjustment of aileron mass balance Each aileron must be statically balanced and/or overbalanced (it means that its center of gravity must be on or forward of the axis of rotation). σa (% Ca) ≤ 0 NOTE:
Dynamic balance of the ailerons is provided for by means of a balancing mass of GB2 = 0.325 kg (lead rollers + duralumin spacing tube) which is, and must always remain in the outboard mass balance bushing.
(13) In consideration of the above condition for aileron mass balancing, the procedure indicated in para (2) subpara (b) is recommended as the simplest method for checking and/or adjusting the aileron mass balance after an aileron repair. A new Balance Record is to be made out after each check/adjustment of mass balance. This procedure must be carried out (a) when there is no Balance Record showing the aileron mass balance before the repair (b) when the aileron trim tab, or the trim tab control is replaced (c) when a new paint coat is applied on the aileron (d) when a new paint coat is applied on the aileron trim tab (e) after any repair resulting in a displacement of the center of gravity behind the axis of rotation (toward the trailing edge). This applies to all ailerons which were hundred-per-cent statically balanced before the repair (i.c.σa = 0% Ca). (The value of σa is shown in point 7 of the aileron Balance Record). (14) Check of aileron mass balance after a repair by calculation This method can only be used if there is a Balance Record showing the aileron condition before the repair. It is applicable if the aileron before the repair was hundred-per-cent statically balanced (σa = 0), if the repair evidently results in a displacement of the center of gravity forward of the axis of rotation, and if the increase in weight mass C.G.
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GR (kg) and the perpendicular distance of additional
XR (m) from the axis of rotation cannot be reliably determined.
020.30.00 Page: 611 Nov 1/11
MAINTENANCE MANUAL
FIG 606 Then Ga (R) (kg) = Ga + GR ..... resultant weight of the aileron after the repair
σ a (R) (% C a ) =
100 x C a (m)
G R (kg) x X R (m) ……... resultant value of aileron mass G a (R) (m)
balance after the repair (σa (R) < 0) where Ca = 0.257 m Since in this case σa (R) (% Ca) is always less than zero (σa (R) (% Ca) < 0 no adjustment of mass balance is made. It is, however, necessary to make out a Balance Record indicating (in the "Notes") the description of the repair and the resulting changes in the weight characteristics of the repaired aileron: GR (kg), XR (m), Ga (R) (kg), σa (R) (% Ca) If the aileron of aircraft is statically overbalanced and if it is possible to determine reliably the increase in weight
GR (kg) and the perpendicular distance of additional mass C.G. XR (m)
from the axis of rotation (both forward of the axis of rotation - , and aft of the axis of rotation + , proceed as follows: (a) Before the repair, weigh the complete aileron and compare its weight with the value of Ga (kg) indicated in point 6 of the Balance Record of the aileron before the repair. If the two values are not coincident, check and/or adjust the mass balance of the aileron in compliance with Instruction for performing mass balance (para (2) subpara (a) mentioned in subsection 020.30.00.
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MAINTENANCE MANUAL (b) If the two weights are the same, read the value of static mass balance σa (% Ca) indicated in point 7 of the Balance Record. (c) Determine the values of
GR (kg) and XR (m) by weighing, measurement or calculation.
(d) Calculate new weight characteristics of the repaired aileron. using the following formulas: Ga (R) (kg) = Ga + ∆GR .......... resultant weight of the aileron after the repair (without adjustment of mass balance);
σ a (R) (% C a ) =
G a (kg) x σ a (% C a ) + 389 . 105 x ∆ G R (kg) x X R (m) ...resultant G a (R) (kg)
value of static mass balance of the aileron after the repair, without any change in the mass balance. (e) If the condition σa (R) (% Ca) ≤ 0 is met, no adjustment of the mass balance is required. It is, however, necessary to make a new Balance Record (marked with the next ordinal number) which must indicate the description of the repair and the resulting changes in the weight characteristics of the repaired aileron: GR (kg), XR (m), Ga (R) (kg) and σa (R) (% Ca) This new Balance Record will supersede the original and/or preceding Balance Record (see para (3)). (f)
If the above stated condition is not met, i.e. σa (R) (% Ca) > 0 an adjustment of mass balance (which actually means new mass balancing) is to be done in compliance with para (2)-b, subsection 020.50.00, and a new Balance Record made out to supersede the preceding one, see para (3).
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SPARE PARTS STORAGE 1. Spare parts storage A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Spare parts of the sets 1:1 and special set specified in the Technical conditions for the aircraft shall be stored under the following conditions: (a) Parts, instruments and aggregates must be stored in their original package. (b) Rubber and rubber parts must be stored separately from electric instruments, blocks and aggregates. (c) Storage rooms must have chemically inert atmosphere and max. relative humidity up to 70 %. Storing equipment and storage must conform to storage system. (d) Board and navigation instruments, blocks and similar aggregates must be stored in air-conditioned storehouse in the temperature range from 10°C up to 30°C with daily temperature deviation max. 4°C and relative humidit y up to 70 %. (e) When the above specified condition is exceeded, it is necessary to check the preservation of parts, instruments and aggregates and renew it, if needed.
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INSTRUCTION ADJUSTMENT / TEST 1. Direction for Mass Balancing of Control Surfaces A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) The control surfaces (elevator, rudder, and ailerons) must be mass balanced to a prescribed value in accordance with the airworthiness requirements, aeroelastic calculation and tests. The value of mass balance of a control surfaces (σ) is defined by the following formula:
σ (%C) =
X T (m) X 100 C (m)
where
XT (m) .......... perpendicular distance of C.G. of the control surface from its axis of rotation ( + behind the axis of rotation) C (m) ........... geometric mean chord of the control surface behind its axis of rotation (perpendicular to the axis of rotation)
FIG. 501
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MAINTENANCE MANUAL σ < 0 .......... the control surface is statically overbalanced σ = 0 .......... the control surface is statically balanced σ > 0 .......... the control surface is statically underbalanced (2) Mass balancing must be made after the control surface has been completely finished (including installation of electrical equipment, controls, etc.) and painted (including colored sings and markings). (3) Mass balancing of the control surfaces must be carried out in a balancing device which enables deflecting the control surfaces with minimum friction in the attachment fittings. The control surfaces are to be suspended at two points, and the bearings must be clean and greased. (4) The Balance Record provides evidence of mass balancing of each particular control surface, as well as of its history on a particular aircraft. The Balance Record is developed during mass balancing of a control surface and its installation on an aircraft. (a) A separate Balance Record is made out in two copies for each particular control surface in a language version according to customers option. One copy is archived in the Manufacturers Certificates Department, the other one is delivered to the aircraft operator, as a part of the technical documentation for the aircraft. NOTE:
Control surfaces manufactured as spare parts are stored unpainted and unbalanced. Before being dispatched to a particular customer (when they have been painted with the top coat including colored signs and markings) they are mass balanced in accordance with this Direction, and both copies of the Balance Record are made out. In this case, only Part A, and the name of the customer in Part B of the Balance Record is filled in. One copy is passed to the file of the Manufacturers Certificates Dept., while the other one is delivered to the customer together with the control surface. Part C, and the remaining sections of Part B will be filled in by the Quality Control of the operator when the control surface is installed on a particular aircraft.
(b) Part A of the Balance Record is filled in by the department having carried out the mass balancing, and confirmed by the Quality Control Inspector of that department. Parts B and C are filled in by the Quality Control Inspector of final assembly when a control surface is installed on a particular aircraft. The Quality Control Inspector also arranges for and is responsible for development of Balance Records in the appropriate language version for the customer.
Part D of the Balance Record (information concerning cancellation of its validity) is filled in only by the aircraft operator when a new Balance Record (marked with the next higher ordinal number) is developed after the mass balance of a control surface has been adjusted due to a repair, or due to replacement of the original control surface by another one.
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MAINTENANCE MANUAL NOTE:
Therefore, part D of the Balance Records (in Czech) archived in the Manufacturers Certificates Department is always blank.
(5) The operator is obliged to archive the Balance Records for all the control surfaces of this aircraft in chronological order showing any intervention in the mass balance (after a repair of a control surface, a repair of its paint coat, after replacement of any trim tab or after replacement of a control surface with another one). This means that both the "valid" and the "cancelled" Records must be archived. Chronology is indicated by ordinal numbers of Balance Records for each particular control surface on a particular aircraft. The Balance Records delivered by the manufacturer together with each aircraft are marked with serial number 1. When a control surface is repaired, or its paint coat is repaired, or any trim tab is replaced, the authorized department must carry out a repeated mass balancing of the control surface, and make out a new Balance Record (Part A). When this control surface is reinstalled on the original aircraft (or installed on another aircraft), the operator (or the Quality Control Inspector of final assembly) will fill in Parts B and C of this Balance Record, and mark the Record with the next higher ordinal number compared to that of the preceding Balance Record (for the control surface installed on that aircraft before). If a new (spare) control surface is installed on the aircraft, the operator (or the Quality Control Inspector of final assembly) will fill in Parts B and C of the Balance Record delivered with the replacement control surface. Part A of the Record is already filled in by the aircraft manufacturer. The Balance Record is marked with the next higher number following that of the preceding Record (for the original control surface). Validity of the preceding Balance Record must be cancelled by the operator who will fill in Part D showing the date, the reason for cancellation (repair or replacement of a control surface), and the ordinal number of the Balance Record superseding it. NOTE:
a)
The operator is responsible for obtaining new forms of the Balance Records by copying the samples provided in this Direction.
b)
If an aircraft (e.g. a prototype intended for testing) is operated by Aircraft Industries, an authorized department (usually Aircraft Prototype Production Dept.) is considered as the aircraft operator.
(6) Any repeated paint coating of the control surfaces is forbidden. If it is necessary, for any reason, to change the painting, the original paint layer must be removed before the new paint coat is applied. (7) Should a condition occur when using this Direction which cannot be resolved while observing the instructions herein, it is necessary to discuss any deviation with Aircraft Industries Stress Analysis Department. (8) During check flights and before the aircraft is put into service, all the requirements of this Direction must be met. EFFECTIVITY ALL
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MAINTENANCE MANUAL (9) Mass balancing of elevator of the L 410 UVP (Dwg. No. B 033 500 L, P), L 410 UVP-E (Dwg. No. B 533 200 L, P), and L-420 aircraft (Dwg. No. B 533 270 L, P) (10) All the principles given in para (1) to (8) of this Direction must be observed. (11) Each half of the elevator must be mass balanced so that the value of the mass balance ranges between 4.38 % and 4.7 % GMC (Ce) behind the axis of rotation (toward the trailing edge): 4.3 < σe (% Ce) < 4.7 (12) Each half of the elevator is mass balanced separately. (13) Conditions for mass balancing: (a) The elevator trim tab must be locked in the neutral position by means of the adhesive tape. (b) Balancing weight (GB) is to be suspended in the hole of the tubular rivet fastening the outboard mass balance.
CAUTION:
THE WEIGHT OF GB INCLUDES THE WEIGHT OF THE DISH FOR LEAD SHOT.
(14) Geometric characteristics (a) Geometric mean chord of the elevator behind its axis of rotation Ce = 0.431 m, measured perpendicular to the axis of rotation. (b) Required position of elevator center of gravity (when underbalanced to σe = + 4.5 % Ge): XT (e) =
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4.5 x Ce = 0.0194 m 100
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MAINTENANCE MANUAL (15) Basic procedure for mass balancing (a) Weigh each half of the elevator separately and determine Ge (b) Balance the elevator by means of the balancing device to σe = 0 %, using balancing weight GB see para (13) subpara (b) NOTE:
•
For exact balancing use lead shot as balancing weight.
•
Balancing to the value σe = 0 means setting the elevator in the balancing device to horizontal balanced position (using balancing weight GB) in which the elevator stays without action of external forces.
(c) Calculate the value of mass balance σe by means of formula No. 3 given in the Balance Record No. 1 and No. 2 (d) If the value of σe is within 4.3 % and 4.7 % Ce, no change in mass balance is required, and a value of
G1 = 0 kg is to be entered in the Balance Record (item No. 5).
(e) Should the center of gravity position be outside the permissible range, it is necessary to change the weight of the inboard mass balance (B 033 562 N) by the value of
G1 (calculated by
means of formula No. 5 given in the Balance Record No. 1, 2) in order to mass balance the elevator σe = 4.5 % Ce (behind the axis of rotation) •
If the value of
G1 is negative (corresponding to σe < 4.5 % Ce), the weight of the inboard
mass balance is to be reduced by this value by drilling out (or milling out) the appropriate amount of material as shown in the Figure on page 1222 (table No. 1). •
If the value of
G1 is positive (corresponding to σe > 4.5 % Ce) the weight of the inboard
mass balance is to be increased by this value by drilling holes as shown in table No. 3 and then filling the holes with lead rollers of 15.5 mm in diameter and not more than 20 mm in length in order to receive the prescribed value. Clinch the rollers (B 270 129 N) when inserted in the holes to secure in them in position. (16) Mass balancing of rudder of the L 410 UVP (DWG. No. B 031 500 N), L 410 UVP-E (DWG. No. B 531 200 N) and L-420 (Dwg. No. B 531 239 N) aircraft (a) All the principles given in para (1) to (8) of this Direction must be observed. NOTE:
Triangular fastening members of middle hinges do not belong to the rudder and therefore, the rudder must be weighed and balanced without these members.
(b) The rudder must be mass balanced to σr = 0 %, it means that its center of gravity is located on the axis of rotation. (c) The rudder trim tab must be set to the neutral position.
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MAINTENANCE MANUAL (d) If the rudder is heavy on the trailing edge, it is to be balanced by increasing
GMU (i.e. upper
additional mass) in the upper mass balance. The value of the additional mass is to be determined according to the upper balance weight (GBU) suspended in the auxiliary hole in rib No. 17 to balance the rudder to σr = 0 %. Note of para (13) subpara (b) is to be kept in mind.
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MAINTENANCE MANUAL (e) If the rudder is heavy on the leading edge, it is to be balanced by drilling off the excess weight GML from the lower mass balance (GML). The value of the weight to be drilled off is determined according to the lower balance weight (GBL) suspended in the auxiliary hole rib. No. 11. Note on para (13) subpara (b) is to be kept in mind.
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MAINTENANCE MANUAL (17) Geometric mean chord of the rudder behind its axis of rotation, Cr = 0.590 m, measured perpendicular to the axis of rotation. (18) Weight the rudder, Cr (o) (kg) Fit the rudder in the balancing device and determine whether it is heavy on the trailing edge (σr > 0 %) statically balanced (σr = 0 %) heavy on the leading edge (σr < 0 %). If the rudder is not statically balanced, proceed as follows: (a) Rudder is heavy on the trailing edge •
Determine the value of the upper balance weight (GBU) required to set the rudder into equilibrium (Cr = 0 %) in accordance with para 16 subpara (d)
•
Read the necessary upper additional mass GMU (kg) for the GBU (kg) in Chart No. D.1. If the GBU exceeds 0.5 kg, further procedure must be consulted with Aircraft Industries Structural Design Dept.
•
Remove the upper mass balance and increase its weight by the value of GBU found in the Chart, by screwing 2 mm thick lead plates (weights) (Dwg. No. B 031 551 N) in predetermined locations (M5 threaded holes). First fit the weights (6 pcs at the most) in the bottom location A, and then successively to the locations B, C and D (see the Chart D.1). The number of weights in each location must not exceed 6 pcs. Secure the screws according to the drawing
•
Reinstall the upper mass balance
(b) Rudder is heavy on the leading edge •
Determine the value of the lower balance weight (GBL) required to set the rudder into equilibrium (σr = 0 % in accordance with para (16) subpara (d)
•
In Chart No. D.2 read the depth H (mm) of four holes to be drilled in the lower mass balance, according to the value of GBL (kg) and the diameter of drill selected (d = 20, 23.5, 25 mm)
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MAINTENANCE MANUAL Lower mass balance:
Remove the lower mass balance and drill four holes of a selected diameter to the depth found in the Chart at Premark locations. NOTE:
If H max exceeds 25 mm, further procedure must be consulted with Aircraft Industries, a.s. Structural Design Dept.
•
Determine the value of
GML (kg) to be removed from the RH vertical scale in the Chart
No. D.2. NOTE:
For all drill diameters, this value is to be read from the curve for d = 23.5 mm.
•
Reinstall the lower mass balance
•
Check for proper mass balancing and fill in the Balance Record.
(19) Mass balancing of aileron of the L 410 UVP (Dwg. No. B 025 601 L, P), L 410 UVP-E (Dwg. No. B 025 601 L, P), and L-420 aircraft (Dwg. No. B 524 910 L, B 025 601 P). All the principles given in para (1) to (8) this Direction must be complied with. (a) Each aileron is provided with
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•
inboard mass balance (between ribs No. 21b and 22)
•
outboard mass balance (between ribs No. 30b and 31a).
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(b) Static mass balance is characterized by the value of σa indicating the aileron C.G. position XT (a) in per cent of geometric mean chord (Ca) of the aileron area behind the axis of rotation: σa (% Ca) =
XT ( a ) x 100 a
where
Ca = 0.257 m ..... geometric mean chord of the aileron area behind its axis of rotation XT (a) (m) ............ position of aileron center of gravity with regard to its axis of rotation
(c) The trim tab on the left aileron must be set to neutral position. (d) Requirements for aileron mass balance •
Each aileron must be mass balanced so as to ensure dynamic overbalance for the 1st antisymmetrical wing bending mode of vibration, for a value of - 2 (% Ca) while it must be statically balanced (σa = 0 % Ca) or overbalanced (inc. heavy on the leading edge: σa < 0 % Ca).
•
Dynamic overbalance is provided by means of "basic" balancing mass of GB2 = 0.325 kg (lead rolls + duralumin spacing tube) which is always put in the outboard mass balance bushing).
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MAINTENANCE MANUAL •
The required static mass balance is to be obtained by adding balancing mass (lead rollers) first in the inboard mass balance bushing (GB1 (kg)) and after this bushing has been filled, adding balancing mass
GB2 (kg) in the outboard mass balance bushing (in which the
balancing mass of GB2 = 0.325 kg had already been put). (e) Basic procedure for mass balancing •
Put the "basic" balancing mass of GB2 = 0.325 kg (lead rollers + duralumin spacing table) in the outboard mass balance bushing of the complete aileron, and screw in the plug of the bushing. The inboard mass balance bushing is to remain empty, but its plug is to be plugged in.
•
Weigh such completed aileron and enter the weight Ga (0) (kg) in the Balance Records No. 4 and No. 5.
•
Suspend the aileron in the balancing device and determine whether it is •
heavy on the trailing edge
•
statically balanced
•
heavy on the leading edge
Proceed according to the corresponding procedure as follows: (f)
Aileron is heavy on the trailing edge. Statically balance the aileron to the axis of rotation, i.c. σa = 0 % Ca. First add lead rollers to the inboard mass balance as follows: •
Suspend a dish compensating for the weight of the plug and the lock screw in the inboard mass balance bushing
•
Add balance weights to the dish to determine the balancing mass required to set the aileron into equilibrium
•
If this balancing mass (lead rollers) can be put completely in the inboard mass balance bushing, no other balancing mass is required for mass balancing. The following values are to be entered in the Balance Records No. 4 and No. 5 : GB1 (kg)
GB2 = 0 kg,
GM = 0 kg, Ga (kg) = Ga (o) + GB1, and σa = (% Ca) If the required balancing mass cannot be put completely in the inboard mass balance bushing, proceed as follows: •
Put as much balancing mass GB1 (kg) as possible in the inboard mass balance bushing.
•
Fix the lead rollers by means of a rubber insert, screw in the plug and lock it.
•
The remaining balancing mass required to balance the aileron is outboard mass balance. Proceed in the same way as indicated above for the inboard mass balance.
•
The required balancing mass,
GB2 (kg), is added to the "basic" balancing mass of
GB2 = 0.325 kg providing for dynamic overbalance to – 2 % Ca. EFFECTIVITY ALL
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MAINTENANCE MANUAL •
Fix the balancing mass in the center mass balance bushing screw in the plug and lock it.
•
Enter the following values in the Balance Records No. 4 and 5: GB1 (kg),
•
GB2 (kg), GM = 0 (kg), Ga (kg) = Ga (O) + GB1 +
GB2, σa = 0 (% Ca)
Check for static balance of the aileron in the balancing device:
(g) Aileron is heavy on the leading edge •
The aileron center of gravity is forward of its axis of rotation (XT < 0 m) which means that the aileron is statically overbalanced (σa < % Ca) and therefore no balancing mass is to be added.
•
Determine the value of static overbalance σa (% Ca) as follows:
•
Suspend the aileron in the balancing device.
•
Insert a pin in the middle attachment fitting (on rib. No. 24), attach a string to the pin, route the string over the trailing edge, and suspend a dish on its end.
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MAINTENANCE MANUAL By means of weights put on the dish, determine the "additional" mass GM (kg) required for putting the aileron into balanced state. Enter the value of GM in the Balance Records No. 4 and 5 •
Calculate the value of static overbalance σa using the following formula: σa (% Ca) = -
•
100 x XM x GM G (kg) = - 106,81 x M C a x Ga Ga (kg)
Enter the following values in the Balance Record. GB1 = 0 kg,
GB2 = 0 kg, GM > 0 kg, Ga (kg) = Ga (0), σa < 0 (% Ca)
(20) Enclosures (a) Chart of determine the necessary upper additional mass
Chart No. D.1
(b) Chart of determine the excess of lower mass balance
Chart No. D.2
(c) Adjustment of elevator inboard mass balance
Table No. 1
(d) Balance Records for elevator
Balance Record No. 1, 2
(e) Balance Record for rudder
Bal. Rec. No. 3
(f)
Bal. Rec. No. 4, 5
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Balance Records for LH aileron
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Chart No. D.1 L 410 UVP, L 410 UVP-E, and L-420 rudder. This chart is used to determine the necessary "upper additional mass" GMU (kg) and it applies to the L 410 UVP aircraft from the 4th series. For the L 410 UVP aircraft up to the 3rd series, determine GMU directly by adding balancing weights in the upper mass balance locations.
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Chart No. D.2 L 410 UVP, L 410 UVP-E, and L-420 rudder. This chart is used to determine the "excess of lower mass balance"
GML (kg) and it applies to the
L 410 UVP aircrafts from the 4th series. For the L 410 UVP aircrafts up to the 3rd series, determine GML by adding balancing weights behind the axis of rotation, at the distance equal to the distance of the holes drilled in the lower mass balance in front of the axis of rotation.
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Table No. 1 Adjustment of elevator inboard mass balance (applies to L 410 UVP, L 410 UVP-E, and L-420 aircrafts) 1
Inboard mass balance before the adjustment
2
Adjustment of mass balance if the weight is to be reduced.
One hole of 15.5 mm in dia. and 20 mm in length represents a 0.031 kg reduction in weight. NOTE: No more than 10 holes can be drilled. 3
Adjustment of mass balance if the weight is to be increased
Fill the holes of 15.5 mm in dia. with 15.5 mm dia. lead rollers (B 270 129 N). Clinch the roller in the hole to secure it in position. The weight of a 20 mm long roller is 0.045 kg. Hence the total increase in weight with be 0.014 kg per hole. No more than 10 rollers can be used.
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MAINTENANCE MANUAL 2. Instruction for alternative Mass Balancing of the Aileron suspended on the wing (in OPERATING CONDITION) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) General (a) Mass balancing on prescribed value must be accomplished after the ailerons suspended on the wing have been assembled completely (including installation of electrical equipment, controls, etc.) and painted (including coloured signs and markings). (b) During the mass balancing of the aileron suspended on the wing the aircraft must be located in closed hangar and positioned in horizontal position (levelled) on hydraulic lifting jacks. (c) Mass balancing of the aileron should be carried on the wing which enables deflecting the aileron with minimum friction in hinges. The aileron (disconnected off the control rod) must be therefore suspended on two hinges (onto wing ribs No. 21K and No. 27K). The suspension bearings must be at mass balancing free of dust collectors, cleaned and greased. End suspension of the aileron on the rib No. 31a must be removed. Aileron tie rod must be inserted into the wing as much as possible and tilted as much as possible towards the side of aerodynamic cover to not hamper to free deflection of the aileron. Fix the tie rod in this position by some kind of soft material (e.g. rag, foam rubber). (d) The aileron suspended on the wing can be considered as statically balanced, if the aileron end rib is in side alignment with the end rib No. 31a on the wing. (2) Balance Record The Balance Record serves as evidence of mass balancing of each particular aileron, as well as of its history on a particular aircraft. The Balance Record is developed during mass balancing of the aileron and its installation on the aircraft. (a) Part A of the Balance Record is filled in by the person who carried out mass balancing and then confirmed by the Quality Control Inspector. Parts B and C should be filled in by the Quality Control Inspector when the aileron has been installed on a particular aircraft. Part D of the Balance Record (information concerning its validity) should be filled in only after the new Balance Record (marked with the next higher ordinal number) is elaborated
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MAINTENANCE MANUAL after new mass balance of the aileron has been performed (because of an aileron repair, repair of the finishing coat, after replacement of the trim tab, after replacement of the aileron with another one etc.) (3) The operator of the particular aircraft is obliged to archive the Balance Records for all the ailerons being ever installed on this aircraft in chronological order, showing every intervention in the mass balance (see item 2-a). This means that both the “valid” and the “cancelled” Records should be archived. The chronology is indicated by the ordinal number of Balance Records for each particular aileron on the particular aircraft. (The Balance Records delivered by the manufacturer together with each new aircraft are marked with ordinal No. 1). After any intervention in the mass balance (see item 2-a) mass balancing of the aileron must be accomplished again and then the new Balance Record should be elaborated (Part A).
When the aileron is installed back on the original aircraft (or on another aircraft), the parts B and C of the Balance Record should be filled in. The Record must be marked with the next higher ordinal number compared to the ordinal number of the Balance Record of the aileron, which has been installed on that aircraft before it. In case that the new (spare) aileron is suspended on the aircraft, fill in Parts B and C of the Balance Record delivered with the substituted aileron. Part A of the Record should be filled in by the new (spare) aileron supplier. The Balance Record is marked with the next higher ordinal number compared to the Balance Record of the aileron, which has been suspended on that aircraft before it. The validity of the precedent Balance Record should be cancelled (in Part D of the Balance Record), showing the date, the reason for cancellation (see item 2-a), and the ordinal number of the Balance Record replacing it. NOTE:
Balance Record forms are available in Appendixes of this Instruction, see Balance Record forms No. 4 and No. 5 enclosed.
(4) Any repeated finishing paint of the aileron is forbidden. If it is necessary for any reason to change the original painting, the original paint layer must be removed before the new finishing paint is applied. (5) Should during usage of this Instruction the condition occur which cannot be re-solved while observing the instruction herein, it is necessary to consult any deviation with the manufacturer AI, a.s. Kunovice. (6) During the flights and before the putting the aircraft into the service, all the requirements of this Instruction must be met.
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MAINTENANCE MANUAL (7) Below described mass balancing procedure is applicable to the ailerons of following aircraft models: L410UVP-E, -E9, -E20 - Dwg. No. B 025 601 L, R (8) All conditions given in section No. (1) of this Instruction must be complied with. (9) Each aileron is provided with two different balancing positions: •
inboard mass balance / between the ribs 21b - 22 /
•
outboard mass balance / between the ribs 30b - 31a /
(10) “Static” mass balance is characterised by the value of σA , indicating the aileron centre of gravity position [XT(A)] in per cent of geometric mean chord (CA ) of the aileron behind the axis of rotation:
σ A [%C A ] =
X T ( A) CA
× 100
where: CA = 0,257 m ……the aileron geometric mean chord percentage behind the axis of rotation XT (A) [m] ………..aileron centre of gravity position regarding to the axis of rotation
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MAINTENANCE MANUAL (11) The trim tab on the left aileron must be set in the neutral position (12) Requirements for aileron mass balance (a) Each aileron must be mass balanced so that to ensure dynamic overbalance 1.AO K (i.e. st
the 1 anti-symmetrical wing bending mode of vibration), over the value of -2
[%CA]
while it must be statically balanced “to the axis” / σA = 0 % CA / or “overbalanced” ( i.e. heavy on the leading edge: / σA < 0 % CA / (b) Dynamic overbalance is provided by means of “basic” balancing mass of GB2 = 0.325.kg (lead rollers + duralumin spacing tube) which is always put into the outboard mass balance bushing). (c) Realize the required static mass balance by means of adding balancing mass (lead rollers) at first into the inboard mass balance bushing (GB1 /kg/) and after that when bushing has been filled, by adding balancing mass ∆GB2 /kg/ in the outboard mass balance bushing (in which the balancing mass of GB2 = 0.325 kg had been already put). (13) Basic procedure for mass balancing (A) Put the “basic” balancing mass of GB2 = 0.325 kg (lead rollers + duralumin spacing tube) in the outboard mass balance bushing of the complete aileron, and screw in the plug of the bushing. Leave the inboard mass balance bushing empty, but screw in its plug. (B) Weigh such completely assembled aileron and enter the weigh GA (0) /kg/ in the Balance Records No. 4 and No. 5. (C) Suspend the aileron on the wings (on hinges on the ribs No. 21K and No. 27K) according to the side alignment of the aileron’s end rib with end rib No. 31a on the wing and define balance condition: •
“heavy on the trailing edge”
•
“statically balanced"
•
“heavy on the leading edge”
(C1) Aileron is “heavy on the trailing edge” Statically balance the aileron to the axis of rotation, i.e. σA = 0% CA. a)
At first realize balancing by means of inside balancing as follows: •
Suspend a dish compensating with its weight the weight of the plug and locking screw in the inboard mass balance bushing.
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MAINTENANCE MANUAL •
By means of balance weights put into the dish determine the balancing mass necessary for balancing of the aileron into balance position.
•
If this balancing mass (lead rollers) can be put completely in the inboard mass balance bushing, no other balancing mass is required for mass balancing. The following values must be entered in the Balance Records No. 4 and/or No. 5: GB1 (kg), ∆GB2 = 0 kg, GM = 0 kg, GA [kg] = GA (0) + GB (1), and σA = (%CA).
(b)
If the required balancing mass can not be put completely into the inboard mass balance bushing, proceed as follows: •
Put as much balancing mass GB1 (kg) as possible into the inboard mass balance bushing.
•
Fix the lead rollers by means of a rubber insert, screw in the plug and lock it.
•
Realize the remaining balancing mass ”to the axis” on outboard mass balance. Proceed in the same way as indicated above for the inboard mass balance. The required balancing mass, ∆GB2 (kg), is added to the “basic” outboard balancing mass of GB2 = 0.325 kg providing dynamic overbalance to -2% CA .
•
Fix the balancing mass in the centre mass balance bushing, screw in the plug and lock it.
•
The following values must be entered in the Balance Records No. 4 and/or No. 5: GB1 (kg), ∆GB2 = 0 kg, GM = 0 kg, GA [kg] = GA (0) + GB (1) , and σA = (%CA). Check the static balance “to the axis” of rotation at re-suspension of the aileron on the wing (in hinges on ribs No. 21K and 27K).
(C2) Aileron is heavy on “the leading edge” The aileron centre of gravity is forward of its axis of rotation / XT < 0 m/, that means the aileron is statically overbalanced / σA < 0 % CK / and therefore no balancing mass must be added. Determine the value of static overbalance σA (% CA) as follows: (a) Suspend the aileron on the wing (onto suspensions on ribs No. 21A and 27A). (b) Attach the hook connected to string directly to the skin edge in the suspension cut-out, lead the string along the trailing edge, then suspend e.g. dish on its end.
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(c) By means of the weight put on the dish determine the “additional” mass GM [kg] needed to set the LH aileron (heavy on the leading edge) into equilibrium state. Record the value of GM in the Balance Records No. 4 and/or No. 5. (d) Calculate the value of static overbalance σA by means of the following formula:
σ A [%C A ] = −
100 × X M × G M G (kg ) = −106,81 × M CA × GA G A (kg )
(e) Enter the following values in the Balance Record: GB1 = 0 kg, ∆GB2 = 0 kg, GM > 0 kg, GA (kg) = GA(0), σA < 0 (% CA)
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CHAPTER
AIR CONDITIONING
MAINTENANCE MANUAL
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CHAPTER 21 AIR CONDITIONING RECORD OF REVISIONS Rev. No.
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021- List of Effective Pages
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L410UVP-E/196d
May 30/14
L410UVP-E/208d
Dec 10/14
021-RECORD OF REVISIONS Page: 1 Dec 10/14
MAINTENANCE MANUAL
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021-RECORD OF REVISIONS Page: 2 Nov 1/11
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021-RECORD OF REVISIONS Page: 3 Nov 1/11
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021-RECORD OF REVISIONS Page: 4 Nov 1/11
MAINTENANCE MANUAL
CHAPTER 21 AIR CONDITIONING RECORD OF TEMPORARY REVISIONS Rev. No.
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021-RECORD OF TEM. REVISIONS Page: 1 Nov 1/11
MAINTENANCE MANUAL
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021-RECORD OF TEM. REVISIONS Page: 2 Nov 1/11
MAINTENANCE MANUAL CHAPTER 21 AIR CONDITIONING CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
GENERAL Description and Operation Purpose Maintenance Practices General
021.00.00
1 1 1 201 201
ALL
DISTRIBUTION Description and Operation General List of components Servicing Check of the air intake of air-conditioning system Inspection of the heating control flaps and their controls in the pilot's cockpit and passenger cabin Inspection of the compensators in the air distribution ducting between the frames No. 3-4, 8-9 and 11-12 Inspection of the compensators in the air distribution ducting between the frames No. 11-12 Inspection of the compensators in the air distribution ducting between the frames No. 3-4 and 8-9
021.20.00
1 1 1 4 301 301 301
ALL
B 580 230 N AIR INTAKE WITH FLAP Description and Operation Purpose
021.20.01
1 1 1
ALL
B 580 693 N ANNULAR EJECTOR Description and Operation Purpose
021.20.02
1 1 1
ALL
B 580 697 N SILENCER Description and Operation Purpose
021.20.03
1 1 1
ALL
B 580 206 N DISTRIBUTION PIECE Description and Operation Purpose
021.20.04
1 1 1
ALL
B 085 015 N AIR SHOWER Description and Operation Purpose Servicing Checking functions and completeness of air showers Removal / Installation Removal and installation of the B 085 015 N air shower
021.20.05
1 1 1 301 301
ALL
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304 305
401 401
021-CONTENTS Page: 1 May 30/14
MAINTENANCE MANUAL Subject
Page
Effectivity
HEATING 021.40.00 Description and Operation General List of components Fault Isolation Servicing Check of the tightness of non-return valves and shut-off flap in the pilot's cabin, passenger's cabin between the frames No. 2-3, wing, engine nacelles Check of the function of the heating control flap on the left control panel Removal / Installation Removal of the heating system piping in the fuselage Installation of the heating system piping in the fuselage Removal of the heating piping in the wing Installation of the heating system piping in the wing Removal of the heating piping in the engine nacelle Installation of the heating piping in the engine nacelle
1 1 1 2 101 301 301
ALL
L 410.8510-08 NON-RETURN VALVE Description and Operation Purpose Removal / Installation Removal of the L 410.8510-08 non-return valve Installation of the L 410.8510-08 non-return valve
021.40.01
1 1 1 401 401 401
ALL
B 085 180 N SHUT-OFF FLAP Description and Operation Purpose Removal / Installation Removal in the B 085 180 N shut-off flap Installation of the B 085 180 N shut-off flap
021.40.02
1 1 1 401 401 401
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COOLING (if installed) Description and Operation General List of components Operation Servicing Inspection of the tension and/or alignment of the compressor drive belt Inspection of the brush and bearing of the compressor drive motor Check of the R-134A compressor assembly for leakage of oil refrigerant Inspection of the evaporator module assembly (evaporator coil, condensate and tubing, cool air ducting) Check of the air-conditioning system function
021.50.00
1 1 1 1 2 301 301
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304 401 401 402 403 404 404 406
304 310 311
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021-CONTENTS Page: 2 Dec 10/14
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TEMPERATURE CONTROL Description and Operation General List of components Operation
021.60.00
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INDICATION Description and Operation General List of components Operation
021.80.00
1 1 1 1 1
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LUN 5610.01-8 DUAL AIR TEMPERATURE INDICATOR Description and Operation Purpose Technical data Operation
021.80.01
1 1 1 1 2
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LUN 5616-8 HEATING AIR TEMPERATURE TRANSMITTER Description and Operation Purpose Technical data Operation
021.80.02
1 1 1 1 2
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LUN 5615-8 CABIN AIR TEMPERATURE TRANSMITTER Description and Operation Purpose Technical data Operation
021.80.03
1 1 1 1 1
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GENERAL DESCRIPTION AND OPERATION 1. Purpose The air-conditioning system is intended for: •
the heating and cooling (if installed) of the pilot and the passenger cabin within the limits satisfying physiological demand for heat
•
the heating of the storage battery bay
•
sufficient ventilation of the pilot and the passenger cabin during flight and landing
•
the cooling of radio navigation equipment
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GENERAL MAINTENANCE PRACTICES 1. General A.
B.
The components removed from the aircraft for laboratory test must be inspected for: •
visible mechanical damage of the body
•
corrosion of plug-and socket connectors, terminals, pushbuttons
•
deformation of plug-and-socket connectors pins
•
deposits of dirt
•
evidence of fluid leaks
When removing a unit (a component) from the aircraft (for laboratory test or replacement), its place of installation, connector or pipe mating parts must be inspected for: •
mechanical damage (cracks) of the place of installation
•
wear of the attachment holes
•
corrosion and deformation of plug-and-socket connector pins
•
dents
•
ruptures
•
deformation of pipe connecting parts
•
damage of connector and pipe union nut threads
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DISTRIBUTION DESCRIPTION AND OPERATION 1. General Hot air for heating purposes is brought by means of a piping to the annular ejector where it is mixed with cold air brought from the outside by means of an air intake. The air intake is provided with a flap controlling the cold air flow rate. The heating or ventilating air is then conveyed by hoses and pipes from the annular ejector via the silencer to the air ducts situated along both sides of the passenger cabin. From the ducts, the air gets into the passenger cabin through slots. Located downstream of the silencer is a distribution piece for fanning the side windows and pilots’ legs. The heating or ventilating air is supplied to the distribution piece through a hose. The distribution piece is provided with a common control flap for side window and pilots’ legs fanning. In addition, the distribution piece comprises a flap for a separate control of the air for side windows fanning. The flow rate of the air for the heating of pilots’ legs is controlled by independent flaps situated at the fanning outlets. The air intake also comprises a branch for inverter cooling. Apart from the system described above, the aircraft is equipped with a system of individual cold air showers for each passenger and pilot. The cold air for passengers enters through airscoops situated in the fuselage skin. From there, the air is led to air channels provided with air showers. The cold air for pilots, enters through airscoops situated in front of the windshield and is further led by a piping to air showers located on the left-hand and the righthand control panel in the pilots’ compartment. The cold air intakes are provided with a drain piping emptying outside the plane. The venting of exhausted air from passenger cabin is secured by its design. Furthermore there is a KA 33 blower installed in the cockpit between frames 4 and 5 which serves for the cooling of radio - navigation equipment (if installed). The blower is set in operation by switching on BATTERY I, II switches and BLOWER circuit breaker on the overhead panel.
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FIG. 1
DISTRIBUTION OF AIR FOR HEATING AND VENTILATION - SCHEMATIC a - cold atmospheric air intake b - hot air supply (see 021.40.00) Explanatory notes - see the list in paragraph 2.
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MAINTENANCE MANUAL
FIG. 2
SUPPLY OF AIR SHOWERS - SCHEMATIC a - cold atmospheric air intake Explanatory notes - see the list in paragraph 2.
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MAINTENANCE MANUAL
Fig. 3
BLOCK DIAGRAM OF KA 33 BLOWER (if installed)
2. List of components No.
Name
Qty
Location
1.
Air intake with flap
B 580 230 N
1
between frames No. 2 and 3
2.
Annular ejector
B 580 693 N
1
between frames No. 2 and 3
3.
Silencer
B 580 697 N
1
between frames No. 3 and 4
4.
Distribution piece
B 580 206 N
1
between frames No. 4 and 5
5.
Air duct
-
-
passenger cabin floor, LH, RH
6.
Outlet for pilots’ legs fanning
-
-
-
7.
Outlet for side window fanning B 581 270 L, P
-
between frames No. 5 and 6
8.
Airscoop
-
-
-
9.
Air channel
-
-
passenger cabin ceiling, LH, RH
10.
Air shower
B 085 015 N
11.
Air intake
12.
21
-
-
-
-
Hose
16/25.5 CSN 635383
-
between frames No. 1 and 2
13.
Circuit breaker BLOWER (if installed)
AZRGK-5
1
overhead panel
14.
Blower (if installed)
KA 33
1
between frames No. 4 and 5
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DISTRIBUTION SERVICING 1. Check of the air intake of air-conditioning system A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Cloth
C. Tools
Not applicable
D. Referenced information
021.20.00.A Routine
E.
Procedures (1) Check the air intake of the air-conditioning system for the following faults: •
dirt
•
foreign objects in the air intake
(2) Remove dirt, if any, using a clean, soft cloth.
2. Inspection of the heating control flaps and their controls in the pilot's cockpit and passenger cabin A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N), Pocket-size battery lamp
B.
Materials
Not applicable
C. Tools
Z 37.9110-10 screwdriver
D. Referenced information
021.20.00.C Periodical
E.
Procedures (1) Place the steps (e.g. B097365N) to the wing. (2) Remove the wing to fuselage fairing using the Z 37.9110-10 screwdriver. (3) Using the Z 37.9110-10 screwdriver remove the cover on the LH side between frames No. 2 and 4. (4) Check of the controls of the cabin heating and ventilation system. (5) Move the HEATING control lever on the left-hand control panel alternatively to the open and closed position. Another worker watches the shut-off flap (under the front upper wing to fuselage
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MAINTENANCE MANUAL fairing) to see whether its lever is moving correspondingly to the marked open and closed positions. All flaps and controls must take up their correct positions. (6) Move the COCKPIT AIR CONTROL levers on the left-hand control panel alternately to the upper and lower position. Set the left pedal at the left pilot’s seat backward. Using a torch check whether the control levers of the flaps move correspondingly, i. e. to the marked open and closed positions (the levers are located behind the instrument panel on the left-hand side in front of frame No. 4, and are to be checked from the space above the pedals). All flaps and controls must take up their correct positions. (7) Move the VENTILATION control lever on the left-hand control panel alternately to its open and closed position. Another worker checks at the air intake flap whether its lever moves correspondingly. All flaps and controls must take up their correct positions. (8) Place and screw down the cover between frames No. 2 and 4 on the LH side. (9) Set and screw down the wing to fuselage fairing. (10) Remove the steps.
3. Inspection of the compensators in the air distribution ducting between the frames No. 3-4, 8-9 and 11-12 A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N), Steps (e.g. B097300N), 9362
L 410. 9361 mats B.
Materials
4 mm dia., 500 mm long glass fabric Lock wire 0.8 mm dia., CSN 426406
C. Tools
No. 697-6x120 screwdriver L 410.9141-05 screwdriver Z 37.9110-10 screwdriver and necessary tools from tool kit
D. Referenced information
021.20.00.D Periodical
E.
Procedures (1) Place the steps (e.g. B097365N) to the wing. 9362
(2) Unwind the L 410. 9361 mats on the wing.
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MAINTENANCE MANUAL (3) Using the Z 37.9110-10 screwdriver remove the wing-to-fuselage fairing. (4) Using the Z 37.9110-10 screwdriver remove the cover on the LH side between frames No. 2 and 4. Using the L 410.9141-05 screwdriver release the locks on the upholstery overhead panel between the frames No.7 and No.10 and drop down the panels. (5) Inspect and check the compensator bellows at the wing-to-fuselage by pressing it gently. Defects not allowed: cracked or distorted compensators. Replace a defective (cracked) compensator. (6) On the left-hand side of the passenger cabin, between frames No. 8 and 9, carefully remove the tightening insulation in the compensator area to make the compensator accessible. By gently pressing the compensator bellows make sure that any cracks and deformation are not present. Replace defective (cracked) compensator. Re-insulate the compensator with glass fabric and secure the insulation. (7) In the area between frames No. 2 and 4 gently press the compensator bellows to make sure that any cracks and deformation are not present. Replace defective (cracked) compensator. (8) Set and screw up the cover between the frames No. 2 and No. 4 on the left hand side. Cover the upholstery central overhead panels and ensure them with locks using the L 410.9141-05 screwdriver. (9) Install and screw down the wing-to-fuselage fairing. 9362
(10) Roll up and remove the L 410. 9361 mats from the wing. (11) Remove the steps.
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4. Inspection of the compensators in the air distribution ducting between the frames No. 11-12 A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N), Steps (e.g. B097300N), 9362
L 410. 9361 mats B.
Materials
Not applicable
C. Tools
Screwdriver (e.g. Z 37.9110-10) and necessary tools from tool kit
D. Referenced information
021.20.00.E Periodical
E.
Procedures (1) Place the steps (e.g. B097365N) to the wing. 9362
(2) Unwind the L 410. 9361 mats on the wing. (3) Using the screwdriver (e.g. Z 37.9110-10) remove the wing-to-fuselage fairing. (4) Inspect and check the compensator bellows at the wing-to-fuselage by pressing it gently. Defects not allowed: cracked or distorted compensators. Replace a defective (cracked) compensator. (5) Install and screw the wing-to-fuselage fairing. 9362
(6) Roll up and remove the L 410. 9361 mats from the wing. (7) Remove the steps.
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MAINTENANCE MANUAL 5. Inspection of the compensators in the air distribution ducting between the frames No. 3-4 and 8-9 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
4 mm dia., 500 mm long glass fabric Lock wire 0.8 mm dia., CSN 426406
C. Tools
No. 697-6x120 screwdriver, L 410.9141-05 screwdriver, Screwdriver (e.g. Z 37.9110-10) and necessary tools from tool kit
D. Referenced information
021.20.00.F Periodical
E.
Procedures (1) Using the Z 37.9110-10 screwdriver remove the cover on the LH side between frames No. 2 and 4. Using the L 410.9141-05 screwdriver release the locks on the upholstery overhead panel between the frames No.7 and No.10 and drop down the panels. (2) On the left-hand side of the passenger cabin, between frames No. 8 and 9, carefully remove the tightening insulation in the compensator area to make the compensator accessible. By gently pressing the compensator bellows make sure that any cracks and deformation are not present. Replace defective (cracked) compensator. Re-insulate the compensator with glass fabric and secure the insulation. (3) In the area between frames No. 2 and 4 gently press the compensator bellows to make sure that any cracks and deformation are not present. Replace defective (cracked) compensator. (4) Set and screw up the cover between the frames No. 2 and No. 4 on the left hand side. Cover the upholstery central overhead panels and ensure them with locks using the L 410.9141-05 screwdriver.
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B 580 230 N AIR INTAKE WITH FLAP DESCRIPTION AND OPERATION 1. Purpose The air intake supplies the air-conditioning system with cold air. The air flow rate is controlled by a flap.
FIG. 1
B 580 230 N AIR INTAKE WITH FLAP (1) Air intake; (2) Flap; (3) Lever; (4) Pin
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B 580 693 N ANNULAR EJECTOR DESCRIPTION AND OPERATION 1. Purpose The annular ejector mixes the hot air brought from the two engines with cold air conveyed from air intake.
FIG. 1
B 580 693 N ANNULAR EJECTOR (1) Annular ejector; (2) Ejector body; (3) Thermal insulation; (4) Pipe
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B 580 697 N SILENCER DESCRIPTION AND OPERATION 1. Purpose The silencer dampens the noise of the flowing air by means of its insulation filling and by passing the air through the holes in its inner body.
FIG. 1
B 580 697 N SILENCER (1) Shell; (2) Inner body; (3) Filling; (4) Screw with washer
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B 580 206 N DISTRIBUTION PIECE DESCRIPTION AND OPERATION 1. Purpose The distribution piece allows for the air flow to be directed either at the side windows or to the pilot’s legs.
FIG. 1
B 580 206 N DISTRIBUTION PIECE (1),(2) Pipes; (3) Bracket; (4) Flap; (5) Lever; (6) Flexible push-pull rod; (7) Flap; (8) Lever; (9) Flexible push-pull rod; (10) Pin with washer and split pin; (11) Grease nipple
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B 085 015 N AIR SHOWER DESCRIPTION AND OPERATION 1. Purpose The air shower is used for individual fanning of passengers and pilots with cold air. The air shower is mounted so as to be able to deflect in any direction. By extending the plate (1) the cold air flow rate can be controlled.
FIG. 1
B 085 015 N AIR SHOWER (1) Flange; (2) Sphere; (3) Ring; (4) Spring; (5) Packing; (6) Sealing ring; (7) Pin; (8) Circlet; (9) Spring; (10) Bolt; (11) Packing
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B 085 015 N AIR SHOWER SERVICING 1. Checking functions and completeness of air showers A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
021.20.05.A periodical
E.
Procedures (1) Checking functions Check free run of air showers by tilting or turning a knob of air showers. Tilting and turning must be continuous without any breaks. However the position of any air shower must not be changed spontaneously. Simultaneously, check in open position, if the holes of air showers are free and without any contaminants. (2) Checking completeness Check, if air showers above each passenger's seat and in front of both pilots seat are firmly fixed, and both any part of air showers and fixing screws are not missing (see fig. 1).
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B 085 015 N AIR SHOWER REMOVAL / INSTALLATION 1. Removal and installation of the B 085 015 N air shower A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
An appropriately sized screwdriver from the tool kit.
D. Referenced information
-
E.
Procedures (1) Removal of the B 085 015 N air shower. (a) Loosen the bowl (6 screws) with the air shower. (b) Loosen the air shower flange (4 screws). (c) Take out the air shower. (2) Installation of the B 085 015 N air shower. (a) Position the air shower flange and secure it by means of screws. (b) Tighten the screws. (c) Screw down the air shower bowl.
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HEATING DESCRIPTION AND OPERATION 1. General The hot air for the heating is tapped from both engines after the last (radial) compressor stage. The hot air is conducted by a piping provided with thermal insulation. In the area of the engine nacelles, the piping comprises a branch from which the hot air is taken engine air intake deicing - see Chapter 030. The piping is running from the left-hand and the right-hand engine join in a mixer in the wing centre section. Located on the pipings before their entry into the mixer are non-return valves, a compensator and a pipe coupling. The mixer comprises a branch where the hot air is tapped for airframe deicing - see Chapter 030. Welded to the mixer is also a test pressure connection with a blinding plug. The hot air from the mixer is led to a shut-off flap. The shut-off flap controls the hot air flow rate. From the shut-off flap, the hot air is led by a piping with compensators to an annular ejector. The annular ejector incorporates a branch through which the hot air is supplied to the storage battery bay.
FIG. 1
HEATING SYSTEM - SCHEMATIC Explanatory notes - see the list in paragraph. 2
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MAINTENANCE MANUAL 2. List of components No.
Name
Qty
Location
1.
Non-return valve
L 410.8510-08
2
between frames No. 11 and 12
2.
Shut-off flap
B 085 180 N
1
between frames No. 11 and 12
3.
Compensator
L 410.8510-05
1
between frames No. 11 and 12
4.
Mixer
-
1
between frames No. 11 and 12
5.
Compensator
L 410.8520-14
1 1
between frames No. 8 and 9 between frames No. 3 and 4
6.
Storage battery bay heating
-
-
-
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Type (Dwg. No.)
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HEATING FAULT ISOLATION No.
Trouble
Possible causes
Correction
1.
Heating intensity drops at normal engine output.
The shut-off flap opens insufficiently. Remove and dismantle the shut-off When the HEATING lever is moved, flap, find the cause, repair or replace. the flap does not go full travel.
2.
Hot air gets into the cabin even though the shut-off flap is closed.
The shut-off flap has been adjusted incorrectly. Sealing surfaces of the shut-off flap are too worn.
Adjust the shut-off flap.
Excessive force is needed to move the HEATING system control lever.
The shut-off flap is jammed or the flexible push-pull rod seizes.
Remove and dismantle the shut-off flap, clean it in spirit or gasoline. Lubricate the flexible push-pull rod.
3.
CAUTION:
Dismantle the shut off flap and reject or repair it. Replace the rejected flap by a new, oversize one.
WHEN RE-INSTALLING THE NON-RETURN VALVES, CARE MUST BE TAKEN NOT TO MOUNT THEM IN A REVERSED POSITION. FOLLOW THE FLOW DIRECTION ARROWS ON THE NON-RETURN VALVE BODY AND ON THE NEIGHBOURING PIPE SECTIONS.
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HEATING SERVICING 1. Check of the tightness of non-return valves and shut-off flap in the pilot's cabin, passenger's cabin between the frames No. 2-3, wing, engine nacelles A.
Fixture, Test and Support Equipment
Test equipment consisting of compressed air bottle, pressure gauge and pressure hose with possibility of 2
reduction to pressure of 0.39 MPa (4 kp/cm ); Stepladder (e.g. B097365N); Stepladder (e.g. B097300N); L 410.9362, 9361 Mats B.
Materials
Asbestos cord (or equivalent), dia 4 mm, length 500 mm dia. 0.8 mm, CSN 426406 Locking wire; B851037N (or L410.8510-10) Seal (2 pcs); B852048N (or L410.8520-25) Seal (2 pcs); HILOMAR 5Q 32H Sealing compound (1 tube)
C. Tools
No. 697 (4.5x120, 6x120) Screw driver; Z 37.9110-10 Screw driver; L 410.9141-05 Screw driver; CSN 292327.1 Pincers; CSN 230341.4 Wire pliers; 17 CSN 290625.6 Open-end wrench; 30 CSN 230625.6 Spanner; 5.5x7 CSN 230611.6 Spanner; L 410.8510.6 Blinding plug
D. Referenced information
021.40.00.A Periodical
E.
Procedures (1) Put the stepladder (e.g. B097365N) to the wing - and the stepladder (e.g. B097300N) to the engine nacelle. 9362
(2) Put the L 410. 9361 mat on the wing. (3) Remove the wing-to-fuselage fairing using a Z 37.9110-10 screwdriver.
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021.40.00 Page: 301 May 30/14
MAINTENANCE MANUAL (4) Open the lower engine cowl of the engine nacelles using a screwdriver No. 697-6x120. (5) Remove the upper front cowl, rear cowl, and the side cowl panel from both engine nacelles according to the instructions given in chapter 054. (6) Release the press button fasteners and remove the caps on the lower side of the wing leading edge, next to the engine nacelles. (7) Remove the cover on the fuselage located between bulkheads No. 2 and No.4 on the left hand side of the nose section using the Z 37.9110-10 screwdriver. (8) Check of tightness of non-return valves and shut-off flap valve. (9) Check for tightness of the heating system in the wing and fuselage, including check of tightness of the non-return valves and the shut-off flap valve as follows: (a) Using pincers, remove locking wires from the bleed air distribution pipelines and bushings located on the frame No.4 which fasten the compensator to the bleed air distribution pipelines. Remove the compensator with caution. (b) Using a 5.5 x 7 CSN 230611.6 spanner, loosen two nuts of the sleeves located in the front area between the frames No. 2 and 3 which fasten the compensator to the bleed air distribution pipelines. Remove the compensator carefully. (c) Using a 5.5 x 7 CSN 230611.6 spanner, loosen two nuts of the sleeves located under the front upper part of the wing-to-fuselage fairing which attach the compensator to the air ejector branch pipe and the pipeline. Remove the compensator carefully. Blind the branch pipe end with blinding plug. (d) Set the HEATING lever on the LH control panel to CLOSED position. (e) Connect hose of the test equipment consisting of a compressed air bottle provided with a pressure gauge, and a pressure hose to the LH bushing located on the lower side of the leading edge above the engine. The hose is connected to the bushing by means of a union nut. (f)
2
Apply air pressure of 0.39 MPa (4 kg/cm ) to the pipeline. Pressure drop in the system from 2
2
0.39 MPa (4 kg/cm ) to 0 MPa (0 kg/cm ) in less than 20 seconds is not permissible. (g) Set the HEATING lever on the LH control panel to OPEN. (h) Blind the open end of the pipeline in front of the frame No.4 by an L 410.8510-06 blinding plug. (i)
Disconnect the hose of the test equipment from the bushing on the leading edge, remove the test equipment, and connect it to the bushing on the RH wing (see paragraph (d)).
(j)
2
Apply air pressure of 0.39 MPa (4 kg/cm ) to the pipeline. Pressure drop in the system from 2
2
0.39 MPa (4 kg/cm ) to 0 MPa (0 kg/cm ) in less than 20 seconds is not permissible.
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MAINTENANCE MANUAL (k) Remove the test equipment. Connect the bleed air pipelines to the bushings using a 30 CSN 230 625.6 spanner. Before connecting the two parts, smear the pipe union with HILOMAR 5Q 32/H sealing compound. Lock the pipe union with 0.8 mm dia. locking wire using wire pliers. (l)
Reinstall the compensator between the pipeline and the annular ejector in the space between frames No. 2 and 4. Use new B851037N (L410.8510-10) seals for the compensator joints. Smear the seals with HILOMAR 5Q 32H compound before fitting them. Connect the compensator to the pipeline by means of sleeves. Tighten the sleeves by nuts using a 5.5 x 7 CSN 230611.6 spanner.
(m) Reinstall the compensator between the pipeline and the mixer in the space under the upper front part of the wing-to-fuselage fairing. Use new B852048N (or L410.8520-25) seals for the compensator joints. Smear the seals with HILOMAR 5Q 32/H compound before fitting them. Connect the compensator to the pipeline and to the mixer branch pipe by means of sleeves. Tighten the seals by must using a 5.5 x 7 CSN 230611.6 spanner. (10) Reinstall and screw on the cover on the left side of the nose section, between bulkheads No. 2 and 4. (11) Fasten the caps on the lower side of the wing leading edge next to the engine nacelles. (12) Reinstall the upper front cowl, rear cowl, and the side cowl panel of both engine nacelles as instructed in chapter 054. (13) Close the lower engine cowl of both engine nacelles. (14) Fit and reinstall the wing-to-fuselage fairing. 9362
(15) Remove the L 410. 9361 mats. (16) Remove the stepladders.
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MAINTENANCE MANUAL
2. Check of the function of the heating control flap on the left control panel A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Gasoline, Lubricate gel
C. Tools
Not applicable
D. Referenced information
021.40.00.B Periodical
E.
Procedures (1) Check of the heating control flap (shut-off flap) free movement (2) Open and close the hot air supply by the HEATING control lever on the left-hand control panel. Defects not allowed: seizing of the flap during its opening or closing. (3) If the flap is defective, proceed as follows: (a) Remove the flap - refer to the work procedure in 021.40.02. (b) Disassemble the shut-off flap and wash its moving parts in gasoline. If the flap has been distorted or damaged in any other way, correct the defect. (c) Install the shut-off flap - refer to the work procedure in 021.40.02. (d) Check free movement of the shut-off flap - refer to the step (1).
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MAINTENANCE MANUAL
HEATING REMOVAL / INSTALLATION 1. Removal of heating system piping in the fuselage A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Remove the cover of the upper wing-to-fuselage fairing, ceiling upholstery in the top front part of the left-hand of the fuselage between frames No. 7 and 11, as well as the upholstery on the left-hand bottom part of the fuselage between frames No. 7 and 8. (2) Remove the left-hand pilot’s seat and the floor sections in this area. (3) Remove the aluminum wrapping foil from the piping and disconnect the flexible push-pull rod from the piping. (4) Remove the covers on the left-hand side between frames No. 2 and 4, using the Z 37.9110-10 screwdriver. (5) Successively remove the following components (see Fig. 401): piping (1); compensator (2); piping (5); piping (6); compensator (2); piping (7); piping (4) and shut-off flap (3). The shut-off flap should be removed in accordance with the appropriate work procedure. Before removal, release all the pipings as well as the flexible push-pull rod from their clips.
FIG. 401
HEATING SYSTEM PIPING IN FUSELAGE (1) Piping; (2) Compensator; (3) Shut-off flap; (4) Piping; (5) Piping; (6) Piping; (7) Piping
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MAINTENANCE MANUAL 2.
Installation of the heating system piping in the fuselage A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
L 410.8520-25 packings HILOMAR 5Q 32/H sealing compound (one tube)
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Successively install the piping sections (4), (7), (6) and (5) - see Fig. 401 from frame No. 11 as far as frame No. 4, including the compensator (2) between frames No. 8 and 9. Attach the pipings and the flexible push-pull rod with clips. Use new packings to seal the joints. Apply thin coat of HILOMAR 5Q 32/H sealing compound to the packings prior to installation. NOTE:
The piping section and compensator between frames No. 2 and 4 will be installed only after the tightness check of the heating system piping joints.
(2) Carry out the tightness check of the heating system in fuselage in accordance with the appropriate work procedure. (3) Install the shut-off flap (3) according to the appropriate work procedure. (4) Install the pipe section (1) and compensator (2) at frame No. 2. Use new packings to seal the joints. Apply thin coat of HILOMAR 5Q 32/H sealing compound to the packings prior to installation. (5) Place and screw down the covers on the left-hand side between frames No. 2 and 4. (6) Re-wrap the piping in aluminum foil and the upholstery inside the fuselage. (7) Re-install the left-hand pilot’s seat and the corresponding floor sections. (8) Install the cover of the upper wing-to-fuselage fairing.
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3. Removal of the heating piping in the wing A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Remove the cover of the upper wing-to-fuselage fairing. (2) Remove the upper front wing cover behind the engines, and the assembly lids on the bottom skin of the wing at the engine nacelles. (3) Remove the pneumatic deicing piping (8) - see fig. 402. (4) Remove the bracket attaching the piping (9) at the wing flap actuator. (5) Release the piping sections (6) and (7) from attaching sleeves (10). Remove the coupling clamps, compensator (11), pipe coupling (12), mixer (4) and the pipe sections (6) and (7).
FIG. 402
HEATING SYSTEM PIPING IN THE WING (1) Non-return valve; (2) Piping; (3) Coupling; (4) Mixer; (5) Shut-off flap; (6) Piping; (7) Piping; (8) Pneumatic deicing piping; (9) Bracket; (10) Attaching sleeve; (11) Compensator; (12) Pipe coupling
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MAINTENANCE MANUAL 4. Installation of heating system piping in wing A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
The L410.8510-10 Sealing
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Successively install the piping section (6), piping section (7), mixer (4), compensator (11), pipe coupling (12) and bracket (9) and attaching sleeves (10) - see fig. 402. (2) Test the assembled piping for tightness in accordance with the work procedure in 021.20.00. (3) Install the pneumatic de-icing piping (8) (4) Fit the upper wing cover behind the engines and the assembly lids on the bottom skin of the wing at the engine nacelles. (5) Fit the upper wing-to-fuselage fairing cover.
5. Removal of the heating piping in the engine nacelle A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
The 0.5 mm dia lock wire
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Open the lower engine cowl of the engine nacelle and remove the upper cowl of the engine nacelle. (2) Remove the lock wire from the couplings of the piping (4) and (5) - see fig. 403. (3) Remove the piping section (5) by disconnecting it from the coupling (7) in the fire wall and from the coupling (8) in the wing. (4) Remove the piping section (4) by disconnecting it from the coupling (7) in the fire wall, the shut-off cock coupling (9) and the engine. (5) Protect the uncoupled ends by wrapping them in polyethylene foil. NOTE:
When dismantling the piping, use two spanners to avoid transferring the torque onto the piping.
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MAINTENANCE MANUAL
FIG. 403
HEATING PIPING IN ENGINE NACELLES (1) Bolt; (2) Flange; (3) Gasket; (4) Piping; (6) Thermal insulation; (7) Fire wall coupling; (8) Wing coupling; (9) Shut-off cock
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MAINTENANCE MANUAL
6. Installation of heating piping in engine nacelle A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
0.5 mm dia. zinc coated lock wire. the Hilomar 5Q 32H Sealing glue
C. Tools
Crown-head socket wrench. Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures NOTE:
Paint all connections with the Hilomar 5Q 32H sealing glue
(1) Remove the polyethylene foil from the pipe section (4) - see fig. 403. Blow the piping through, set it on the engine and fit the bolts (supplied by the engine manufacturer). Only a crown-head socket wrench can be used for this purpose. Connect the remaining ends of the piping to the fire wall coupling (7) and the shut-off cock (9) coupling. After installation lock all couplings, bolts and nuts with 0.5 mm dia. lock wire. (2) Re-install the pipe section (5) by connecting it to the fire wall coupling (7) and to the wing coupling (8). Before the assembly apply a thin layer of Hilomar 5Q 32H onto the couplings. After installation lock the couplings with 0.5 mm dia. lock wire. NOTE:
2
Test the pipe section (5) for tightness with pressure air of 0.78 MPa (8 kp/cm ) for five minutes.
(3) Fit the upper cowl of the engine nacelle and close the lower engine cowl of the engine nacelle. NOTE:
When assembling the piping, use two spanners to avoid the torque transfer onto the piping.
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L 410.8510-08 NON-RETURN VALVE DESCRIPTION AND OPERATION 1. Purpose The non-return valve prevents the pressure air in the hot air piping from escaping into the atmosphere if one of the engines fails. The non-return valve closes the failed engine branch by means of flaps.
FIG. 1
L 410.8510-08 NON-RETURN VALVE (1) Shell; (2) Pin; (3) Grille; (4) Flaps; (5) Pin a = air flow direction
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L 410.8510-08 NON-RETURN VALVE REMOVAL / INSTALLATION 1. Removal of L 410.8510-08 non-return valve A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information
-
E.
Procedures (1) Remove the wing-to-fuselage fairing cover. (2) Remove the clamps attaching the non-return valve. (3) Remove the packings between the non-return valve and the compensator or the pipe coupling, and the mixer. Remove the non-return valve.
2. Installation of L 410.8510-08 non-return valve A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
L 410.8510-10 packings (4 pieces) HILOMAR 5Q 32/H sealing compound
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit
D. Referenced information
-
E.
Procedures (1) Install the non-return valve between the mixer and the compensator or pipe coupling. Insert the L 410.8510-10 packings. Apply a thin coat of HILOMAR 5Q 32/H sealing compound to the packing before installation. CAUTION:
INSTALL THE NON-RETURN VALVE IN SUCH A WAY THAT THE ARROW ON ITS BODY AGREES WITH THE AIR FLOW DIRECTION I.E. FROM THE ENGINE TO THE MIXER.
(2) Fix the non-return valve with clamps. (3) Screw down the cover of the wing-to-fuselage fairing.
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B 085 180 N SHUT-OFF FLAP DESCRIPTION AND OPERATION 1. Purpose The shut-off flap opens or closes the hot air supply from the engine compressors to the air-conditioning system.
FIG. 1
B 085 180 N SHUT-OFF FLAP (1) Control lever; (2) Pipe; (3) Flap; (4),(5) Bushings; (6) Screw; (7) Screw; (8) Diaphragm; (9) Screw O = open Z = closed
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B 085 180 N SHUT-OFF FLAP REMOVAL / INSTALLATION 1. Removal of B 085 180 N shut-off flap A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information
-
E.
Procedures (1) Remove the wing-to-fuselage fairing cover. (2) Remove the split pin, pin and washer connecting the control rod with the flap lever. (3) Remove the clamps attaching the shut-off flap. Remove the packings between the shut-off flap, mixer and piping. Remove the shut-off flap.
2. Installation of B 085 180 N shut-off flap A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
L 410.8520-25 packing (2 pieces) AEROSHELL GREASE 6 lubricating grease HILOMAR 5Q 32/H sealing compound (one tube)
C. Tools
Spanners and screwdrivers of appropriate sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Install the shut-off flap between the piping and the mixer. Insert the L 410.8520-25 packings. Apply a thin coat of HILOMAR 5Q 32/H sealing compound to the packings prior to installation. (2) Attach the shut-off flap by means of the clamps. (3) Connect the control rod by means of the pin, washer and split pin. Before assembly, grease the pin with the lubrication grease in use. (4) Check the shut-off flap function. Pay special attention to the tightness of the flap in its closed position. (5) Screw down the wing-to-fuselage fairing cover.
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COOLING (if installed) DESCRIPTION AND OPERATION 1. General The R-134a Air Conditioning System by the ENVIRO SYSTEMS Inc. is designed to maintain a required temperature to the cockpit and the passenger cabin. The system is controlled manually.
2. List of components No.
Name
Qty
Location
1
Conditioned air outlet
B585328N
4
refer to the fig. 3
2
Air duct (distributor)
B584636N
2
between 20 and 21st frame upper LH and RH side
3
Evaporator module
ENVIRO P/N 1134200-68 (95225857)
1
between 20 and 21st frame upper RH side
4
Evaporator module
ENVIRO P/N 1134200-69 (95225858)
1
between 20 and 21st frame upper LH side
5
Air duct (hoses)
BWT10-2140540D BAXT (87150175)
4
refer to the fig. 3
6
Compressor condenser module
ENVIRO P/N 1134400-11 (95217082)
1
Between frames 2 and 4
7
Hot air outlet
B584570N
1
between 2 and 3 frame
8
Contactor
6041 H215 MS 24171-1D
1
component of compressor
9
Contactor
TKS 201 DOD
1
between 2 and 3 frame
10
Switch-over COOL/OFF/FANS
2 TL 1-1E
1
LH control panel
11
Switch-over HI/LO
1 TL 1-3
1
LH control panel
12
Signal cell FANS-COMP.
02 LUN 2697.03-8
1
LH control panel
13
Relay
TKE 52 PODGB
1
between 2 and 3 frame
14
Pressure switch
1250 232
1
component of compressor
15
Fuse
IP 150
1
right side between 1 and 2 frame
16
Fuse
IP 100
1
on 8 frame the right
17
AIRCONDITION circuit breaker
AZRGK-15
1
overhead panel
18
AIRCONDITION fuse
F/0.63A EN60127-2/1500
1
Frame 4
19
Relay
TKE 52 PODGB
2
between 7 and 8 frame
20
Relay
TKE 52 PODGB
1
between 9 and 10 frame, LH
21
Fuse
F/0.63A EN60127-2/1500
1
between 8 and 9 frame
22
COMPR. START push-button KNR
1
LH control panel
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Type (Drwg. No.)
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MAINTENANCE MANUAL
3. Operation Cabin air is sucked into air ducts located on both sides of the passenger compartment. Air passes through the ducts to the evaporator where it is cooled. The cool air is then discharged by the evaporator blower into air ducts and blower out into the passenger cabin. 28 V DC It is actuated by an AIRCONDITION circuit breaker supplies the air conditioning system. Located on the overhead panel. When the circuit breaker is switched on the AIRCONDITION light on the LH control panel will illuminate. Setting the air-conditioning mode selector on the LH control panel into FANS position will actuate the blowers, which is indicated by the illumination of the FANS light on the LH control panel. When the selector is set into the COOL position, the air conditioning package (blowers and the compressor) will be actuated and the FANS and COMP lights on the LH control panel will illuminate. A HI/LO blower speed selector is also located on the LH control panel. Operation described above is valid for putting the system into operation on the ground. During flight the system is put into operation by means of the push-button COMPR. START. NOTE:
EFFECTIVITY ALL
Operation in flight is described in the Flight Manual.
021.50.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL
FIG. 1
BLOCK DIAGRAM OF AIRCONDITIONING SYSTEM
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MAINTENANCE MANUAL
FIG. 2
REFRIGERANT DISTRIBUTION AND COMPRESSOR COOLING (SEE LIST OF INSTRUMENTS FOR LEGEND)
FIG. 3
COOL CONDITIONED AIR DISTRIBUTION (SEE LIST OF INSTRUMENTS FOR LEGEND)
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MAINTENANCE MANUAL
FIG. 4
AIRCONDITONING SYSTEM Legend to figure - see the following page
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021.50.00 Page: 5 May 30/14
MAINTENANCE MANUAL Legend to fig. 4 (1) AIR-CONDITION circuit breaker; (2) Signal cell FANS-COMP.; (3) Switch-over HI/LO; (4) Switch-over COOL/OFF/FANS; (5) COMPR. START push button; (6) AIR-CONDITION fuse; (7) Relay TKE 52 PODGB; (8) Contactor TKS 201 DOD; (9) Fuse IP 150; (10) Compressor; (11) Fuse IP 100; (12) Fan; (13) Inlet air; (14) Hour meter
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MAINTENANCE MANUAL
COOLING (if installed) SERVICING NOTE:
Service hours are indicated on the hour meter see fig.4 - position (14). Hour meter is operating under way compressor only. Use light and mirror for read service hours.
WARNING:
DANGER BELT!
1. Inspection of the tension and/or alignment of the compressor drive belt A.
Fixture, Test and Support Equipment
P/N T1134610 (95225872) Enviro belt tensioning tool; P/N FDK-10 (95225873) Wagner spring scale; Eye protection
B.
Materials
Not applicable
C. Tools
Small hand tools and socket set.
D. Referenced information
021.50.00.A Periodical
E.
Procedures
The following is a recommended component maintenance / inspection schedule and associated service hours: Type maintenance
Service hours
Visual inspection
500 - 800
Tension & alignment
800 - 1000
Replacement
On condition
When the compressor drive belt requires removal and replacement, tension or alignment the following procedures will apply: A.
Belt removal procedure: (1) Verify all airplane or ground power to motor is off. (2) Remove all access panels and exhaust ducts to gain access to the compressor module. (3) Remove all fasteners securing the belt guard assy (4) With socket and box end type wrenches slightly loosen the two 3/8 bolts that support the R-134a compressor. (5) Loosen (ccw turn) tension nut on compressor side of rod end bearing and swing compressor down to loosen belt.
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MAINTENANCE MANUAL (6) Loosen socket head set screws in motor pulley and slide pulley off motor shaft while at the same time sliding the drive belt off the compressor pulley. NOTE:
This procedure assures that the motor pulley flange and belt are not damaged during removal.
CAUTION:
DO NOT BEND OR TWIST EXCESSIVELY THE DRIVE BELT DURING REMOVAL, OR DAMAGE CAN OCCUR.
(7) Inspect belt for cracks or missing teeth and clean any oil or other contamination from both pulleys and belt. B.
Drive belt replacement procedure: (1) Verify belt size and part number before installing or damage may result. (Belt P/N 232L 100). (2) Verify # 3 woodruff key is installed on motor shaft. (3) Place belt on motor pulley and slide pulley on end of the motor shaft and at the same time slide belt over compressor pulley. Slightly tap the motor pulley on the shaft until the belt completely covers the compressor pulley. NOTE:
Verify the belt teeth are in grooves of each pulley and during installation rotate both pulleys slightly to assure proper engagement.
CAUTION:
DURING THESE PROCEDURES DO NOT SHARPLY BEND OR TWIST THE BELT AND DO NOT ALLOW BELT TO ROTATE ON MOTOR PULLEY FLANGE. DAMAGE TO BOTH MAY RESULT.
(4) After the belt is installed, rotate the compressor pulley clockwise (cw) to align belt on pulley. The belt must ride directly over the compressor pulley. NOTE:
If the belt is too far forward or aft on the compressor pulley the motor pulley must be adjusted fore or aft allow belt to ride directly over compressor pulley.
(5) If belt alignment is good, slightly tighten the two (2) 3/8 compressor support bolts and turnrod end bearing adjust nut until snug. C. Drive belt alignment procedure: (1) Loosen motor pulley set screws, if required. With motor pulley on shaft rotate compressor pulley clockwise (cw) with a suitable wrench. At the same time slide the motor pulley forward or aft until the belt rides directly over the compressor pulley. (2) Slightly tighten the motor pulley set screws and rotate the compressor pulley clockwise (cw) for approximately ten (10) revolutions to assure belt is tracking as required. If so, tighten the set screws. (3) Belt is ready for tensioning.
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MAINTENANCE MANUAL CAUTION:
ALL BOLTS MUST BE SLIGHTLY TIGHT BEFORE ALIGNMENT IS PERFORMED OR BELT MISALIGNMENT MAY RESULT.
D. Drive belt tensioning procedure: (1) Verify all compressor mounting hardware is slightly tight and belt is properly aligned. (2) Apply hand pressure to the compressor to increase belt tension and tighten upper compressor mounting bolt. NOTE: CAUTION:
A Wagner FDK-10 spring loaded force gauge is required for this procedure. DO NOT OVER TENSION BELT. BELT OR MOTOR BEARING DAMAGE MAY RESULT.
(3) Place Enviro belt tension tool on drive belt and orient as shown in figure 301. (4) Position the spring scale into the pilot hole on the tensioning fixture corresponding to the belt mid-span between pulleys. (5) Depress the spring scale until the plunger housing contacts the tension tool surface.
FIG. 301
BELT ALIGNMENT (6) The scale should indicate a load of 1.50 to 1.75 lbs. NOTE:
This is equivalent to a belt deflection of 0.10 inch with a mid-span force of 1.50 to 1.75 lbs.
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MAINTENANCE MANUAL (7) Repeat paragraph (2) and (5) until proper belt tension is achieved. (8) When proper belt tension is obtained tighten compressor mounting bolts. Torque the nuts to 19.7 22.6 N.m (175 - 200 in-Ibs). (9) Recheck belt alignment as described in section (C.) in this procedure and adjust as required. CAUTION:
DO NOT OVER TENSION THE BELT. IMPROPER BELT TRACKING AND BELT / MOTOR DAMAGE CAN HAPPEN.
2. Inspection of the brush and bearing of the compressor drive motor A.
Fixture, Test and Support Equipment
Micrometer Scribe or wire hook Volt-OHM meter (digital) Shop air, 40 psig (max) Eye protection Respiration mask
B.
Materials
P/N 125 1171 Brush
C. Tools
Small hand tools and socket set.
D. Referenced information
021.50.00.B Periodical
E.
Procedures
The following is a recommended component maintenance / inspection schedule and associated service hours: Type maintenance
Service hours
Brush inspection
500 - 800
Brush replacement
800 - 1000
Bearing inspection
1000-1500
Bearing replacement
2500- 3000
Motor overhaul
2500- 3000
A periodic brush inspection is required to assure that excessive damage to the motor commutator or armature does not occur. A visual inspection shall be performed at 500 - 800 hours of operations or less frequently as service experience indicates. Inspection of the drive motor shall be performed in accordance with, but not limited, to the following:
Brush wear inspection
Commutator wear inspection
Internal contamination inspection
Bearing noise inspection
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MAINTENANCE MANUAL A.
Motor brush inspection: (1) Verify all electrical power is off to system. (2) Remove all access panels and exhaust ducts to gain access to the drive motor. (3) Disconnect power leads from motor terminals (1/4-28). Tag positive lead. (4) Remove condenser support bracket to provide access to brush cover fasteners and remove motor cuff shroud. (5) Loosen and unsnap the brush cover assembly. Remove it from the motor. (6) With wire hook or scribe, lift the brush spring and remove the brush. (7) Inspect the brush for cracks, chipped edges, frayed leads, loose rivets or shunt connections. Replace defective brush(es). (8) Continue inspection until all brushes have been checked. In addition, inspect brush holders and springs for looseness, damage from arcing, heat distortion or cracks. NOTE:
All brushes should indicate uniform wear.
(9) Measure each brush as shown in figure 302 and record values. Using the brush with the shortest measured length calculate the wear rate by subtracting the measured value from 1.000 inch and dividing by the operating hours. The remaining brush life is obtained by subtracting. 450 inch (minimum length) from the measured brush wear and dividing by the wear rate. (10) With brushes removed and using shop air at 40 psig (max) and nozzle, blow out as much carbon and/or copper dust as possible out of the commutator, armature and field windings. Purge from the commutator end of the motor. (11) Replace existing brushes in holder with brush chamfer leading edge pointing in the direction of rotation of the commutator as shown in figure 302. CAUTION:
REPLACE THE BRUSHES FOR THE ORIGINAL TYPE P/N OF THE BRUSHES. USING NON-ORIGINAL TYPE OF BRUSHES MAY DAMAGE THE AIR-CONDITION SYSTEM.
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MAINTENANCE MANUAL
FIG. 302
BRUSH DATA A. NEW BRUSH LENGTH
1.00 INCH
B. MINIMUM WEAR LGTH
0.45 INCH
C. USABLE BRUSH LGTH
0.55 INCH
Example Brush wear
= 1.000 - measured value. = 1.000 - .700 =. 300 inch.
Wear rate
=.300 = .300 (wear) = 0006 (in/hr) hours 500 hr
Usable brush length
= measured value - min. length = .450 inch = .700 - .450 = .250 inch
Remaining brush life =
usable brush wear length wear rate =.250 = 416 hrs .0006
NOTE:
All brushes should indicate uniform wear.
CAUTION:
BRUSHES MUST BE CHECKED PRIOR TO REMAMING BRUSH LIFE HOUR CALCULATED OR, DAMAGE TO MOTOR WILL BE CAUSED. FOR BRUSH REPLACEMENT SEE PARAGRAPH F. EYE AND MOUTH PROTECTION MUST BE USED DURING THIS OPERATION OR EXCESSIVE LUNG AND EYE IRRITATTON WILL OCCUR. DO NOT DIRECT AIR JET ON BEARING OR INTERNAL CONTAMINATION WILL RESULT. DURING BRUSH REPLACEMENT DO NOT ALLOW BRUSH SPRING TO SNAP INTO PLACE QUICKLY, OR DAMAGE TO BRUSH CAN HAPPEN. ALSO DO NOT CHIP OR SCRATCH BRUSH CONTACT SURFACE DURING INSTALLATION.
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MAINTENANCE MANUAL B.
Commutator wear inspection: While the brushes are removed for inspection the commutator must be inspected for excessive or uneven wear. The commutator should have a burnished appearance with light filming. If the commutator is black, burned, pitted or excessively worn, the motor should be replaced. If the depth of the mica undercut remaining on the commutator is less than .020 inch the motor should also be replaced.
C. Motor insulation resistance check: After the inspection of the commutator a quick check of the motor insulation resistance should be performed. This check may be done with or without the brushes installed but the power leads must be removed from the motor during this procedure. (1) Verify that unit power is off and disconnect leads. (2) With ohm meter positive lead connected to the motor positive terminal and the other lead connected to the motor case (ground) measure and record the resistance. Resistance value must be equal to or greater than 10 K. If less, the motor should be replaced. D. Internal contamination inspection: (1) Verify that no foreign matter is lodged in the motor air intake or field winding areas. (2) Inspect for excessive moisture in motor or corrosion of parts. (3) Purge motor and air passages as required to remove any dust, dirt or other contamination. E.
Motor bearing inspection: Motor bearings should be inspected every 800 - 1000 operational hours to assure that premature seizure does not occur. (1) Verify that unit power is off and the motor is accessible. (2) On unitized systems (containing a condenser coil assembly) disconnect compressor discharge hose clamp and remove condenser support bracket to access the brush cover. (3) Remove the brush cover. On some systems removal of motor power leads is required prior to brush cover removal, tag positive terminal. (4) Remove brushes from brush guides and remove drive belt and motor pulley as outlined in technol. procedure 1. (in this section) (5) Rotate motor shaft with fingers to obtain "feel" of bearings rotating. If rotation is rough or bearings sound dry, the motor should be replaced. CAUTION:
CAREFULLY LAY BRUSH SHUNT LEADS IN A POSITION WHICH WILL PREVENT ANY POSSIBLE SHORTING PROBLEMS. LEADS MUST BE ABLE TO EASILY FOLLOW BRUSH AND SPRING MOVEMENT AS BRUSH WEAR OCCURS. IMPROPER LEAD PLACEMENT WILL RESULT IN MOTOR DAMAGE.
(6) If bearings rotate smoothly, install belt and brushes. Check belt alignment and tension as described in technol. procedure 1. (in this section)
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021.50.00 Page: 307 Dec 10/14
MAINTENANCE MANUAL (7) Replace the brush cover, tighten and safety wire brush cover screws. Replace the motor cooling fan shroud if equipped. (8) Replace condenser support bracket and secure all screws with lock wire. Attach a clamp to the compressor discharge hose. Connect the power leads to 1/4-28 motor power terminal studs and cover them with insulating boots, if required, prior to condenser support bracket installation. (9) Replace the drive belt and pulley, align and tension as described in technol. procedure 1. (in this section). F.
Motor brush replacement: Motor brushes must be replaced when remaining brush length (the worst brush) is .450 inch as shown in figure 302. New brushes may be installed by first level maintenance personnel only under the following conditions:
Motor was operating correctly prior to brush replacement.
Motor inspection did not show any defects which would require motor replacement.
Only approved vendor brushes are used.
Brushes are installed, seated and tested in accordance with the following procedures.
(1) Verify all power is off, all panels, shrouds, brackets and fairings are removed. (2) Perform brush inspection procedure as outlined in paragraph A (if required). (3) With a stiff wire hook or scribe lift brush spring from the holder and remove each worn brush set until all four sets are removed. NOTE:
Verify that motor commutator is clear of any contamination and all carbon dust is removed.
(4) Remove the brush shunt wire terminal screw and discard the worn brush set. Continue this step until all four screws are removed. (5) Install each brush set by lifting brush springs, sliding the brush into the holder (with brush leading edge in direction of motor rotation) and lightly releasing the brush spring on the brush. (See figure 302). CAUTION:
DO NOT THE ALLOW BRUSH SPRING TO STRIKE HARD INTO PLACE, OR DAMAGE TO BRUSH CAN HAPPEN.
(6) Verify that the brush seats flat on the commutator and that no binding in holder is present. Align the brush spring in the center of the brush groove. (7) Install the terminal screw and the lock washer on the brush shunt lead and other leads and tighten. Repeat this step for other brush sets. CAUTION:
DO NOT CROSS THREAD OR OVER TORQUE BRUSH LEAD SCREWS OR THREAD DAMAGE MAY RESULT.
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021.50.00 Page: 308 Dec 10/14
MAINTENANCE MANUAL (8) Seat new brushes in accordance with the following procedure. All new brushes must be seated to assure proper motor operation and/or performance. If the motor is operated without seating brushes the motor warranty may be voided. CAUTION:
EXCESSIVE SEATING IS NOT ADVISED. BRUSH LIFE MAY BE REDUCED REMOVE SAND PAPER AND BLOW OUT ALL CARBON DUST FROM THE COMMUTATOR AND BRUSH AREA EYE, NOSE AND THROAT PROTECTION MUST BE WORN DURING THIS PROCEDURE.
(9) Carefully lay the brush shunt leads in such position as to prevent any shorting problems. Leads must be able to easily follow brush and spring movement as brush wear occurs. (10) Replace the brush cover and attach the motor power cables, if required. (11) Replace all bracketry and hardware removed to access motor. (12) Visually inspect unit to assure that the bracketry is properly installed, the cooling fan does not interfere with the shroud, the motor drive belt aligned / tensioned and the belt cover is installed. (13) The motor should be tested to verify proper operation. Therefore, connect ground power source or verify airplane power is on and turn the system on. (14) Run the system for minimally 15 minutes to seat brushes and check motor operation. (15) Turn the system and airplane power off. System is ready for use.
BRUSH SEATING PROCEDURE Cut a 7 inch long by 1. 5 inch wide strip of 400 500 grit sand paper and place, with rough side out, on the commutator Secure one end of the paper to the commutator with the masking tape in such manner so that the taped end will lead in the direction of shaft rotation (ccw looking at fan end). The other end will remain loose and overlap the taped end. Raise each brush momentarily while rotating the shaft until the taped end passes under each brush. After the sand paper is properly located tight against the commutator and encompasses all brush surface areas, carefully rotate the armature, by hand, in the normal direction of rotation until a full seat is obtained on each new brush. Three or four rotations are usually adequate.
EFFECTIVITY ALL
021.50.00 Page: 309 Dec 10/14
MAINTENANCE MANUAL 3. Check of the R-134A compressor assembly for leakage of oil refrigerant A.
Fixture, Test and Support Equipment
R-134a charging manifold with gauges and hoses. R-134a electronic leak detector. R-134a refrigerant cylinder. Hand and eye protection.
B.
Materials
Leak check fluid, (soapy solution). Thread sealant Dry nitrogen, regulated. Isopropyl Alcohol, flush liquid.
C. Tools
Small hand tools and socket set.
D. Referenced information
021.50.00.C Periodical
E.
Procedures
The following is a recommended component maintenance / inspection schedule and associated service hours: Type maintenance
Service hours
Leak check, shaft seal
500 - 800
Bearing inspection
1000 - 1500
Bearing replacement
On condition
Oil level check
On condition
The compressor assembly requires more inspection than maintenance since field repair with first line technicians is limited. Inspection consists of checking for excessive oil leaks, belt alignment / tension and refrigerant leaks. The compressor should be periodically checked at 500-800 hours of operation in which the following should be performed: A.
Compressor inspection procedure: (1) Verify that ground power or airplane power to the system is off. (2) Remove access doors, exhaust ducts and enclosures to gain access to the compressor. (3) Remove the belt cover and inspect for alignment and tension (Refer to the work procedure No. 1. - in this section). (4) Visually inspect the compressor pulley for excessive wear, nicks, cracks or looseness. (5) Visually inspect the compressor shaft for excessive oil leaks.
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021.50.00 Page: 310 Dec 10/14
MAINTENANCE MANUAL NOTE:
If excessive oil is noted, the compressor should be checked for leaks. Use fluid or leak detector as required. If leak is noted, the compressor should be replaced. If compressor has not been operated for 30-60 days or more, the dynamic shaft seal may have a small leak due to lack of oil on seal surface. Operation of system should eliminate this type of leak If not, replace the compressor.
(6) Check all fasteners for looseness. Re-torque as required. (7) Visually check the drive belt for cracks, wear and excessive oil. With clean shop rag clean all oil and other contamination from the belt cogs. NOTE:
Checking the compressor oil quantity is only required if an excessive amount of oil is observed due to leaking or the system has been vented very quickly thereby causing a loss of oil. An oil check can only be made with the system vented. (See oil check procedure.)
(8) If visual check is good, replace the belt cover and secure the fasteners.
4. Inspection of the evaporator module assembly (evaporator coil, condensate and tubing, cool air ducting) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
021.50.00.D Periodical
E.
Procedures
The following is a recommended component maintenance / inspection schedule and associated service hours: Type maintenance
Service hours
Inspection
500 - 800
Replacement
On condition
Only field serviceable high inspection or maintenance components will be addressed in the evaporator module section. A.
Evaporator coil inspection: The evaporator coil must be inspected every 500 - 800 operating hours for excessive lint and/or other contamination in the coil fins. Clean as required by using a vacuum or low pressure purge source. Bent coil fins must be combed to straighten.
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MAINTENANCE MANUAL B.
Condensate drain and tubing inspection: Verify that the evaporator condensate drain and associated tubing is not blocked or tubing linked. Clean and re-route tubing as required.
C. Cool air ducting inspection: Cool air ducting from the evaporator blower should be checked to assure that no excessive air loss is experienced due to loose connections, cracked or linked hose. Repair as required.
5. Check of the air-conditioning system function A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
021.50.00.E Seasonal
E.
Procedures During cold winter months the system should be operated for a minimum of 15 minutes every two weeks to maintain a thin oil film on the compressor drive shaft dynamic seal to prevent leakage. NOTE:
If ambient temperature is below 32° F (0° C) the pressure switch may require an electrical jumper to allow the compressor drive motor power contactor to energize and enable system to operate
WARNING:
EXTENDED OPERATION OF THE SYSTEM AT LOW AMBIENT TEMPERAFURES COULD RESULT IN MAJOR DAMAGE OF THE R 134A COMPRESSOR.
For more information see: ENVIRO SYSTEMS INCORPORATED - Document No. GM R134a GENERAL OPERATING, SERVICING AND MAINTENANCE MANUAL FOR AIRBORNE R-134a AIRCONDITIONNING SYSTEMS from October 3, 2008 or later applicable edition.
EFFECTIVITY ALL
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MAINTENANCE MANUAL
TEMPERATURE CONTROL DESCRIPTION AND OPERATION 1. General The heating and ventilation system is controlled by the: •
VENTILATION lever,
•
HEATING lever,
•
COCKPIT AIR CONTROL levers,
•
COCKPIT AIR CONDING.
The temperature of the air in the heating and ventilation system is indicated by a set of instruments.
2. List of components No.
Name
Type (Dwg.No.)
Qty
Location
1.
VENTILATION control lever
-
1
Left-hand control panel
2.
HEATING control lever
-
1
Left-hand control panel
3.
COCKPIT AIR CONTROL lever
-
2
Left-hand control panel
4.
COCKPIT AIR CONDING lever
-
2
Leg fanning outlets at the captain’s and pilot’s station
3. Operation The VENTILATION control lever opens and closes the atmospheric air intake flap. The HEATING control lever opens and closes the shut-off flap of the hot air tapped from the compressors. If it necessary to heat the passenger cabin the two control levers are opened so that the temperature in the air ducts does not exceed 80°C. As soon as the pass enger cabin temperature reaches the selected value (the recommended temperature is from 22°C to 24°C), the two control levers are adjusted to maintain the selected temperature without its further increasing. The pilot’s cockpit and the passenger cabin are ventilated with cold air if the HEATING lever is in the fully closed position and the VENTILATION lever is opened. Apart from the heating and ventilation system described above, each passenger or pilot has an air shower at his/her disposal which allows for adjusting the cold air flow rate individually. The cold air flow from the shower is available after turning the lid of shower counterclockwise and deflecting its spheric body in the desired direction. The COCKPIT AIR CONTROL levers control the flaps regulating the flow rate of the air blowing on the side windows of the cockpit and the legs of pilots. The air for fanning legs of pilot’s and the cockpit side windows is only available when at least one of the HEATING/VENTILATION control levers is in the open position. The fanning proper is activated by moving the COCKPIT AIR CONTROL lever to its open position (upward). If the right-hand COCKPIT AIR CONTROL lever is in the lower position the air is conducted to the outlets at legs of pilot’s where EFFECTIVITY ALL
021.60.00 Page: 1 Nov 1/11
MAINTENANCE MANUAL each pilot can individually adjust the air flow rate by control lever marked COCKPIT AIR CONDING. If the right-hand COCKPIT AIR CONTROL lever is in the WINDSHIELD position, the air is brought to the side windows of the pilot’s cockpit. If this lever is in the middle of its travel the air is distributed evenly between the windows and the legs of pilot’s. NOTE:
The passenger cabin can be heated faster if the cockpit air control is out of operation (lefthand COCKPIT AIR CONTROL lever is closed position i.e. down).
EFFECTIVITY ALL
021.60.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL
FIG.1
EFFECTIVITY ALL
TEMPERATURE CONTROL SYSTEM - SCHEMATIC
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INTENTIONALLY LEFT BLANK
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MAINTENANCE MANUAL
INDICATION DESCRIPTION AND OPERATION 1. General Air temperatures in the heating and ventilation system of the aircraft are indicated by means of an indication system.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Heating air temperature transmitter
LUN 5616-8
1
between frames No. 7 and 8, LH, in the air ducts
2.
Cabin air temperature transmitter
LUN 5615-8
1
between frames No. 12 and 13, in the passenger cabin
3.
Dual air temperature indicator LUN 5610.01-8
1
Left-hand control panel
4.
CENTRAL WARNING DISPLAY - AIRFRAME circuit - breaker
1
overhead panel
AZRGK 5
3. Operation The air-conditioning system temperature is monitored on the LUN 5610.01-8 dual air temperature indicator; its bottom scale shows the air temperature in the heating air ducts, the top one that in the passenger cabin. The air-conditioning system temperature indication is switched on the CENTRAL WARNING DISPLAY AIRFRAME circuit-breaker.
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MAINTENANCE MANUAL
FIG. 1
TEMPERATURE INDICATION - SCHEMATIC
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MAINTENANCE MANUAL
FIG. 2
LOCATION OF THE INDICATION INSTRUMENTS (1) LUN 5610.01-8 Dual air temperature indicator (2) LUN 5616-8 heating air temperature transmitter (3) LUN 5615-8 cabin air temperature transmitter
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021.80.00 Page: 3 Nov 1/11
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
021.80.00 Page: 4 Nov 1/11
MAINTENANCE MANUAL
LUN 5610.01-8 DUAL AIR TEMPERATURE INDICATOR DESCRIPTION AND OPERATION 1. Purpose The dual air temperature indicator is intended for measuring the air temperature in the aircraft cabin (from 0 to 40°C) and the air temperature in t he hot air ducts of the aircraft heating system (from +20 to +120°C). The indicator is linked to the following transmitters: •
LUN 5615-8 cabin air temperature transmitter
•
LUN 5616-8 heating air temperature transmitter
2. Technical data Rated feeding voltage
28 V DC
Operating feeding voltage
23.5 to 29 V DC
Current drain at 28 V
up to 130 mA
Rated measuring range •
cabin temperature indicator
0 to 40°C
•
heating duct temperature indicator
+ 20 to + 120°C
Tolerances of the indicator and of the indicator linked to the transmitters (bracketed values), °C: Tolerances, °C Air temperature indicator
Scale divisions, °C
- 40°C to + 60°C
- 40°C to + 60°C + 60°C to + 85°C
± 1.5 (± 3)
± 3 (± 4.5)
± 4 (± 5.3)
± 2 (± 4)
± 4 (± 6)
± 5 (± 7)
40 to 100
± 2 (± 3.5)
± 4 (± 5.5)
± 5 (± 6.5)
20 to 39
± 3 (± 4.5)
± 5 (± 6.5)
± 6 (± 7.5)
101 to 120
± 3 (± 5)
± 5 (± 7)
± 6 (± 8)
0 to 9 31 to 40
Heating ducts
EFFECTIVITY ALL
Operating conditions
20°C ± 5°C 10 to 30 cabin
Standard cond.
021.80.01 Page: 1 Nov 1/11
MAINTENANCE MANUAL
3. Operation The instrument is essentially an electrical bridge one arm of which is represented by a resistance temperature transmitter, the other being a fixed-resistance resistor. Two additional arms are formed by the moving system coils. The system is supplied between the transmitter and the middle common outlet of the two coils. As the current flows through the two coils, different moments acting against each other are created. However, these moments are being balanced owing to the fact that, when the two coils are rotating in a magnetic field, one of them gets to a point where the magnetic induction is higher. Consequently, the two moments are in equilibrium if the induction ratio of the coil positions corresponds to the given current ratio. Hence, the resulting setting of the moving system depends on the ratio of the currents rather than on their absolute magnitude. The reversing spiral springs influence the equilibrium of the moments only negligibly. They carry current to the coils and reset the moving system to zero.
FIG. 1
LUN 5610.01-8 DUAL AIR TEMPERATURE INDICATOR
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MAINTENANCE MANUAL
LUN 5616-8 HEATING AIR TEMPERATURE TRANSMITTER DESCRIPTION AND OPERATION 1. Purpose The heating air temperature transmitter in connection with the corresponding indicator is designed for remote measurement of the temperature of the air flowing through the aircraft ducts hot air heating system.
2. Technical data Rated feeding voltage
28 V DC
Operating feeding voltage
23.5 to 29 V DC
Permissible current load
max. 15 mA
Transmitter tolerances: Transmitter resistance, Ohm
Ohm
%
°C
- 60 - 50
70.90 73.70
± 0.55
± 0.8
±2
0.28 0.30
- 40 - 30 - 20
76.70 79.80 83.00
± 0.45
± 0.6
± 1.5
0.31 0.32 0.34
- 10 0 10 20 30
86.40 90.10 93.60 97.20 100.90
± 1.2
0.37 0.35 0.36 0.37 0.38
40 50 60 70 80 90
104.70 108.65 112.62 116.80 121.06 125.40
± 1.5
0.395 0.4 0.42 0.426 0.434 0.44
100 110 120 130 140 150
129.80 134.25 138.80 143.40 148.20 153.10
EFFECTIVITY ALL
Tolerances
Ambient temperature, 0°C
± 0.43
± 0.6
± 0.9
± 0.5
± 0.6
± 0.7
±2
Resistance change (Ohm) per 1°C
0.445 0.455 0.46 0.48 0.49
021.80.02 Page: 1 Nov 1/11
MAINTENANCE MANUAL
3. Operation The transmitter function is based on the physical property of the heat sensing element (nickel wire) which electric resistance changes with ambient air temperature in such a way that there is only one definite resistance value for each temperature value. The transmitter is connected to the bridge of the DC ratio-based measuring mechanism of the indicator which is calibrated in °C.
FIG. 1
LUN 5616-8 HEATING AIR TEMPERATURE TRANSMITTER (1) Transmitter casing; (2) Heatsensing element; (3) Plug-and socket connection
EFFECTIVITY ALL
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MAINTENANCE MANUAL
LUN 5615-8 CABIN AIR TEMPERATURE TRANSMITTER DESCRIPTION AND OPERATION 1. Purpose The temperature transmitter of cabin air in connection with the corresponding indicator is designed for remote measurement of the air temperature in the aircraft cabin.
2. Technical data Rated feeding voltage
28 V DC
Operating feeding voltage
23.5 to 29 V DC
Permissible current load
max. 10 mA
Transmitter tolerances: Ambient temperature, 0°C
Transmitter resistance, Ω (Ohm)
Tolerances Ω (Ohm)
%
°C
Resistance change Ω (Ohm) per 1°C
- 60 - 50
141.80 147.40
± 1.8
± 1.2
± 3.5
0.56 0.60
- 40 - 30 - 20
153.40 159.60 166.00
± 1.5
± 0.9
± 2.5
0.62 0.64 0.68
- 10 0
172.80 180.20
± 1.3
± 0.7
±2
0.74 0.70
+ 10 + 20 + 30
187.20 194.40 201.80
± 1.05
± 0.5
± 1.5
0.72 0.74 0.76
+ 40 + 50 + 60
209.40 217.30 225.24
± 1.4
± 0.6
±2
0.79 0.794 -
3. Operation The transmitter function is based on the physical property of the heat sensing element (nickel wire) which electric resistance changes with ambient air temperature in such a way that there is only one definite resistance value for each temperature value. The transmitter is connected to the bridge of the DC ratio-cased measuring mechanism of the indicator which is calibrated in °C.
EFFECTIVITY ALL
021.80.03 Page: 1 Nov 1/11
MAINTENANCE MANUAL
FIG. 1
LUN 5615-8 CABIN AIR TEMPERATURE TRANSMITTER (1) Insulating base; (2) Protective cover; (3) Heat sensing element; (4) Terminals a = air flow direction
EFFECTIVITY ALL
021.80.03 Page: 2 Nov 1/11
CHAPTER
22 AUTO FLIGHT
MAINTENANCE MANUAL
CHAPTER 22 AUTO FLIGHT LIST OF EFFECTIVE PAGES Chapter, Section, Subject
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Record of Temp. Revisions
Contents
Maintenance Practices
Fault Isolation
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Servicing
Removal / Installation
Adjustment / Test
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CHAPTER 22 AUTO FLIGHT RECORD OF REVISIONS Rev. No.
Chapter, Section, Subject
Numbers of Pages Rev. Pages
New. Pages
Del. Pages
Document Number
Date of Revision
MM is reissued on Nov 1/11. This contains revisions from No. 1 to No. 6 7
8
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L410UVP-E/170d
Apr 5/13
L410UVP-E/208d
Dec 10/14
L410UVP-E/212d
Apr 15/15
L410UVP-E/220d
Nov 20/15
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L410UVP-E/236d
Mar 10/17
022-RECORD OF REVISIONS Page: 2 Mar 10/17
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022-RECORD OF REVISIONS Page: 3 Nov 1/11
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MAINTENANCE MANUAL
CHAPTER 22 AUTO FLIGHT RECORD OF TEMPORARY REVISIONS Rev. No.
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022-RECORD OF TEM. REVISIONS Page: 1 Nov 1/11
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MAINTENANCE MANUAL
CHAPTER 22 AUTO FLIGHT CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
022.00.00
1 1 1 201 201
ALL
KFC 325 OR KFC 275 AUTOPILOT 022.10.00 Description and Operation General (analog version) General (EFIS version) List of components (analog version) List of components (EFIS version) Operation Fault Isolation Troubleshooting the autopilot system Servicing Check of autopilot function Removal / Installation Removal all servo capstan assemblies from the airplane, check of the slip-clutch torque setting and installation of the servo capstan assemblies back into the airplane after check Adjustment / Test Basic adjustment
1 1 1 2 3 5 6 101 101 301 301 401 401
ALL
GENERAL Description and Operation General Maintenance Practices General
CONTROL AND SIGNALIZATION OF KFC 325 OR KFC 275 AUTOPILOT Description and Operation General Control servo description
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MAINTENANCE MANUAL
GENERAL DESCRIPTION AND OPERATION 1. General The KFC 325 or KFC 275 autopilot for automatic flight control is installed on the aircraft (if installed).
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GENERAL MAINTENANCE PRACTICES 1. General A.
B.
The components removed from the aircraft for laboratory test must be inspected for: •
visible mechanical damage of the body
•
corrosion of plug-and-socket connectors, terminals, pushbuttons
•
deformation of plug-and-socket connector pins
•
deposits of dirt
•
evidence of fluid leaks
When removing a unit (a component) from the aircraft (for laboratory test or replacement), its place of installation, connector or pipe mating parts must be inspected for: •
mechanical damage (cracks) of the place of installation
•
wear of the attachment holes
•
corrosion and deformation of plug-and-socket connector pins
•
dents
•
ruptures
•
deformation of pipe connecting parts
•
damage of connector and pipe union nut threads
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KFC 325 OR KFC 275 AUTOPILOT 0B
DESCRIPTION AND OPERATION 1.a General (analog version) 4B
The KFC system of flight control is a digital triaxial flight control system having an electrical pitch trim systems which provides auto trim during autopilot operation and manual electric trim for the pilot when the autopilot is not engaged. Manipulation with aircraft control elements may be made manually (according to the data indicated on the flight director attitude gyro). During the flight control with autopilot the control elements are controlled by electronic servo-drives. The motion of the elevator, elevator trim tabs, rudder and ailerons is controlled by servo-drives. The flight control system cooperates with the following systems: •
the NAV I navigational system (a source of deflection signals from given heading of aircraft VOR, LOC course plane GS descent plane)
•
the MKR I radio markers receiver (a source of signal for switching of level sensitivity of receiver ILS)
•
the RA I radar altimeter (a source of signal for fluent sensitivity change of ILS receiver and flight indication of decision height)
•
encoding altimeter (a source of flight height barometric signals)
•
flight direction altitude gyro (left gyro horizon) - (a source of aircraft pitch and roll bank signals)
•
GK I gyromagnetic compass (a signal source of gyromagnetic heading of aircraft)
•
electrical control circuit of wing flaps (a signal source for the relay switch of elevator trim level)
•
DME I interrogator (a signal source of fluent sensitivity change of the VOR receiver applies to KFC 325)
•
SSR I transponder (a source of encoded flight height signal)
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022.10.00 Page: 1 Nov 1/11
MAINTENANCE MANUAL
1.b General (EFIS version) 5B
The KFC system of flight control is a digital triaxial flight control system, consist of the command system and autopilot system. Control of the aircraft steering systems can be (according to the displayed data on the corresponding PFD display) performed manually: a) with the intervention to the steering according to the information the PFD in the FD mode or in the synchronic steering mode after the activation with the CWS button b) using the manually electric trim or with the autopilot (according to the commands of the autopilot computer) in AP resp. AP/YD mode. During the flight control with autopilot the control elements are controlled by electronic servo-drives. The motion of the elevator, elevator trim tabs, rudder and ailerons is controlled by servo-drives. Autopilot system is possible switched over using the pressbutton (with the annunciator) to the I or II system resp. to the PFD LH or PFD RH accordance with which of the pilots is in the command. (Displayed data are corresponding changed on the PFD displays). The flight control system cooperates with the following systems: •
Power supply (power voltage 28V DC and 36V AC)
•
EFI-890R
•
-
a source of the deflection signals VOR/ILS (primary source is a dual NAV/GPS I, II systems)
-
a source of deflection signals from set track course and of deflection signals from set course
-
a source of the BARO SET data pressure setting
-
displaying AP/FD modes
-
displaying FD command information the dual (AHRS I, II) Attitude heading reference system (a source of aircraft pitch and roll bank signals and signal source of gyromagnetic heading of aircraft)
•
the dual (ADC I, II) digital Air data computer (a source of encoding flight height barometric signals)
•
dual GPS Receivers (a source of ROLL STEERING signal)
•
the MKR I radio markers receiver (a source of signal for switching of level sensitivity of receiver ILS)
•
the RADIO ALTIMETER radar altimeter (a source of signal for fluent sensitivity change of ILS receiver and flight indication of decision height)
•
electrical control circuit of wing flaps (a signal source for the relay switch of elevator trim level)
•
Dual audio - (Assurance of the warning aural tone signalization of the autopilot)
•
Flight data recorder (FDR) (Record of the active signal for the engage servo-drives of the ailerons and the elevator)
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022.10.00 Page: 2 Nov 1/11
MAINTENANCE MANUAL 2. List of components (analog version) 6B
No. 1а.
1b.
Name
Part Number
Qty
Location
065-00064-0007
1
Between the 1st and 2nd frames on the right
Adapter ROLL
065-05053-0008
1
Adapter PITCH
065-05052-0008
1
Adapter OPTION
065-05051-0008
1
Adapter LOGIC
065-05034-0008
1
065-00064-0007
1
Adapter ROLL
065-05053-0011
1
Adapter PITCH
065-05052-0011
1
Adapter OPTION
065-05051-0011
1
Adapter LOGIC
065-05034-0011
1
Flight computer (for KFC 325)
Flight computer (for KFC 275)
Type (Dwg. No.) KCP 220
KCP 220
Between the 1st and 2nd frames on the right
2.
Mode controller
KMC 321
065-00086-0000
1
Rear control panel
3.
Annunciator panel
KAP 315A
065-00063-0000
1
Cover of the control panel
4.
Altitude setter
KAS 297C
065-00089-0005
1
Left control panel
5.
Air data computer
KDC 222
065-00085-0002
1
Between the 3rd and 4th frames on the right
6.
Yaw rate gyro
KRG 331
060-00024-0000
1
Between the 1st and 2nd frames on the right
7.
Vertical gyro (if installed)
KVG 350
060-00026-0000
1
Between the 1st and 2nd frames
8.
Flight command indicator (if installed)
KCI 310 FLT
066-03020-0012
1
Left control panel
9.
Alert annunciator or Autopilot disconnect alerter
KAA 15 or LUN 2733
071-01466-0000 95028051
1
Between the 3rd and 4th frames on the right
10.
Servo-drive of ailerons
KSA 372 X
065-00056-0070
1
Between the 6th and 7th frames on the left below
11.
Servo-drive of elevator
KSA 372 X
065-00056-0070
1
On the 26th frame
12.
Servo-drive of rudder
KSA 372
065-00056-0050
1
On the 24th frame
13.
Servo-drive of elevator trim tab
KS 272 A
065-00061-0050
1
On the 23 rd frame
14.
UP-TRIM-DN switch
B501854N
200-05068-0000
1
Left steering wheel
15.
A/P DISC switch
B501853N
031-00428-0000
2
Left and right steering wheel
16.
CWS push-button
B501678N
031-00514-0000
1
Left steering wheel
17.
GA push-button
031-0514-00
-
1
Left ECL
18.
Relay
3 AMP-DPDT
-
1
Between the 6th and 7th frames on the right below
19.
Fan blower
KA 33
-
1
Between the 1st and 2nd frame
20.
AP fuse
1 CSN 354733F/1500
-
1
Between the 8th and 9th frames above
21.
AUTOPILOT 26V/400 Hz fuse
1 CSN 354733F/1500
-
1
In fuse panel
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022.10.00 Page: 3 Dec 10/14
MAINTENANCE MANUAL
No.
Name
Type (Dwg. No.)
Part Number
Qty
Location
22.
AP/FD circuit breaker
AZRGK-10
-
1
Overhead panel
23.
ELECTRIC TRIM circuit breaker
AZRGK 5
-
1
Overhead panel
24.
Diode
KZL 81/40 or KY 132/1000
-
1
Between the 6th and 7th frames on the right below
25.
Relay switch
KA 138
-
1
Between 2nd and 3rd frames, RH side
26.
Annunciator push button switch NAV 1/NAV 2
P/N 031-00535-0045
031-00535-0045
1
Cover of the control panel
27.
Annunciator NAV 1/NAV 2
LUN 2697.02-8
-
1
Cover of the control panel
28.
Sonalert
SC 628
-
2
On vertical control panel
29
Annunciator AUTOPILOT DISCONNECT (If installed)
LUN 2662.41
-
2
Cover of the instruments panels
NOTE: Items 23 to 25 are installed on aircrafts on which the Information Bulletin No. L410 UVP-E/040b has been accomplished.
The autopilot system components are identified, in addition to Model Designation, with a Part Number (P/N ….) which relates the component to a particular assembly.
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022.10.00 Page: 4 Apr 5/13
MAINTENANCE MANUAL 2. List of components (EFIS version) 7B
No. 1.
Name
Part Number
Qty
Location
065-00064-0007
1
Between the 1st and 2nd frames on the right
Adapter ROLL
065-05053-0033
1
Adapter PITCH
065-05052-0008
1
Adapter OPTION
065-05051-0008
1
Adapter LOGIC
065-05034-0008
1
Flight computer (for KFC 325)
Type (Dwg. No.) KCP 220
2
Mode controller
KMC 321
065-00086-0008
1
Rear control panel
3
Altitude selector
KAS 297C
065-00089-0005
1
Central instrument panel
4
Air data computer
KDC 222
065-00085-0002
1
Between the 3rd and 4th frames
5
Alert annunciator or Autopilot disconnect alerter
KAA 15 or LUN 2733
071-01466-0000 95028051
1
Between the 3rd and 4th frames on the right
6
Roll servo
KSA 372 X
065-00056-0070
1
Between the 6th and 7th frames on the left below
7
Pitch servo
KSA 372 X
065-00056-0070
1
On the 26th frame
8
Yaw servo
KSA 372
065-00056-0050
1
On the 24th frame
9
Servodrive of elevator trim tab
KS 272 A
065-00061-0050
1
On the 23 rd frame
10
UP-TRIM-DN switch
B501854N
200-05068-0000
1
Left steering wheel
11
A/P DISC switch
B501853N
031-00428-0000
2
Left and right steering wheel
12
CWS push-button
B501678N
031-00514-0000
2
Left and right steering wheel
13
GA push-button
031-0514-00
-
1
Left ECL
14
Relay
3 AMP-DPDT
-
1
Between the 6th and 7th frames on the right below
15
Cooling blower
KA 33
071-04037-0001
1
Between the 1st and 2nd frame
16
Circuit breaker AUTOPILOT
KLIXON 7274-2-1
-
4
Circuit breakers panel
17
AP/FD circuit breaker
AZRGK-10
-
1
Overhead panel
18
ELECTRIC TRIM circuit breaker
AZRGK 5
-
1
Overhead panel
19
Diode
KY 132/1000
-
1
Between the 6th and 7th frames on the right below
20
Annunciator push button switch AUTOPILOT TRANSFER LT/RT
58210A4B0C1F4L5N12
-
1
Central instrument panel
21
Sonalert
SC 628
038-00008-0000
1
On vertical control panel
22
Sonalert
SC 628D
038-00008-0001
1
On vertical control panel
23
Annunciator AUTOPILOT DISCONNECT (If installed)
LUN 2662.41
-
2
Cover of the instruments panels
24
Relay block
SR-263
-
2
Between frames 1 and 2
25
Interface adapter
GAD42
010-00154-01 or 010-00154-11
1
Between frames 4 and 5, right down
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022.10.00 Page: 5 Nov 20/15
MAINTENANCE MANUAL
No.
Name
Type (Dwg. No.)
Part Number
Qty
Location
26
Relay
B 073 576 N
-
5 2
Between frames 1 and 2, up Between frames 5 and 5a, down
27
Relay with diode
B 073576N/1N4007
-
1
Between frames 1 and 2, up, LH
3. Operation 8B
A.
Starting-up the flight control system (analog version) into operation is carried out by turning on the BATTERY I, II, INVERTERS 115V I, II, GK I switches, NAV I, VHF I, MKR I, RA I, INTERCOM, DME I and SSR I circuit breakers on the overhead panel. If the GYRO HORIZON on the left instrument panel is turned on, then wait until both the flags (ALTITUDE and COMPUTER) are hidden on the flight director check gyro display and turn on the ELECTRIC TRIM and AP-FD circuit breaker located on the overhead panel.
B.
Starting-up the flight control system (EFIS version) into operation is carried out by turning on the BATTERY I, II, INVERTERS 36V I, II, AHRS I, II, switches, NAV/GPS I, II, COM I, II, MKR, RADIO ALTIMETER, INTERCOM I, II, PFD I, II, DCP I, II, CHP, DCU, ADC I, II, and SSR I, II circuit breakers on the overhead panel. Then wait until the ATT flag is hidden on the Primary flight display EFI 890R and turn on the ELECTRIC TRIM and AP-FD circuit breaker located on the overhead panel.
The flight control system provides the selection of 14 operating modes securing the transmission of signals for the manual electric trim and for the autopilot. Operating modes are activated by pressing appropriate push-buttons on the mode controller of the altitude setter, on the left and right steering wheel and left ECL. The push-buttons on the mode controller and the altitude setter are used with several functions - at the first depression the mode is activated, at the second depression the function is cancelled (until automatic cancellation is used by the selection of another mode). Any operating mode that is not compatible with a newly selected mode will be automatically cancelled. The last selected operating mode has priority (it is not necessary to cancel an operating mode manually). Visual indication of a selected operating mode (with the exception of the CWS mode) is indicated by the illumination of appropriate indicator on the annunciator panel or on the mode controller.
The use of the flight control system in flight is described in the Flight Manual.
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MAINTENANCE MANUAL
FIG. 1
THE KFC 325 AND KFC 275 FLIGHT CONTROL SYSTEM WIRING (Applies to aircrafts on which Information Bulletin No.L410 UVP-E/040b has not been accomplished)
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MAINTENANCE MANUAL
FIG. 2
THE KFC 325 AND KFC 275 FLIGHT CONTROL SYSTEM WIRING (Applies to aircrafts on which Information Bulletin No.L410 UVP-E/040b has been accomplished)
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MAINTENANCE MANUAL
FIG. 3
THE KFC 325 FLIGHT CONTROL SYSTEM WIRING (EFIS VERSION)
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MAINTENANCE MANUAL
KFC 325 OR KFC 275 AUTOPILOT 1B
FAULT ISOLATION 1. Troubleshooting the autopilot system 9B
A.
Fixture, Test and Support Equipment
Fluke 8060A or V2-55 1 DC millivoltmeter or or equivalent multimeter with DC range 0 – 300 V, accuracy ±0.2% Change microohmmeter 2 NAV tester (e.g. IFR 4000 or NAV 402 AP) Pitot tester (e.g. Barfield 1811DA0A or KPU-3) KTS 162 Testing equipment Tilt table for gyro or AHRS Extension cable for KI 254 Extension cable for KCI 310 External power supply of 28V
B.
Materials
Not applicable
C. Tools
Tool kit
D. Referenced information
-
E.
Procedures (1) System turn-on (a) Analog version: Switch on the BATTERY I, II switches the INVERTERS 115 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING and GYROCOMPASS I circuit breakers on the overhead panel. Switch on the GYRO HORIZON on the left instrument panel. NOTE:
If you are not complied with the order of switching circuit breakers EL. TRIM., AP / FD will sound alarm (warning signal)
(b) EFIS version Switch on the BATTERY I, II switches and the INVERTERS 36 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING, AHRS I, II, ADC I, II, PFD I, II, DCU, DCP I, II, CHP circuit breakers on the overhead panel.
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CAUTION:
•
AN EXTERNAL POWER SUPPLY OF 28V IS TO BE USED DURING ALL GROUND TESTS.
•
THE AUTOPILOT SYSTEM TEST MAY ONLY BE STARTED AFTER THE WARNING FLAGS HEADING (ON THE LEFT HSI), ATTITUDE, COMPUTER (ON THE LEFT HORIZON) HAVE DISAPPEARED (OUT OF VIEW).
•
THE KTS 162 TESTING EQUIPMENT MAY ONLY BE USED BY PERSONS DULY QUALIFIED AND AUTHORIZED TO DO IT.
(c) Engage the autopilot. Red TRIM warning light illuminates on the annunciator panel. No other annunciators shall illuminate or audible tones be present after approximately 1 second from power application. The FDI command bars, the COMPUTER and ATTITUDE flags must be out of view. (d) Problems observed •
No TRIM light annunciation, COMPUTER flag in view. Possible cause: Missing 28 V DC power, or KCP 220 computer power supply failure. Troubleshooting procedure: Check circuit breakers and power wiring or replace the KCP 220 computer.
•
Random annunciations on annunciator panel or mode controller. Possible cause: KCP 220 computer connectors improperly installed. Troubleshooting procedure: Check connectors on KCP 220 computer for orientations (correct connector on correct plug).
(2) Pre-flight test (a) Press the TEST button on the autopilot mode controller. All annunciators on the annunciator panel and the mode controller illuminate. The TRIM annunciator flashes 4 times followed by 12 flashes of the AP annunciator. While the AP annunciator is flashing an audible warning sounds for 2 seconds. The FDI command bars must be in view, all digits and symbols on the KAS 297C altitude (vertical speed preselector) must be lit. (b) Problems observed •
Some annunciators on annunciator panel not lit. No flashing AP annunciator or tone. Autopilot will not engage. Possible cause: Incorrectly installed adapter modules in the KCP 220. Troubleshooting procedure: Inspect adapter modules for correct physical orientation on the circuit board and that the individual modules are located on their designated circuit board.
•
All pre-flight test indications correct except no flashing AP annunciator or audible warning.
EFFECTIVITY ALL
022.10.00 Page: 102 Nov 1/11
MAINTENANCE MANUAL Possible causes: No G-dump signal from KDC 222 air data computer, KCP 220 internal rate monitors failed, adapter modules incorrectly installed. Troubleshooting procedures: Replace KDC 222 air data computer or check wiring. Replace KCP 220 computer. Inspect adapter modules for correct installation. •
No flashing TRIM annunciator or incorrect number of TRIM annunciator flashes. Possible cause: Auto trim system failure. Troubleshooting procedures: Check pitch trim servo feeding circuit. Check pitch trim servo motor for proper operation. Replace the pitch trim servo.
•
TRIM annunciator flashes and audible warning sounds continuously after test. Possible causes: Manual trim failure, incorrect "servo" or "pitch" board adapter module installed. Troubleshooting procedure: Check for correct installation of the correct adapter modules.
•
No audible warning during test. Autopilot will not engage. Possible cause: Vertical gyro valid signal absent. Troubleshooting procedure: Check for presence of VG or altitude flag, or check VG valid wiring to KCP 220 computer.
(3) Manual electric trip operation (a) Pressing the UP/DOWN rocker switch on the mode controller in the UP/DOWN direction causes pitch trimming action in the respective direction. It will also cause the autopilot to disengage (if engaged) and previously used modes will remain annunciated. (b) Problems observed •
Pitch trim servo clutch will not engage or servo will not drive. No TRIM light annunciation. Possible cause: Loss of clutch engage and drive signals. Troubleshooting procedure: Check wiring between rocker switch on mode controller and KCP 220 computer.
•
TRIM annunciator illuminates. No input from trim switch. Possible cause: Trim system power failure. Troubleshooting procedure: Check pitch trim circuit breaker and power wiring.
•
TRIM annunciator illuminates whenever trim switches are activated. Possible causes: Loss of clutch engage signal or servo movement in incorrect direction.
EFFECTIVITY ALL
022.10.00 Page: 103 Nov 1/11
MAINTENANCE MANUAL Troubleshooting procedure: Check clutch engage wiring or trim drive and feedback wiring. (4) AP with FD mode (a) Pressing the AP button on the mode controller after successful preflight test causes the autopilot to engage with flight director mode. All servo clutches will engage, the flight director command bars will come into view, and the autopilot will maintain whatever pitch attitude was present at engagement while commanding a wings level attitude in roll. (b) Annunciations FD, AP annunciators lit, command bars in view with up (down and left) right commands corresponding to inputs necessary to maintain wings level and a selected pitch attitude. (c) Problems observed •
Autopilot will engage but will not maintain wings level or synchronize to a given pitch attitude. Possible cause: Loss of pitch and roll altitude signals. Troubleshooting procedure: Check vertical gyro for proper output and wiring to KCP 220 computer.
•
Autopilot will not maintain wings level attitude. One wing slightly lower than the other. Possible cause: Vertical gyro level position does not coincide exactly with aircraft’s wings level attitude. Troubleshooting procedure: Adjust ROLL NULL potentiometer in mode controller.
•
Autopilot engagement will cause short-term oscillations in one or any number of the pitch, roll and gyro axes. Possible cause: No servo feedback to KCP 220 computer. Troubleshooting procedure: Check servo feedback wiring between applicable servo and the KCP 220 computer.
(5) Heading mode (a) Press the HDG button on the mode controller. The autopilot will engage heading mode and respond to inputs from the heading bug located in the HSI. (b) Annunciations FD and HDG annunciators lit, command bars in view with left/right roll commands corresponding to heading bug inputs. Attitude or COMPASS flag out of view. (c) Problems observed •
Autopilot will not engage HDG mode Possible cause: Loss of compass or directional gyro valid signal. Troubleshooting procedure: Ensure COMPASS/HEADING flag is out of view, or check DG valid wiring to KCP 220 computer.
EFFECTIVITY ALL
022.10.00 Page: 104 Nov 1/11
MAINTENANCE MANUAL •
Autopilot will not respond to heading bug inputs. Maintains a wings level attitude. Possible cause: Loss of heading datum signal from HSI. Troubleshooting procedures: Check wiring between HSI and KCP 220. Also check HSI for heading datum output.
•
Autopilot will not maintain a selected heading. Turns aircraft off in a direction opposite of the selected heading. Possible cause: Polarity of heading datum signal incorrect (DC heading datum indicators only). Troubleshooting procedure: Check polarity of heading datum connections and check indicator for correct output.
(6) Altitude mode (a) Pressing the ALT button on the mode controller will cause the autopilot to engage in altitude hold mode and maintain the pressure altitude that was present at the moment of engagement. (b) Problems observed •
Autopilot will not maintain selected altitude. Possible cause: Loss of altitude information from the KDC 222 air data computer or loss of static pressure to KDC 222. Troubleshooting procedure: Check 4.75 kHz line between KDC 222 air data computer and KCP 220 AP computer. Check static system connection for proper installation at the KDC 222.
(7) NAV/APR mode (a) Press the NAV/APR button on the mode controller. The autopilot will engage in a NAV/APR ARM mode. When the proper course deviation and rate of closure conditions are met, the autopilot will engage in a NAV/APR CPLD mode and command the aircraft towards the desired VOR/ILS navigation station. Upend receiving a valid GS signal and having the glideslope deviation pointer cross the center deviation mark, the autopilot will engage the GS mode and provide pilot steering commands to the runway. (b) Annunciations FD, NAV ARM, NAV, APR, ARM, APR, GS annunciators lit, command bars in view with left/light commands corresponding to course deviation and course datum inputs. Up/down commands corresponding to glideslope deviation inputs. (c) Problems observed •
Autopilot will not track a centered deviation indication. Possible cause: Loss of course datum from the NAV indicator.
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MAINTENANCE MANUAL Troubleshooting procedure: Check course datum lines between the NAV indicator and the KCP 220 computer. Also check the NAV indicator for the correctly scaled output. •
Autopilot will not engage into a NAV/APR mode from a NAV/APR ARM mode. Possible cause: Loss of course deviation signals to the KCP 220 computer. Troubleshooting procedure: Check course deviation lines between the NAV receiver and the KCP 220. If deviation voltage is present then the KCP 220 computer has a failure.
•
Autopilot will not engage into an APR ARM mode when an ILS frequency is selected on the NAV receiver. Possible cause: Loss of ILS ENERGIZE signal from the NAV receiver. Troubleshooting procedure: Check ILS energize line between the NAV receiver and the KCP 220 computer.
(8) IAS mode (a) Press the IAS button on the mode controller. The autopilot will engage in indicated airspeed hold mode and command the aircraft to maintain the indicated airspeed current at the moment of mode engagement. Increasing/decreasing deviations from the selected airspeed can be made with respective down/up inputs from the VERT TRIM switch on the mode controller. (b) Annunciations FD and IAS annunciators lit, command bars in view with up/down commands in pitch attitude required to maintain a selected airspeed. (c) Problems observed •
Autopilot will not maintain a selected airspeed. Possible cause: Loss of IAS signal from the KDC 222 air data computer or loss of pressure in the pitot-static system. Troubleshooting procedure: Check IAS input line between the KDC 222 and the KCP 220 computer. Check pitot-static system connection at the KDC 222 for proper installation.
(9) VS mode (a) Press the VS button on the KAS 297C preselector. The autopilot will engage in a vertical speed mode and command the aircraft to maintain a given vertical speed as selected by the rotary knob on the KAS 297 C. Synchronization to an established vertical speed may be also accomplished by pressing and then releasing the CWS with on the control wheel. (b) Annunciations FD annunciator on the mode controller, VS annunciator and 3 to 4 digit number (indicating EFFECTIVITY ALL
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MAINTENANCE MANUAL selected vertical speed) in the KAS 297C display lit with an upward/downward pointing caret to indicate direction. Command bars in view with up/down indications corresponding with inputs needed to maintain a given vertical speed. (c) Problems observed A.
Autopilot will not command a selected vertical speed from the KAS 297C or by synchronization with the CWS switch. Possible cause: Loss of altitude information from the KDC 222 air data computer. Troubleshooting procedure: Check 4.75 kHz oscillator line between the KDC 222 and the KAS 297C. Check pitot-static system connection at KDC 222 for proper installation.
(10) Alt PRESELECT mode (a) Select a predetermined altitude by rotating the knob on the KAS 297C unit until the derived altitude appears in the display. Pressing the ALT button on the KAS 297 C will cause the autopilot to engage in an ALT ARM mode. The aircraft is then placed in ascent/descent configuration to intercept the selected altitude. Upon mearing the selected altitude the autopilot will change mode to altitude capture (ALT CAP) and begin to command the aircraft to level out at the selected altitude. Upon reaching the altitude, the autopilot will change mode to altitude hold (ALT HOLD) and command the aircraft to maintain that altitude. (b) Annunciations FD and ALT annunciator on the mode controller, ALT ARM, ALT CAP annunciators and 3 to 5 digit number (for preselected altitude) in the KAS 297C display lit. Command bars in view with up/down commands. (c) Problem observed A.
ALT ARM mode will not engage. KAS 297C display is dashed. Possible cause: Loss of serial communication between the KAS 297C and the KCP 220 computer, or loss of the altitude valid signal from the interconnecting encoding altimeter. Troubleshooting procedure: Check data, clock, and address communication lines between the KAS 297C and the KCP 220. Check the line between the encoding altimeter and the KAS 297C.
•
Autopilot will command the aircraft to same altitude other than the selected one. Erratic pitch axis activity when ALT ARM mode is selected. Possible cause: Loss of one or more encoded altitude signals from the inconnecting altimeter.
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MAINTENANCE MANUAL Troubleshooting procedure: Check all altitude encoding lines between the encoding altimeter and the KAS 297C. Check the altimeter for proper encoded altitude output. •
Autopilot will command the aircraft to an altitude within 30 metres of that selected. Possible cause: Loss of calibration between the KAS 297C and the interconnecting altimeter Troubleshooting procedure: Re-establish calibration between the KAS 297C and the altimeter (as instructed in para (12)).
(11) GA mode (a) Press the GA button on the LH power control lever to engage the flight director into a go-around mode. The command bars will then command a selected pitch up angle for the aircraft to maintain during a go-around procedure after a missed approach. Selection of this mode will disconnect the previously engaged autopilot. (b) Annunciations FD and GA annunciator lit. Command bars in view with up/down commands necessary to maintain the aircraft at the selected pitch up attitude. (c) Problems observed •
GA mode will not engage Possible cause: Loss of ground signal from the GA switch to the mode controller. Troubleshooting procedure: Check the GA switch for proper operation and the line between the switch and the mode controller.
•
GA mode causes command bars to command a pitch up angle other than the one specified in the appropriate installation manual. Possible cause: Incorrect resistor strap on option board adapter module. Troubleshooting procedure: Check option adapter module for correct part number and/or proper installation.
(12) Altitude calibration The calibration is made on the KAS 297C altitude/vertical speed selector. During climb, the KAS 297C receives altitude information from the encoding altimeter. To achieve high accuracy, the calibration is performed at several altitudes. The calibration procedure can be conducted either on the ground, using a tester to simulate altitude, on in flight. (a) Calibration procedure •
Set standard pressure (1013.23 mb) on the encoding altimeter.
•
Press both the VS ENG and ALT ARM buttons on the KAS 297C and hold them for more than 5 seconds. The unit will display a digital altitude information supplied by the encoding altimeter. The unit is to be calibrated at an altitude of 0, 5,000, 10,000 and 15,000 feet.
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MAINTENANCE MANUAL •
When the encoding altimeter indicates accurately the calibrated altitude, momentarily press VS ENG button on the KAS 297C. The error difference from the actual altitude is now stored for operational use.
NOTE:
Errors greater than 125 feet can not be corrected.
(b) To exit the calibration mode first press the ALT ARM button, then press the VS ENG button and release both. CAUTION:
IT THE CALIBRATION PROCEDURE IS ACCOMPLISHED, BUTTONS MUST NOT BE OPERATED IN THE CALIBRATION MODE. OTHERWISE, DISTORTION OF CALIBRATION AND INCREASE OF AUTOPILOT ERROR WOULD OCCUR.
(13) Switched the autopilot off (a) Analog version: Switch off the BATTERY I, II switches the INVERTERS 115 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING and GYROCOMPASS I circuit breakers on the overhead panel. Switch off the GYRO HORIZON on the left instrument panel. (b) EFIS version Switch off the BATTERY I, II switches and the INVERTERS 36 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING, AHRS I, II, ADC I, II, PFD I, II, DCU, DCP I, II, CHP circuit breakers on the overhead panel.
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KFC 325 OR KFC 275 AUTOPILOT 2B
SERVICING 1. Check of autopilot function 10B
A.
Fixture, Test and Support Equipment
NAV tester (e.g. IFR 4000 or NAV 402 AP) Pitot tester (e.g. Barfield 1811DA0A or KPU-3) External power supply of 28V
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Switching autopilot on (a) Analog version: Switch on the BATTERY I, II switches the INVERTERS 115 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING and GYROCOMPASS I circuit breakers on the overhead panel. Switch on the GYRO HORIZON on the left instrument panel. NOTE:
If you are not complied with the order of switching circuit breakers EL. TRIM., AP / FD will sound alarm (warning signal)
(b) EFIS version Switch on the BATTERY I, II switches and the INVERTERS 36 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING, AHRS I, II, ADC I, II, PFD I, II, DCU, DCP I, II, CHP circuit breakers on the overhead panel. (2) Ground tests of the autopilot installed in the aircraft CAUTION:
•
AN EXTERNAL POWER SUPPLY OF 28V IS TO BE USED DURING ALL GROUND TESTS.
•
THE AUTOPILOT SYSTEM TEST MAY ONLY BE STARTED AFTER THE WARNING FLAGS HEADING (ON THE LEFT HSI), ATTITUDE, COMPUTER (ON THE LEFT HORIZON) HAVE DISAPPEARED (OUT OF VIEW).
NOTE:
Checking of autopilot function is performed when an autopilot failure occurs, and after servo clutch torque adjustment. Checks as per para (3), (4), (4-b), (4-k), (4-l), (6-a), (7-a) and (8-e) are recommended at the beginning of each flying day.
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MAINTENANCE MANUAL (a) Before starting the work: •
Inspect visually all the installed units of the system.
•
Check for the condition and connection of wiring and connectors.
•
Check for intactness of the seals on the individual units.
•
Check the supply voltage of the 28.5 V and 26 V 400 Hz on the voltmeters on the instrument panel
•
Inspect the free motion of the steering units (areas)
(3) PFT - Preflight test. (a) Press the TEST button on the autopilot mode controller. All annunciators should illuminate, with the TRIM annunciator flashing four (4) times. Then the annunciators extinguish and the test concludes with the AP annunciator flashing twelve (12) times accompanied by an aural tone for two (2) seconds. CAUTION:
AFTER THE SUCCESSFUL COMPLETION OF THE SELF TEST NO ANNUNCIATOR ON THE AUTOPILOT MODE CONTROLLER MUST BE LIT.
(4) Manual electric pitch trim test (a) Push the left side of the split TRIM (MET) switch to the fore and aft positions while leaving the right side untouched. The pitch trim wheel should not spontaneously move. Rotate the trim wheel manually against the engaged clutch to check the pilot’s trim overpower capability. (b) Press the right side of the split TRIM (MET) switch to the fore and aft positions while leaving the left side untouched. Again, the trim wheel should not spontaneously move. Normal trim force should be required to move the trim wheel manually. (c) Press and hold the AP DISC switch. The manual electric trim must not run (nose up or nose down) when both sides of the split TRIM (MET) switch are pressed simultaneously. (d) Switch off the AP/FD circuit breaker on the overhead panel and press the TRIM (MET) switch on the control wheel. The pitch trim must be inactive. Switch on the AP/FD circuit breaker and press the TEST button on the autopilot mode controller. (e) Switch off the ELECTRIC TRIM circuit breaker on the overhead panel. The manual electric pitch trim must be inactive. Switch on the ELECTRIC TRIM circuit breaker and push the TEST button on the autopilot mode controller. (f)
Press both sides of the MET split switch on the control wheel (down and up). The pitch trim must run in the correct direction.
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MAINTENANCE MANUAL (g) With the aircraft at rest (at an airspeed of 0 km/hr) move the trim wheel until it comes to a stop. Press the TRIM (MET) button on the control wheel and hold it until the trim wheel stops turning. Verify that the trim operation time is within 27s ± 3 s. Repeat the same procedure moving the trim controls in the opposite direction. (h) Perform the check as per para (4-g) above at a simulated airspeed of 330 km/hr (178 kts) (over the RH Pitot hub). (i)
The trim operation time must be within 40s ± 3s. Repeat the check with the trim running in the opposite direction. After ending, set the neutral position of the pitch trim tab.
(j)
Press the CWS button. Command bars on the FDI must come into view. FD is illuminated.
(k) Press the AP pushbutton on the autopilot control panel, AP and FD annunciators are illuminated. (l)
Press and hold the CWS buttons and verify that the ROLL, PITCH and PITCH TRIM servo clutches disengage.
(m) The YAW servo clutch does not disengage. Unloose the CWS buttons (n) With the autopilot engaged, apply force to the controls to determine if the servos can be overpowered in all axes. (5) Autopilot disconnection check. (a) Check the autopilot disconnection by pressing the both TRIM (MET) switches - emit the warning aural tone. AP annunciator (on the autopilot control panel) is blinking and extinguish. (b) Verify that the ROLL, PITCH and PITCH TRIM servo clutches are disengage. The YAW servo clutch does not disengage. (c) Press the AP button on the autopilot control panel, switch off the AP/FD circuit breaker on the overhead panel. Verify that the ROLL, PITCH and PITCH TRIM servo clutches are disengage and that the YAW servo is disengage. (d) Switch on the AP/FD circuit breaker on the overhead panel, perform the PFT - Preflight test, and press the AP pushbutton on the autopilot control panel. Press the AP DISCONECT pushbutton on the left steering wheel. AP annunciator is blinking and goes the warning aural tone. Repeat the test with the AP DISCONECT pushbutton on the right steering wheel. CAUTION:
ALL FOLLOWING TESTS (FD / AP CHECK, NAV I, NAV II / GPS) ARE CARRY ON AT FIRST WITH ACTIVATED FD (CLUTCHES DISENGAGED) AT SECOND WITH ACTIVATED AP (ON THE KMC 321).
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MAINTENANCE MANUAL (6) FD / AP check (FDI commands). NOTE:
Verify that the landing flaps system is in the zero position (zero indication)
(a) Set the steering column to the slightly pull on position. Switch on the AP on the autopilot control panel. Press the UP/DOWN toggle switch on the autopilot control panel. CAUTION:
THE FDI COMMAND BARS (LEFT HORIZON) MUST RUN IN THE CORRECT DIRECTION (UP AND DOWN) AND SAME SO MUST RUN THE STEERING COLUMNS
(b) Reduce the motion of the steering column, repeated the test and verify that the automatic electric trim (AUTOTRIM) carry out in same direction as command after 3 sec delay after handhold of the steering column. NOTE:
Abort the test can be with using AP DISCONNECT pushbutton on the left or right steering wheel.
(c) Set the initial position for tests the HDG, NAV, APR and GPS modes. Set the left HSI so that the over switch the SLAVE / FREE switch to the FREE position and with the CCW-CW button set up course i.e. 35°. a CRS knobs on the course 35° to the opposite the fixed white line
(d) Set the HDG (LUBBER LINE).
(7) HDG DATUM course mode check. (a) Press the FD and at good gyro compass function (i.e. Compass flags out of view) press the HDG button on the autopilot control panel. (b) Turn the HDG
knob (course selector) to the right and left +/- 30°from the fixed white
line (LUBBER LINE) (on the left HSI). CAUTION:
MUST BE VALID FOLLOWING CORRELATIONS: CRS TO RIGHT - FDI BANKING TO RIGHT CRS TO LEFT - FDI BANKING TO LEFT
(8) NAV mode check-NAV RIGHT-LEFT, CRS DATUM. (a) Set the initial position for tests the HDG, NAV, APR and GPS modes. Set the left HSI so that the over switch the SLAVE / FREE switch to the FREE position and with the CCW-CW button set up course i.e. 35°. (b) Set the HDG
a CRS knobs on the course 35° to the opposite the fixed white line
(LUBBER LINE). (c) Set the Nav tester (e.g. IFR 4000) and NAV I (NAV II) receiver on the 108.00 MHz.
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MAINTENANCE MANUAL (d) Set the VOR BRG 49° TO on the Nav tester (e.g. IFR 4000), thus evocate full CDI deviation to right. (e) Press the FD, HDG, NAV pushbuttons on the autopilot control panel and FD, HDG, NAV ARM annunciators will be illuminated on the control and annunciator panel (if installed). Reduce the CDI deviation on the value BRG TO 39° by means the NAV tester. (f)
After slowly reduce the value on the 35° (34°). The ARM and HDG annunciators extinguished while passing through the center of the CDI. CAUTION:
AT TURNING THE CRS +/- 10°FROM THE FIXED WHITE LINE (LUBBER LINE) MUST THE FDI TRACED THE BAR MOTION AS FOLLOWS: (CRS TO RIGHT - FDI BANKING TO RIGHT CRS TO LEFT - FDI BANKING TO LEFT).
(g) Set to zero the CDI deviation when is switch off NAV tester. (h) Turn the CRS knob on the HSI ± 30° from the fixed white line (LUBBER LINE). CAUTION:
FDI COMMAND BARS MUST DEVIATE ACCORDING TO THE CHANGE OF THE CRS. CRS - TO RIGHT FROM THE FIXED WHITE LINE - FDI - BANKING TO RIGHT CRS - TO LEFT FROM THE FIXED WHITE LINE - FDI - BANKING TO LEFT CRS - 0 - FDI - 0.
(i)
Switch on again NAV tester (e.g. IFR 4000).
(9) APR, GS and BC modes check (NAV LEFT - RIGHT, GS UP - DN, GS FLAG, LOC ENG). (a) Set the initial position for tests the HDG, NAV, APR and GPS modes. Set the left HSI so that the over switch the SLAVE / FREE switch to the FREE position and with the CCW-CW button set up course i.e. 35°. (b) Set the NAV I (NAV II) receiver at the 108.10 MHz LOC frequency. (c) Set the G/S XTL-HI on the NAV tester (e.g. IFR 4000). 334.70 MHz (108.10 MHz LOC) frequency must be displayed on the display. (d) Switch to function the PEAK LOCK overswitch (ganged function LOC-GS). (e) Switch DDM LOC 0.155 to right and DDM GS 0.175 up. (f)
Switch on the FD, HDG, APR on the autopilot control panel, reduce the value by means DDM LOC to the zero CDI Deviation.
(g) FD, HDG, APR ARM annunciators are illuminated on the control and annunciator panel.
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MAINTENANCE MANUAL (h) The ARM and HDG annunciators extinguished while passing through the center of the CDI. CAUTION:
CHANGE OF THE DDM LOC DEVIATION ON THE NAV TESTER (E. G. IFR 4000) MUST THE FDI TRACED THE BAR MOTION AS FOLLOWS: CDI TO RIGHT - FDI BANKING TO RIGHT CDI TO LEFT - FDI BANKING TO LEFT
(i)
Set the zero the CDI by means DDM LOC and reduce the deviation of the GS indicator by means DDM G/S on the NAV Tester to the zero. NOTE:
After reach of the zero deviation of the GS indicator, GS annunciator is illuminated on the annunciator panel and simultaneously FDI decline and returned to the zero position (return to the tracing deviation of the GS indicator)
CAUTION:
CHANGE OF THE CDI DEVIATION BY MEANS DDM G/S ON THE NAV TESTER (E. G. IFR 4000) MUST THE FDI TRACED MOTION OF THE INDICATOR AS FOLLOWS: GS UP - FDI UP; GS DOWN - FDI DOWN; GS 0 - FDI 0.
NOTE:
In case repeatedly check, repeated the procedure from the para (d).
(10) CRS check in APR mode. (a) Set the initial position for tests the HDG, NAV, APR. Set the left HSI so that the over switch the SLAVE / FREE switch to the FREE position and with the CCW-CW button set up course i.e. 35°. a CRS knobs on the course 35° to the opposite the fixed white line
(b) Set the HDG (LUBBER LINE).
(c) Switch on the FD, HDG, APR on the autopilot control panel. (d) Set the zero of the CDI DDM LOC and turn the CRS on the left HSI ± 30° from the fixed white line (LUBBER LINE). CAUTION:
MUST BE VALID FOLLOWING CORRELATIONS: CRS TO RIGHT - FDI BANKING TO RIGHT CRS TO LEFT - FDI BANKING TO LEFT
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MAINTENANCE MANUAL (11) BC check (Back course) in APR mode. (a) Set the initial position for tests the HDG, NAV, APR. Set the left HSI so that the over switch the SLAVE / FREE switch to the FREE position and with the CCW-CW button set up course i.e. 35°. (b) Set the HDG
a CRS knobs on the course 35° to the opposite the fixed white line
(LUBBER LINE). (c) Switch on the FD, HDG, APR and BC on the autopilot control panel. (d) Set the zero of the CDI DDM LOC, press BC and turn the CRS on the left HSI ± 30° from the fixed white line (LUBBER LINE). CAUTION:
MUST BE VALID FOLLOWING CORRELATIONS: CRS TO RIGHT - FDI BANKING TO LEFT CRS TO LEFT - FDI BANKING TO RIGHT CRS - 0 - FDI - 0 CHANGE OF THE DDM LOC DEVIATION ON THE NAV TESTER (E. G. IFR 4000) MUST THE FDI TRACING THE BAR MOTION AS FOLLOWS: CDI TO RIGHT - FDI BANKING TO LEFT CDI TO LEFT - FDI BANKING TO RIGHT CDI - 0 - FDI BANKING - 0
(12) Switched the autopilot off (a) Analog version: Switch off the BATTERY I, II switches the INVERTERS 115 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING and GYROCOMPASS I circuit breakers on the overhead panel. Switch off the GYRO HORIZON on the left instrument panel. (b) EFIS version Switch off the BATTERY I, II switches and the INVERTERS 36 V I, II, EL. TRIM, AP / FD, INTERCOM I, II, PA, SSR I, RADIOALTIMETER I, FLAPS, LIGHTING, AHRS I, II, ADC I, II, PFD I, II, DCU, DCP I, II, CHP circuit breakers on the overhead panel.
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MAINTENANCE MANUAL KFC 325 OR KFC 275 AUTOPILOT 3B
REMOVAL / INSTALLATION 1. Removal all servo capstan assemblies from the airplane, check of the slip-clutch torque 1B
setting and installation of the servo capstan assemblies back into the airplane after check A.
Fixture, Test and Support Equipment
B598975N (2 pc) Blocking of the control cables, B596331N Servicing platform , B971051N (L 410.9712) Force-measuring set
B.
Materials
Binding (securing) wire
C. Tools
7/64 inch Hex socket driver (spanner) ¼’’ Ratchet 100mm ¼’’ Extension 150mm ¼’’ Extension 7/16 inch Female spanner
D. Referenced information
022.10.00.A Periodical
E.
Procedures (1) Remove the LH pilot’s seat (refer to the chapter 25). (2) Remove covers of the LH cockpit floor panels. (3) Release the quick-release fasteners of the cover on bulkhead No. 21. (4) Locate a B596331N servicing platform in the bay behind bulkhead No. 21. (5) Remove KS 272A elevator trim tab servo installed in the bay behind bulkhead No. 21. (a) Set the elevator trim tab control wheel to the middle position and secure it against moving with blocking control cables (9) – refer to the fig. 401. CAUTION: IT IS VERY IMPORTANT TO THE SECURE THE CONTROL CABLES AGAINST MOVING. (b) Remove the sprocket protection cover with help the cross screwdriver. (c) Disconnect the bonding strip at the turnbuckle (3) - refer to the fig. 401. (d) Remove the binding wire securing the turnbuckle (3) and unscrew them. (e) Remove the cable (2) from the sprockets (4) and (6). (f)
Remove the retaining ring (7) from the shaft of the servo (1).
(g) Remove the KS 272A servo. EFFECTIVITY ALL
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MAINTENANCE MANUAL
FIG. 401
KS 272A ELEVATOR TRIM TAB SERVO (PITCH TRIM) (1) KS 272A elevator trim tab servo; (2) Cable with chain; (3) Turnbuckle; (4) Sprocket; (5) Drum; (6) Servo sprocket; (7) Retaining ring; (8) Chain coupler, (9) Blocking of the control cables
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MAINTENANCE MANUAL (6) Removal of the KSA 372X aileron servo (ROLL) (a) Disconnect the plug (socket-plug connection) of the ROLL servo. (b) Remove the six screws and dust cover (pos. No. 2 – refer to the fig. 402) from the servo capstan. Lift the slip clutch assembly of the capstan pulley. (c) Remove the 4 pcs screws and washers (pos. No. 36 and 37). (d) Remove the KSA 372X aileron servo. Mark the original position of the servo clutch and servo, before the disassembly (for assurance of correct re-installation). Wash the connecting material with petrol and prepare it for further usage.
FIG. 402
KSA 372X AILERON SERVO (ROLL) For description of the figure, see the Illustrated Parts Catalogue (IPC) of the airplane
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MAINTENANCE MANUAL (7) Removal of the KSA 372X elevator servo (PITCH) (a) Disconnect the plug (socket-plug connection) of the PITCH servo. (b) Remove the six screws and dust cover (pos. No. 2 – refer to the fig. 403) from the servo capstan. Lift the slip clutch assembly of the capstan pulley. (c) Remove the 4 pcs screws and washers (pos. No. 7 and 8). (d) Remove the KSA 372X elevator servo. Mark the original position of the servo clutch and servo, before the disassembly (for assurance of correct re-installation). Wash the connecting material with petrol and prepare it for further usage.
FIG. 403
KSA 372X ELEVATOR SERVO (PITCH) For description of the figure, see the Illustrated Parts Catalogue (IPC) of the airplane
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MAINTENANCE MANUAL (8) Removal of the KSA 372 rudder servo (YAW) (a) Disconnect the plug (socket-plug connection) of YAW servo. (b) Remove the six screws and dust cover (pos. No. 40 – refer to the fig. 404) from the servo capstan. Lift the slip clutch assembly of the capstan pulley. (c) Remove the 4 pcs screws and washers (pos. No. 27 and 28). (d) Remove the KSA 372 rudder servo. Mark the original position of the servo clutch and servo, before the disassembly (for assurance of correct re-installation). Wash the connecting material with petrol and prepare it for further usage.
FIG. 404
KSA 372 RUDDER SERVO For description of the figure, see the Illustrated Parts Catalogue (IPC) of the airplane
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MAINTENANCE MANUAL (9) Check the ROLL, PITCH, YAW, PITCH TRIM slip-clutch torque setting. (a) The servo mount part number and setting required for each axis of the airplane is mentioned in section 022.10.01. (b) Sending of the servos with the slip clutch assembly for torque check and setting procedure to an authorized BENDIX KING / HONEYWELL center is recommended. CAUTION:
ONLY DULY AUTHORIZED SERVICE CENTERS AND/OR PERSONS MAY CARRY OUT ANY ADJUSTMENT AND SETTING ON THE AUTOPILOT SERVOS AND SERVO TORQUE CLUTCHES.
(c) Verify that the record the slip clutches torque reading, airplane type, and date on the decal affixed to the all slip clutches body. (10) Install the KS 272A elevator trim tab servo (PITCH TRIM) (a) Fit the sprocket (6) see Fig. 401 with the clutch and gear to the shaft of the servo, and secure with the retaining ring (7). (b) Install the servo reeve the cable and chain through the sprockets as shown on fig. 401. (c) Check undisturbed and right orientation chain couplers (8). The couplers have to be installed so that fuse point from the second cable at the control circuit. (d) Connect the cable (2) with the elevator trim tab control cable by means of a turnbuckle, and adjust the cable tension according to the table 401. CAUTION:
THREADS OF THE CABLE AND CONNECTORS MUST BE FULLY HIDDEN IN THE TURNBUCKLE.
(e) Install the landing strip in parallel with the turnbuckle. (f)
Secure both the turnbuckle and the bonding strip by means of a binding wire.
(g) Mount the sprocket protection cover with help the cross screwdriver. (h) Check that the elevator trim tab is in the neutral position and release the elevator trim tab control wheel (cables) - remove the blocking of the control cables. (11) Installation of the KSA 372X aileron servo (ROLL) (a) Install the KSA 372X aileron servo and secure with the 4pcs screws and washers (pos. No. 36 and 37 - refer to the fig. 402) (b) Install clutch assembly in capstan and secure the dust cover (pos. No. 2 – refer to the fig. 402) with the six screws. (c) Connect the plug (socket-plug connection) of the ROLL servo.
EFFECTIVITY ALL
022.10.00 Page: 406 Mar 10/17
MAINTENANCE MANUAL (12) Install KSA 372X elevator servo (PITCH) (a) Install the KSA 372X elevator servo and secure with the 4pcs screws and washers (pos. No. 7 and 8 - refer to the fig. 403) (b) Install clutch assembly in capstan and secure the dust cover (pos. No. 2 – refer to the fig. 403) with the six screws. (c) Connect the plug (socket-plug connection) of the PITCH servo. (13) Install KSA 372 rudder servo (YAW) (a) Install the KSA 372 rudder servo and secure with the 4pcs screws and washers (pos. No. 27 and 28 - refer to the fig. 404) (b) Install clutch assembly in capstan and secure the dust cover (pos. No. 40 – refer to the fig. 404) with the six screws. (c) Connect the plug (socket-plug connection) of the YAW servo. (14) Check and adjustment of servos cable tension. (a) Check for tension of the cables with the B971051N (L 410.9712) force-measuring set. The values found must meet those given in table 401. Should these values differ, adjust the cable tension by means of turnbuckles of respective control cable. After adjustment, lock the turnbuckles by means of 0.8 mm dia securing wire. NOTE:
Control cables diameters of the rudder, elevator, elevator trim tab and aileron servo(s) ..... 2 mm Force of tension of the control cables Control cable (lb)
(N)
(kp)
PITCH
33 ± 3
147 ± 13
14.7 ± 1.3
ROLL
33 ± 3
147 ± 13
14.7 ± 1.3
YAW
35 ± 3
156 ± 13
15.6 ± 1.3
50.7 ± 5
222 ± 22
22.6 ± 2.2
PITCH TRIM
TAB. 401
VALUES OF SERVO CABLE TENSION.
(15) Work close up (a) Remove the B596331N servicing platform from the bay behind the bulkhead No. 21. (b) Fix the cover to bulkhead No. 21 by means of quick release fasteners. (c) Reinstall the covers of the LH cockpit floor panel. (d) Reinstall the RH pilot’s seat. (see chapter 25).
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022.10.00 Page: 407 Mar 10/17
MAINTENANCE MANUAL (e) Check for proper function of the autopilot according to the work procedure no. 1 -Check of autopilot function - mentioned in this section (section SERVICING - from the page 301)
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022.10.00 Page: 408 Mar 10/17
MAINTENANCE MANUAL KFC 325 OR KFC 275 AUTOPILOT ADJUSTMENT / TEST 1. Basic adjustment 1B
A.
Fixture, Test and Support Equipment
Ground Power Unit (e.g. GPU-600); Digital Multimeter (e.g. EXTECH MG302 or equivalent); Air Data Tester (e.g. BARFIELD 1811D A0A); B598984N Connection set of Air Data Tester; IDEAL & AEROSMITH 1310-1-L-90 Manual tilt and turn table (or equivalent) and B599000N Adapter plate kit; KTS 162 Tester (use only if the airplane not equipped with a measure clamps on the connectors of the KCP220 – refer to the fig. 503); 112-620-37436 Extender cable (when the PITCH/ROLL signal source is KVG 350); B598959N Extender cable for AHRS (if installed) or suitable digital level (protractor)
B.
Materials
Not applicable
C. Tools
Necessary tools from the tool kit
D. Referenced information
-
E.
Procedures In the event that a KFC 275/325 component (i.e. KCP 220, KMC 321, KI 254 or KAS 297C) requires removal for maintenance or replacement or troubleshooting, alignment or adjustments may be required. NOTE 1: All autopilot components must be replaced with the exact same unit part number. NOTE 2: The adjustment procedure can be accomplished by a trained and properly certificated Aircraft Maintenance Engineer. (1) Flight computer / attitude gyro alignment procedure: (a) Place the airplane to the “flight” position, where PITCH/ROLL signal sources indicated zero; (b) Connect the Ground Power Unit of corresponding quality to the airplane;
EFFECTIVITY ALL
022.10.00 Page: 501 Mar 10/17
MAINTENANCE MANUAL (c) Connect the KTS 162 Flight Line Tester between KCP 220 unit and airplane harness with the six cables provided (used only if the airplane not equipped with a measure clamps on the J2201 and J2202 connectors of the KCP 220 unit – refer to the fig. 503) (d) Remove the KMC 321 Mode Controller from the control panel without the disconnecting from harness. For view on side of KMC 321 Mode Controller (location of potentiometers), refer to the fig. 501
FIG. 501
KMC 321 MODE CONTROLLER ADJUSTMENTS BACK BRITE:
Back light adjustment for mode buttons
NOM BRITE:
Mode annunciator brightness adjustment
RN:
Roll Null
RC:
Roll Command Bar
PC:
Pitch Command Bar
ACCEL: Lateral Acceleration adjustment (e) Mount the KI 254 Flight Command Indicator (valid for KFC 275), the KVG 350 vertical gyro or AHRS (valid for KFC 325) in the adapter plate installed on the tilt and turn table and connect the vertical gyro to the airplane harness using the extender cable. Also connect the vertical gyro to an air source if required. The AHRS unit can be positioned to required position by use a digital level (protractor) without the extender cable. If is the dual installation of attitude gyro installed on the airplane, carry out the basic adjustment / verification of the both attitude gyro systems. NOTE:
When making gyro alignment adjustments, always have the gyro set to zero degrees tilt in the axis not under test.
EFFECTIVITY ALL
022.10.00 Page: 502 Mar 10/17
MAINTENANCE MANUAL (f)
Before applying power make sure that the proper adapter modules are installed in the KCP 220 Flight Computer - refer to the List of Components, and the all antistatic protection of adapter modules are removed – refer to the fig. 502. Apply power to the system. All associated circuit breakers must be activated.
FIG. 502
ANTISTATIC PROTECTION OF KCP 220 ADAPTERS MUST BE REMOVED! (g) After the gyro is fully erected (ten minutes minimum run-up time), engage the System Preflight Test function by depressing the TEST button on the Mode Controller – refer to the Step (3) in work procedure “Check of autopilot function” in this section. (h) Upon successful passage of Pre-flight Test, engage the Flight Director mode by depressing the FD button on the Mode Controller and proceed with the following. (i)
Set the Gyro Stand to zero in both the pitch and roll axis. Adjust the leveling screws for pitch and roll zero visual indication with no parallax.
(j)
Measure the voltage from J2201 pin 20 with reference to J2202 pin 42 with a digital voltmeter. Adjust the Roll Null adjustment for 0.0 VDC. This potentiometer is accessible through the hole labeled RN on the side of the Mode Controller.
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022.10.00 Page: 503 Mar 10/17
MAINTENANCE MANUAL
FIG. 503
MEASURE CLAMPS ON THE CONNECTORS OF THE KCP 220 (k) Measure the voltage from J2201 pin 40 with reference to J2202 pin 42 with a digital voltmeter. Adjust the Pitch Null adjustment for 0.0 VDC. This potentiometer is accessible through the hole labeled PN on the bottom of the KCP 220. (l)
Measure the voltage again from J2201 pin 20 with respect to J2202 pin 42. Tilt the gyro to a twenty-five degree right bank by turning the tilt stand CW to the detent. Visually adjust to exactly twenty-five degrees bank. Adjust the Roll Gain adjustment for -5.0 +/- 0.1 VDC. This potentiometer is accessible through the hole labeled RG on the bottom of the KCP 220.
(m) Tilt the Gyro to a twenty-five degree left bank by turning the Tilt Stand CCW to the detent. Visually adjust to exactly twenty-five degrees bank. The voltage should read +5.0 +/- 0.1 VDC. If the reading in step (m) exceeds +5.1 VDC, repeat step (l) and reduce the gain setting by onehalf the amount exceeded in step (m). If step (m) measured less than +4.9 VDC, repeat step (l) and increase the gain setting by one-half the amount short in step (m). Repeat steps (l) and (m)
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022.10.00 Page: 504 Mar 10/17
MAINTENANCE MANUAL until both the right and left bank voltage measurement are within tolerance. The proper total voltage excursion must be 10 +/- 0.2 VDC. IMPORTANT:
Check the correct direction of the motion of the FD Bar and steering wheels.
(n) With the Gyro Test Stand in the zero pitch position, adjust the leveling screws on the Tilt Stand to obtain a pitch zero visual indication on the vertical gyro. (Horizon line aligned with 90 deg index marks.) Reset the Pitch Null (Step (k)) after any re-leveling is done. (o) Measure the voltage again from J2201 pin 40 with respect to J2202 pin 42. Tilt the Gyro ten degrees nose down with the Tilt Stand by moving the adjustable support bar to the rear slot. Adjust the Pitch Gain adjustment for +2.0 +/- 0.1 VDC. This potentiometer is accessible through the hole labeled PG on the bottom of the KCP 220. (p) Tilt the Gyro ten degrees nose up with the Tilt Stand by moving the adjustable support bar to the forward slot. The voltage should read 2.0 +/- 0.1 VDC. If the meter reading exceeds -2.1 VDC, repeat steps (o) and reduce the gain by one-half the amount exceeded in step (p). If the meter reading is less than -1.9 VDC, repeat step (o) and increase the gain by one-half the amount short in step (p). Repeat steps (o) and (p) until both pitch up and down are within tolerance. The proper total voltage excursion must be 4 +/- 0.2 VDC. IMPORTANT:
Check the correct direction of the motion of the FD Bar and steering wheels.
(2) Adjustment in YAW Channel The so-called “Lateral Acceleration” is adjusted in this channel. Voltage in this channel is measured from J2203 pin 42 with reference to J2202 pin 42 with a digital voltmeter. Sensitivity in this case amounts to 180 mV for 1°; the airplane must be situated in flight horizon and in relative standstill. Final adjustment of voltage approximately 0.0 VDC is being executed by ACCEL potentiometer accessible through the hole labeled ACCEL on the side of the Mode Controller.
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022.10.00 Page: 505 Mar 10/17
MAINTENANCE MANUAL
(3) Adjustment of position indicator The airplane is to be locate in the flight horizon. The KI 254 Position indicator (valid for KFC 275) or KCI310A or SA-4550 position indicator (valid for KFC 325) must be mounted in the cockpit instrument panel. Using potentiometer RC (Roll Command Bar adjustment in ROLL Channel) and potentiometer PC (Pitch Command Bar adjustment in PITCH Channel) the Command Bar adjustment into the centric position is made. This adjustment is a visual one and you must bear in mind the pilot’s view. (4) Adjustment of brightness The KMC 321 Mode Controller contains the BACK BRITE potentiometer (if installed) for back light adjustment of mode buttons and NOM BRITE potentiometer for the brightness adjustment of mode annunciator. (5) Adjustment of inclinometers Verify and/or set the inclinometers on FDI and Turn and Bank Indicators to middle. (6) Check of the adjustment of rudder damper Push the YD push button on the KMC 321 Mode Controller and verify if is the rudder in middle position and not move. Adjustment is executed by ACCEL potentiometer accessible through the hole labeled ACCEL on the side of the Mode Controller. (7) Calibration of altitude This calibration procedure is performed on the KAS 297C Altitude selector for assurance of high accuracy of the transmission of altitude value. The calibrating procedure is as follows: (a) Connect the Air data tester by means the B598984N Connection set to the airplane Pitotstatic system - refer to the AMM section 012.02.00. (b) Set the standard pressure 1013.23 mb on the coding altimeter. (c) Simultaneously push the VS ENG and ALT ARM push buttons on the KAS 297C Altitude selector and hold them longer than 5 sec. The display shows a digital information of the altitude supplied by the coding altimeter. (d) Calibrating procedure is to be carried out in altitudes 0; 5,000; 10,000 and 15,000 feet. When the coding altimeter displays accurately the calibrated altitude value, we press shortly the button VS ENG. In this moment the deviation from the actual altitude is saved in the memory and is respected in all readings. NOTE:
Deviation greater then 125 feet cannot be calibrated!
(e) Calibrating mode is cancelled if the ALT TRIM push button and then the VS ENG push button is pressed; after very short simultaneous holding both buttons are to be released again. EFFECTIVITY ALL
022.10.00 Page: 506 Mar 10/17
MAINTENANCE MANUAL CAUTION:
IF CALIBRATING PROCEDURE IS FINISHED, BUTTONS MUST NOT BE OPERATED IN THE CALIBRATING MODE. OTHERWISE, DISTORTION OF CALIBRATING AND INCREASE OF AUTOPILOT’S ERROR SHOULD OCCUR.
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MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
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022.10.00 Page: 508 Mar 10/17
MAINTENANCE MANUAL
CONTROL AND SIGNALIZATION OF KFC 325 OR KFC 275 AUTOPILOT DESCRIPTION AND OPERATION 1. General The operation of flight control system and signalization of its operating conditions are provided by means of the following instruments. A.
The KMC 321 Mode controller The mode controller provides switching ON/OFF of the autopilot and the flight director control and by pressing an appropriate push-button the individual system mode is selected. Moreover, there is located the TEST push-button to provide the test of flight control system and the switch of horizontal control (allows to set flight altitude or pitching position without cancellation of preset mode of commanded control system or without turning off the autopilot). Moreover, the control box allows to indicate switching on the individual system modes (activated modes use the green light indication, standby modes use amber light).
FIG. 1
THE KMC 321 MODE CONTROLLER
EFFECTIVITY ALL
022.10.01 Page: 1 Nov 1/11
MAINTENANCE MANUAL B.
The KAS 297C Altitude setter The KAS 297C Altitude setter allows to preset a required flight altitude at climb and descent and the vertical airspeed at climb and descent.
FIG. 2
THE KAS 297 ALTITUDE SETTER
C. The KAP 315 A Annunciator panel The annunciator panel provides continuously data on operation conditions. It indicates operating modes being just activated and standby modes before activation. Moreover, the alarm annunciation of elevator trim failure is indicated.
FIG. 3
THE KAP 315 A ANNUNCIATOR PANEL
EFFECTIVITY ALL
022.10.01 Page: 2 Nov 1/11
MAINTENANCE MANUAL D. The UP-TRIM-DN, A/P DISC Switch and CWS Push-button •
The UP-TRIM-DN (on the left steering wheel) The servodrive of an elevator trim tab is controlled by the switch. The switch consists of two halves - the left half provides the supply of trim tab servodrive clutch, the right half controls the direction of motion. To use the switch correctly both the halves must be pressed.
•
The A/P disk switch (on the left and right steering wheel) The switch controls immediate turning off of all the servodrives and circuits of flight director mode.
•
The CWS switch (on the left and right steering wheel) Press The push-button activated the flight director mode (FD). NOTE:
•
The FD mode can be activated with the FD push-button on the mode controller.
GA push-button (on left ECL) The GA push-button is used to engrage the go-ground mode pressing the push-button cancels all the activated modes). The flight control system enables selection of 14 operating modes which provide signals for the flight director and the autopilot.
FIG. 4
THE SWITCHES ON THE LEFT AND RIGHT STEERING WHEEL
EFFECTIVITY ALL
022.10.01 Page: 3 Nov 1/11
MAINTENANCE MANUAL E. NAV 1/NAV 2 annunciator push-button switch (if installed) The NAV 1/NAV 2 annunciator push-button switch provides switching over of the cooperate navigation system with the autopilot. If the switch is in the position NAV 1 - the left PNI indicator displays navigation data from NAV I system (the right PNI indicator from the NAV II) and the autopilot cooperates with the NAV I system. If the switch is in the position NAV 2 the left PNI indicator displays navigation data from the NAV II system (the right PNI indicator from the NAV I system) and the autopilot cooperates with the NAV II system. The NAV 1 / NAV 2 annunciator (on the cover of the control panel) indicates which navigation data (either from the NAV I or the NAV II navigation system) are displayed on the right PNI indicator. F.
KA 138 relay switch NOTE:
This switch is only installed in aircrafts on which the Information Bulletin No. L410 UVP-E/040b has been accomplished.
The relay switch enables the autopilot to be connected either to NAV 1 (KX 165) or NAV 2 (KNS 81) system (see Sub-Section 034.53.00). The relay switch is controlled by a select switch with NAV 1/NAV 2 annunciators. In normal operation, the autopilot system is connected to NAV 1 system. With the autopilot engaged, NAV 1 annunciator on the select push-button is illuminated on the copiloťs side. When switching over to NAV 2, the KI 525A indicators are also switched over simultaneously, and the NAV 2 annunciator on the select push-button is illuminated on the pilot’s side with the NAV 1 annunciator illuminated on the copilot’s side.
EFFECTIVITY ALL
022.10.01 Page: 4 Dec 10/14
MAINTENANCE MANUAL G. The LUN 2733 Autopilot disconnect alerter (if installed): The Autopilot disconnect alerter serves for assurance of the light and aural signalization at the KFC 275 or KFC 325 autopilot disconnect.
FIG. 5
LUN 2733 AUTOPILOT DISCONNECT ALERTER (1) LUN 2733 Autopilot disconnect alerter, (2) Mount assy 212260001001
EFFECTIVITY ALL
022.10.01 Page: 5 Dec 10/14
MAINTENANCE MANUAL
FIG. 6
BLOCK SCHEME OF THE LUN 2733 AUTOPILOT DISCONNECT ALERTER
Connector pin-out of the LUN 2733 Autopilot disconnect alerter Connector Type: HDC15M500V5C-14 Pin
Signal Label
Signal Description
1
+28VDC
Power +28V of airplane wiring
2
+28VDC
Power +28V of airplane wiring
3
ACFT_GND
Ground (0V) of airplane wiring
4
ACFT_GND
Ground (0V) of airplane wiring
5
CHASSIS_GND
Chassis ground
6
RELAY
Output of RELAY signalization
7
LAMP
Output of LAMP signalization
8
CWS
Input of CWS signal
9
AP_CLU_ENG
Input of AP Clutch Engage signal
10
TRIM_INTERUPT
Input of Trim Interrupt signal
11
TRIM_POWER
Input of Trim Power
12
AP/TRIM_HORN
Input of AP/Trim Horn
13
AURAL_ALERT_OUT_HIGH
Output Aural Audio Out
14
AURAL_ALERT_OUT_LOW
Ground Aural Audio Out
15
NC
Not connected
EFFECTIVITY ALL
022.10.01 Page: 6 Dec 10/14
MAINTENANCE MANUAL 2.
Control servo description A.
Aileron servo: No.
Name
Type (Dwg. No.)
Part number
Note
KSA 372 X
065-00056-0070
-
1.
ROLL servo
2.
ROLL servo mount
KSM 375
065-00015-0001
-
3.
ROLL servo clutch
-
200-00318-0001
T Q = 175 in . lbs
The aileron control by autopilot servo is operated by a KSA 372X electric servo (fig. 7) located under cockpit floor between frames No. 6 and 7. Motion of the servo drum is transferred by cable transmission (2) to a sector with bell crank (3). Cable transmission is tensioned according to the table 402 in section 022.10.00. Tension of the cable transmission can be adjusted by means of turnbuckles (4). Motion of the bell crank is transferred by a tie rod (5) a to quadrant (6) which actuates primary aileron control.
FIG. 7
AILERON SERVO (1) KSA 372 X aileron servo; (2) Cable transmission; (3) Sector with bell crank; (4) Turnbuckle; (5) Tie rod; (6) Quadrant
EFFECTIVITY ALL
022.10.01 Page: 7 Dec 10/14
MAINTENANCE MANUAL B.
Rudder servo: No.
Name
Type (Dwg. No.)
Part number
Note
1.
YAW servo
KSA 372
065-00056-0050
-
2.
YAW servo mount
KSM 375
065-00015-0001
-
3.
YAW servo clutch
-
200-00318-0001
T Q = 145 in . lbs
The rudder control by autopilot servo is operated by a KSA 372 electric servo (fig. 8) located on frame No. 24. Motion of the servo drum is transferred by cable transmission (3) supported by pulleys (5) to rudder primary control cables. Cable transmission is tensioned according to the table 402 in section 022.10.00. Tension of the cable transmission can be adjusted by means of turnbuckles (2). Clamps (4) are used to attach the cable transmission to the primary control cables.
FIG. 8
RUDDER SERVO (1) KSA 372 rudder servo; (2) Turnbuckle; (3) Cable transmission; (4) Clamp; (5) Pulley
EFFECTIVITY ALL
022.10.01 Page: 8 Dec 10/14
MAINTENANCE MANUAL C. Elevator servo: No.
Name
Type (Dwg. No.)
Part number
Note
KSA 372 X
065-00056-0070
-
1.
PITCH servo
2.
PITCH servo mount
KSM 375
065-00015-0001
-
3.
PITCH servo clutch
-
200-00318-0001
T Q = 125 in . lbs
The elevator control by autopilot servo is operated by a KSA 372 X electric servo (fig. 9) located at frame No. 26. Motion of the servo drum is transferred by cable transmission (3) supported by a pulley (4) to the elevator primary control system. The cable transmission is tensioned according to the table 402 in section 022.10.00. Tension of the cable transmission can be adjusted by turnbuckles (2).
FIG. 9
ELEVATOR SERVO (1) KSA 372 X elevator servo; (2) Turnbuckle; (3) Cable transmission; (4) Drive-pulley provided with lever
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022.10.01 Page: 9 Dec 10/14
MAINTENANCE MANUAL D. Elevator trim tab servo: No.
Name
Type (Dwg. No.)
Part number
Note
1.
PITCH TRIM servo
KS 272 A
065-00061-0050
-
2.
PITCH TRIM mount
KM 277
065-00041-0002
-
3.
PITCH TRIM clutch
-
200-02085-0002
T Q = 26 in . lbs
The elevator trim tab control by autopilot servo is operated by a KS 272 A electric servo (fig. 10) located on frame No. 23. Motion of the servo sprocket is transferred to a cable and chain (2) of the trim tab primary control. The cables are tensioned according to the table 402 in section 022.10.00. Tension of the cable transmission can be adjusted by turnbuckles (3).
FIG. 10
ELEVATOR TRIM TAB SERVO (1) KS 272 A elevator trim tab servo; (2) Cable and chair; (3) Turnbuckle; (4) Sprocket; (5) Chain-coupler
EFFECTIVITY ALL
022.10.01 Page: 10 Dec 10/14
CHAPTER
COMMUNICATIONS
MAINTENANCE MANUAL
CHAPTER 23 COMMUNICATIONS LIST OF EFFECTIVE PAGES Chapter, Section, Subject
Page
Date
Chapter, Section, Subject
Page
Date
Title page
-
-
023.11.00
3003
Nov 1/11
List of Effective Pages
1
Apr 15/15
Description and Operation
3004
Nov 1/11
2
Dec 10/14
023.11.01
1
Dec 10/14
3
Apr 15/15
Description and Operation
2
Dec 10/14
4
Nov 1/11
Removal / Installation
401
Dec 10/14
1
May 30/14
402
Dec 10/14
2
Apr 15/15
403
Dec 10/14
3
Nov 1/11
404
Dec 10/14
4
Nov 1/11
405
Dec 10/14
1
Nov 1/11
406
Dec 10/14
2
Nov 1/11
023.12.00
1001
Nov 1/11
1
Dec 10/14
Description and Operation
1002
Nov 1/11
2
Dec 10/14
Servicing
1301
May 30/14
3
Dec 10/14
1302
Apr 15/15
4
Dec 10/14
023.12.00
2001
Nov 1/11
5
Dec 10/14
Description and Operation
2002
Nov 1/11
6
Dec 10/14
023.12.00
3001
May 30/14
023.00.00
1
Nov 1/11
Description and Operation
3002
May 30/14
Description and Operation
2
Nov 1/11
3003
May 30/14
201
Nov 1/11
3004
May 30/14
202
Nov 1/11
023.12.01
1001
Nov 1/11
301
May 30/14
Description and Operation
1002
Nov 1/11
302
Nov 1/11
Servicing
1301
May 30/14
023.10.00
1
Nov 1/11
1302
Nov 1/11
Description and Operation
2
Nov 1/11
1303
Nov 1/11
023.11.00
2001
Nov 1/11
1304
Nov 1/11
Description and Operation
2002
Nov 1/11
1305
Nov 1/11
3001
Nov 1/11
1306
Nov 1/11
3002
Nov 1/11
Record of Revisions
Record of Temp. Revisions
Contents
Maintenance Practices
Servicing
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023-LIST OF EFFECTIVE PAGES Page: 1 Apr 15/15
MAINTENANCE MANUAL Chapter, Section, Subject
Page
Date
Chapter, Section, Subject
Page
Date
023.12.01
1307
Nov 1/11
023.40.00
1001
May 31/12
Servicing
1308
Nov 1/11
Description and Operation
1002
Nov 1/11
1309
Nov 1/11
Servicing
1301
Nov 1/11
1310
May 30/14
1302
Nov 1/11
1311
Nov 1/11
023.40.00
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May 31/12
1312
Nov 1/11
Description and Operation
2002
Nov 1/11
1401
Nov 1/11
2003
Nov 1/11
1402
Nov 1/11
2004
Nov 1/11
023.12.01
2001
May 30/14
023.40.00
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May 31/12
Description and Operation
2002
Nov 1/11
Description and Operation
3002
Nov 1/11
3001
May 30/14
3003
Nov 1/11
3002
Nov 1/11
3004
Nov 1/11
023.12.02
1
May 30/14
023.40.01
1001
Nov 1/11
Description and Operation
2
Nov 1/11
Description and Operation
1002
Nov 1/11
301
May 30/14
Servicing
1301
May 30/14
302
May 30/14
1302
Nov 1/11
401
May 30/14
1303
Nov 1/11
402
Nov 1/11
1304
Nov 1/11
023.12.03
1001
Nov 1/11
1305
May 30/14
Description and Operation
1002
Nov 1/11
1306
May 30/14
Servicing
1301
Nov 1/11
1307
May 30/14
1302
Nov 1/11
1308
May 30/14
1401
Nov 1/11
1309
May 30/14
1402
Nov 1/11
1310
Nov 1/11
023.30.00
1
Nov 1/11
1401
Nov 1/11
Description and Operation
2
Nov 1/11
1402
Nov 1/11
023.31.00
3001
Nov 1/11
023.40.01
2001
May 31/12
Description and Operation
3002
Nov 1/11
Description and Operation
2002
May 31/12
Servicing
3301
Nov 1/11
023.40.01
3001
May 31/12
3302
Nov 1/11
Description and Operation
3002
May 31/12
023.32.00
1
May 30/14
023.40.02
1001
Nov 1/11
Description and Operation
2
Nov 1/11
Description and Operation
1002
Nov 1/11
3
Nov 1/11
Servicing
1301
Nov 1/11
4
Nov 1/11
1302
Nov 1/11
Removal / Installation
Servicing
Removal / Installation
Removal / Installation
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Removal / Installation
023-LIST OF EFFECTIVE PAGES Page: 2 Dec 10/14
MAINTENANCE MANUAL Chapter, Section, Subject
Page
Date
Chapter, Section, Subject
Page
Date
023.40.02
1303
Nov 1/11
023.70.00
301
Nov 1/11
Servicing
1304
Nov 1/11
Servicing
302
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May 31/12
L410UVP-E/170d
Apr 5/13
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May 30/14
023-RECORD OF REVISIONS Page: 1 May 30/14
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MAINTENANCE MANUAL CHAPTER 23 COMMUNICATIONS CONTENTS Subject
Chapter, Section, Subject
GENERAL 023.00.00 Description and Operation General Maintenance Practices General Servicing Check of the function of the shock absorbers of the rear panel in the pilot's cockpit
Page
Effectivity
1 1 1 201 201 301 301
ALL
SPEECH COMMUNICATION Description and Operation General
023.10.00
1 1 1
ALL
HF COMMUNICATION Description and Operation General List of components Operation
023.11.00
2001 2001 2001 2001 2001
L410 UVP-E9
3001 3001 3001 3001 3001
L410 UVP-E20
HF COMMUNICATION Description and Operation General List of components Operation HF ANTENNA (if installed) Description and Operation General List of components Operation Removal / Installation Replacement of the HF antenna
023.11.01
1 1 1 1 1 401 401
ALL
VHF COMMUNICATION Description and Operation General List of components Operation Servicing Check of the LUN 3524.13 transceiver operation Measurement of resistance of VHF transceiver antenna cable
023.12.00
1001 1001 1001 1001 1001 1301 1301
L410 UVP-E
VHF COMMUNICATION Description and Operation General List of components Operation
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L410 UVP-E9
023-CONTENTS Page: 1 Dec 10/14
MAINTENANCE MANUAL Subject
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VHF COMMUNICATION Description and Operation General List of components Operation
3001 3001 3001 3001 3001
L410 UVP-E20
LUN 3524.13 TRANSCEIVER 023.12.01 Description and Operation Purpose Technical data Operation Servicing Check of VHF transceiver Check of external appearance Check of AVC function Receiver gain Receiver sensitivity Function of squelch Output performance of the transceiver Ability of modulation Distorting of audio signal Monitoring Check carrier frequency Check the correct connection of the aerial cables to the station Removal / Installation Removal and Installation of the transceiver LUN 3524.13
1001 1001 1001 1001 1001 1301 1301 1301 1302 1303 1304 1305 1306 1308 1309 1310 1311 1312
L410 UVP-E
KY 196A TRANSCEIVER Description and Operation Purpose Technical data Operation
2001 2001 2001 2001 2001
L410 UVP-E9
KY 196A TRANSCEIVER Description and Operation Purpose Technical data Operation
3001 3001 3001 3001 3001
L410 UVP-E20
5 QK 405 16 OR CI 268-5 ANTENNA 023.12.02 Description and Operation Purpose Technical data Description Operation Servicing Inspection of the antenna Check of the correct connection of the cable to the antenna Inspection of the antenna
1 1 1 1 1 1 301 301 301
ALL
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ALL
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401 401
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5 QK 405 01 ANTENNA Description and Operation Purpose Technical data Description Operation Servicing Inspection of the 5 QK 405 01 antenna Removal / Installation Removal and Installation of the 5 QK 405 01 antenna
023.12.03
1001 1001 1001 1001 1001 1001 1301 1301 1401 1401
L410 UVP-E
PASSENGER ADDRESS AND ENTERTAINMENT Description and Operation General
023.30.00
1 1 1
ALL
PXE 7300 IN-FLIGHT ENTERTAINMENT SYSTEM (if installed) Description and Operation General List of components Description Operation Servicing Check of PXE 7300 IFE system (if installed)
023.31.00
3001
L410 UVP-E20
FD 932DVD-LP IN-FLIGHT ENTERTAINMENT SYSTEM (if installed) Description and Operation General List of components Operation
023.32.00
INTERCOMMUNICATION Description and Operation General List of components Operation Servicing Check of the intercom Operation
023.40.00
Removal / Installation Removal and Installation of the antenna
3001 3001 3001 3001 3002 3301 3301 1
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L410 UVP-E
INTERCOMMUNICATION Description and Operation General List of components Operation
2001 2001 2001 2001 2002
L410 UVP-E9
INTERCOMMUNICATION Description and Operation General List of components Operation
3001 3001 3001 3001 3002
L410 UVP-E20
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MAINTENANCE MANUAL Subject
LUN 3591.11 OR LUN 3591.13 AUDIO SELECTOR BOX Description and Operation Purpose Technical data Operation Servicing Check of audio switch box LUN 3591.11 or LUN 3591.13 Check of external appearance Check of frequency characteristics Distortion check Check the signal noise level Load change influence check Check of voltage amplification coefficient of inputs from navigation and communication receivers Check of coefficient of voltage amplification from microphone input Function check under decreased supply voltage Servicing Removal and Installation of the audio switch box LUN 3591.11 or LUN 3591.13
Chapter, Section, Subject
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1001 1001 1001 1001 1001 1301 1301
L410 UVP-E
1302 1302 1304 1305 1306 1307 1308 1309 1401 1401
KMA 24 H-70 AUDIO SELECTOR BOX Description and Operation Purpose Technical data Operation
2001 2001 2001 2001 2001
L410 UVP-E9
KMA 24 H-70 AUDIO SELECTOR BOX Description and Operation Purpose Technical data Operation
3001 3001 3001 3001 3001
L410 UVP-E20
1001 1001 1001 1001 1001 1301 1301
L410 UVP-E
LUN 3591.22 CONNECTION BOX Description and Operation Purpose Technical data Operation Servicing Check for proper function of LUN 3591.22 connection box Removal / Installation Removal and Installation of LUN 3591.22 connection box
023.40.02
GSSh-A-18, GSSh-A-18E HEADSET Description and Operation General List of components Operation Servicing Inspection of GSSh-A-18 or GSSh-A-18E headset
023.40.03
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L410 UVP-E
023-CONTENTS Page: 4 Dec 10/14
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
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B076031N RELAY CHANGE-OVER SWITCH Description and Operation General List of components Operation Removal / Installation Removal and Installation of B076031N relay change-over switch
023.40.04
1001 1001 1001 1001 1001 1401 1401
L410 UVP-E
LUN 3513 AMPLIFIER Description and Operation Purpose Technical data Operation Servicing Check for proper function of LUN 3513 amplifier Removal / Installation Removal and Installation of LUN 3513 amplifier
023.40.05
1001 1001 1001 1001 1001 1301 1301 1401 1401
L410 UVP-E
ARZ 3908 LOUDSPEAKER Description and Operation Purpose Technical data
023.40.06
1 1 1 1
ALL
STATIC DISCHARGING 023.60.00 Description and Operation General Static discharging Servicing Inspection of the static dischargers Removal of the static dischargers, cleaning their seating areas and installation them again back Inspection of the all bonding strips of moving parts. Check of the reliability of their fixations
1 1 1 1 301 301 302
ALL
COCKPIT VOICE RECORDER (if installed) Description and Operation General Servicing Battery check / Battery replacement of the DK 120 or ELP-362D underwater acoustic beacon Check of the cockpit voice recorder operation
023.70.00
1 1 1 301 301
DK 120 OR ELP 362D UNDERWATER ACOUSTIC BEACON (if installed) Description and Operation Purpose Technical data Accessories Servicing Battery replacement of the DK 120 or ELP-362D underwater acoustic beacon
023.70.01
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023-CONTENTS Page: 5 Dec 10/14
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A 100 A COCKPIT VOICE RECORDER (if installed) Description and Operation General List of components Operation
023.71.00
1 1 1 1 1
ALL
FA 2100 COCKPIT VOICE RECORDER (if installed) Description and Operation General List of components Operation Servicing CVR Data Readout or Download Removal / Installation Removal and installation of the FA 2100 CVR Unit
023.72.00
1 1 1 3 3 301 301 401 401
ALL
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MAINTENANCE MANUAL
GENERAL DESCRIPTION AND OPERATION 1. General The communication system, for external communication with the aircraft, is provided by VHF transceivers. In addition an HF transceiver may be installed in same aircrafts. The intercommunication of the aircraft crew members is provided by the intercommunication system. To prevent the transceivers from being interfered by static electricity discharges the aircraft is provided with a system of static dischargers mounted on the trailing edge of the wing, tail unit and rear part of the fuselage and all the aircraft assemblies are electrically bonded. In addition, pilot’s voice recording device may be installed as part of the communication system.
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GENERAL MAINTENANCE PRACTICES 1. General A.
B.
The components removed from the aircraft for laboratory test must be inspected for: •
visible mechanical damage of the body
•
corrosion of plug-and-socket connectors, terminals, pushbuttons
•
deformation of plug-and-socket connector pins
•
deposits of dirt
•
evidence of fluid leaks
When removing a unit (a component) from the aircraft (for laboratory test or replacement), its place of installation, connector or pipe mating parts must be inspected for: •
mechanical damage (cracks) of the place of installation
•
wear of the attachment holes
•
corrosion and deformation of plug-and-socket connector pins
•
dents
•
ruptures
•
deformation of pipe connecting parts
•
damage of connector and pipe union nut threads
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GENERAL SERVICING 1. Check of the function of the shock absorbers of the rear panel in the pilot's cockpit A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.00.00.A Periodical
E.
Procedures (1) Functional check of the rear control panel shock-absorbing characteristics. (2) When pressed down and released, the rear control panel must resume its original position (3) The following defects are not permitted: The rear control panel plate must not be in contact with the rear control panel frame. (4) Press down the rear control panel in various places and in the middle. The panel must resume its initial position.
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SPEECH COMMUNICATIONS DESCRIPTION AND OPERATION 1. General The speech communication system consists of a VHF communication system (refer to 023.12.00, VHF Communication) and if installed, a HF communication system (refer to 023.11.00 HF Communication).
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MAINTENANCE MANUAL
HF COMMUNICATION DESCRIPTION AND OPERATION 1. General The High Frequency (HF) transceiver system is used for long distance voice and data communication to other aircraft and/or ground stations. KHF 950 HF radio station can be optionally installed on the aircraft.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Circuit breaker HF
AZRGK 2
1
On the overhead panel
2.
Contactor
TDK 501 DOD
1
Between 8th and 9th frames on left
3.
Circuit breaker HF
AZRGK 25
1
Between 8th and 9th frames on left
4.
Control box
KCU 951
1
On the rear control panel
5.
Power amplifier (antenna block)
KAC 952
1
Between 21st and 22nd frames
6.
Receiver (driver)
KTR 953
1
Between 1st and 2nd frames on right
8.
Antenna
KPN 071-1214-00
1
Between 8th and 21st frames
9.
Fuse block
KPN 071-0022-00
1
On 8th frame on left
3. Operation The radio station is set in operation by switching on BATTERY I, II switches and HF and INTERCOM I, II circuit breakers on the overhead panel and turning OFF/VOLUME knob on the control box of the radio station (KCU 951) on the rear control panel from the left checked position to the right. NOTE:
a.
If the radio station is not set in readiness (about 1 minute after switching on), the selected frequency is not displayed and transmission will be blocked.
b.
If the FREQ/CHAN switch is not pressed, the frequency which was used during the previous transmission is displayed on the screen.
c.
If the FREQ/CHAN switch is pressed the channel with corresponding frequency which was used during the previous transmission is displayed on the screen.
Listening in headphones is switched on by HF lever switch on the audio selector box. Selection of the short-wave radio station for transmission is made by the turning switch on the audio selector box. By switching it on to the HF position the signal from the microphone is led to the SW radio station. By turning the SQELCH noise squelch knob in the anti-clockwise direction until the noise is very low or disappears. Control and using of the SW radio station during flight is described in the Flight Manual. The SW radio station is switched off by switching off the above mentioned switches and circuit breakers. EFFECTIVITY
023.11.00
L 410 UVP-E9
Page: 2001 Nov 1/11
MAINTENANCE MANUAL
FIG. 2001
SCHEME OF KHF 950 RADIO STATION
EFFECTIVITY
023.11.00
L 410 UVP-E9
Page: 2002 Nov 1/11
MAINTENANCE MANUAL
HF COMMUNICATION DESCRIPTION AND OPERATION 1. General The High Frequency (HF) transceiver system is used for long distance voice and data communication to other aircraft and/or ground stations. KHF 950 SW radio station is installed on the aircraft.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Circuit breaker HF
AZRGK 2
1
On the overhead panel
2.
Contactor
TDK 501 DOD
1
Between 8th and 9th frames on left
3.
Circuit breaker HF
AZRGK 25
1
Between 8th and 9th frames on left
4.
Control box
KCU 951
1
On the rear control panel
5.
Power amplifier (antenna block)
KAC 952
1
Between 21st and 22nd frames
6.
Receiver (driver)
KTR 953
1
Between 1st and 2nd frames on right
8.
Antenna
KPN 071-1214-00
1
Between 8th and 21st frames
9.
Fuse block
KPN 071-0022-00
1
On 8th frame on left
3. Operation The radio station is set in operation by switching on BATTERY I, II switches and HF and INTERCOM or INTERCOM I, II circuit breakers on the overhead panel and turning OFF/VOLUME knob on the control box of the radio station (KCU 951) on the rear control panel from the left checked position to the right. NOTE:
a.
If the radio station is not set in readiness (about 1 minute after switching on), the selected frequency is not displayed and transmission will be blocked.
b.
If the FREQ/CHAN switch is not pressed, the frequency which was used during the previous transmission is displayed on the screen.
c.
If the FREQ/CHAN switch is pressed the channel with corresponding frequency which was used during the previous transmission is displayed on the screen.
Listening in headphones is switched on by HF lever switch on the audio selector box. Selection of the short-wave radio station for transmission is made by the turning switch on the audio selector box. By switching it on to the HF position the signal from the microphone is led to the SW radio station. By turning the SQELCH noise squelch knob in the anti-clockwise direction until the noise is very low or disappears. Control and using of the SW radio station during flight is described in the Flight Manual. The SW radio station is switched off by switching off the above mentioned switches and circuit breakers. EFFECTIVITY L 410 UVP-E20
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MAINTENANCE MANUAL
FIG. 3001
SCHEME OF KHF 950 RADIO STATION (THE VARIANT WITH ONE CIRCUIT BREAKER INTERCOM)
EFFECTIVITY L 410 UVP-E20
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FIG. 3002
SCHEME OF KHF 950 RADIO STATION (THE VARIANT WITH TWO CIRCUIT BREAKERS INTERCOM I, II)
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HF ANTENNA (IF INSTALLED) DESCRIPTION AND OPERATION 1. General The HF antenna serves for transmitting and receiving in High Frequency (HF) band.
2. List of components No.
Name
Qty
Location
1.
HF antenna wire
1
Between 8th and 21st frames
2.
Insulator
1
On 8th frame up
3.
Insulator
1
On 21st frame up
4.
Turnbuckle
1
On 8th rib of fin
3. Operation The HF antenna transmits and receives in HF band if the HF transceiver system for long distance voice and data communication to other airplane and/or ground stations is installed.
FIG. 1
HF ANTENNA INSTALLATION (2) Turnbuckle, (3), (4) Insulator, (26) HF antenna wire
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MAINTENANCE MANUAL HF ANTENNA (IF INSTALLED) REMOVAL / INSTALLATION 1. Replacement of the HF antenna A.
Fixture, Test and Support Equipment
B971051N (L410.9712) Tension meter or e.g. T5 SERIE (T5-2002-101-00) PACIFIC SCIENTIFIC Tensitron ACX digital airplane cable tension meter, Steps (e.g. B097365N); P/N 14053 or P/N 50ARM300-250 Tool Wire Release (device for stripping of insulation is included in the 45ARM300 kit)
B.
Materials
45ARM300 HF Wire Antenna System (Ord. No. B501564N); Sealing putty (e.g. Teroson Terostat MS 930)
C. Tools
Necessary tools from tool kit
D. Referenced information E.
Procedures (1) Place the stairs (e.g. B097365N) to the airplane. (2) Remove the old wire from the chuck jaw fitting as follows. Cut off wire not less than 2” from the fitting on the upper part of the №.8 frame – refer to the Fig. 401. Do not remove the sleeve (6). Remove polyethylene (2) so as to expose the wire conductor (3) gripped by the chuck jaws. Slide P/N 50ARM300-250 tool onto the wire and press the release tube firmly into the nozzle aperture. By this action the chuck jaws are tripped, thereby releasing the grip on the wire. Remove the wire. (3) Unscrew the sleeve (6) and the elbow (5) from insulator (3) – refer to the Fig. 408 on the upper part of the frame № 21. Remove the wire according to step (2). (4) Fix the wire to the insulator (3) on the upper part of the frame № 21 as follows. Fit end of the wire (26) by means of the P/N 50ARM300-250 tool as follows. Insert wire into P/N 50ARM300-250 tool until it bottoms in the counter bore refer to the Fig. 402. Hold wire in one hand. Place thin knife blade with other hand into slot of the P/N 50ARM300-250 tool. Apply pressure on knife blade and rotate a complete revolution around the wire to partially sever the insulation at 7/ 16” point – refer to the Fig. 403. The P/N 50ARM300-250 tool is so designed as to prevent the knife blade from making contact with the conductor. This is important, since radial nicking of the conductor may cause early
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MAINTENANCE MANUAL failure of the wire. Hold wire in one hand and with pliers grip and twist end of insulation, finally removing end of insulation. The exposed conductor must be 7/ 16”, with no nicks or scratches.
FIG. 401
REMOVAL OF THE WIRE FROM INSULANT (1) P/N 50ARM300-250 Tool Wire Release, (2) Insulation, (3) Wire, (4) Insulator body
FIG. 402
FIG. 403
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MAINTENANCE MANUAL Using a file, carefully remove all burrs and sharp edges from the end of the conductor to permit easy entry into the chuck jaws. Run the wire through the elbow (5) and the sleeve (6). Thrust the wire end firmly and quickly into the fitting through the hole as far as it will go. This will permit the chuck to engage the bared end of the wire – refer to the Fig. 404.
FIG. 404 To ensure firm seating of wire, give sharp tug. When wire is properly installed, the end of the insulation should pass into counter bore of chuck housing – refer to the Fig. 405.
FIG. 405 Make sure that the entire 7/ 16” length of bare conductor is firmly secured by jaws. Fill the threaded cavity with sealing putty e.g. Teroson Terostat MS 930. Fill the elbow (5) and sleeve (6) as well. Screw the elbow (5) and the sleeve (6) into the insulator body. Screw by finger tight, do not use pliers. To improve finger pressure on sleeve a small piece of the emery cloth between fingers and sleeve is permitted. (5) Run the antenna wire (26) through the lug of the turnbuckle (7) – refer to the Fig. 406. (6) Cut the wire to approximate length, allowing a few extra inches for later trimming to exact length. Straighten the wire carefully to eliminate all kinks. (7) Fix the wire to insulator (4) on the upper part of the frame № 8 according to step (4). (8) Tighten the antenna wire for a tension 70 - 100 N by means the turnbuckle (7). Measure the tension by B971051N (L410.9712) or equivalent. (9) Remove the stairs.
EFFECTIVITY ALL
023.11.01 Page: 403 Dec 10/14
MAINTENANCE MANUAL
FIG. 406
HF ANTENNA TURNBUCKLE, DETAIL I. OF FIGURE 1 (7) Turnbuckle, (8) Attachment, (23) Fork turnbuckle, (25) Tension cable, (26) Cable – HF antenna.
FIG.407
P/N 50ARM300-250 TOOL FOR STRIPPING OF INSULATION OF THE ANTENNA WIRE
EFFECTIVITY ALL
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MAINTENANCE MANUAL
FIG. 408
INSULANT ON THE No. 21 FRAME (3) Insulant, (5) Elbow, (6) Sleeve
FIG.409
INSULANT ON THE No. 8 FRAME (4) Insulant, (6) Sleeve
EFFECTIVITY ALL
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MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
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MAINTENANCE MANUAL VHF COMMUNICATION DESCRIPTION AND OPERATION 1. General The Very High Frequency (VHF) Communication (VHF COM) system is used for voice communication between aircraft and/or aircraft and a ground station. The aircraft is equipped with two VHF transceivers. The transceivers are located on the rear control panel. Connected to the transceivers are power and control wires and coaxial cables from antennas. The LH VHF I transceiver antenna is located up on the fuselage between frames No.7 and 8. The RH VHF II transceiver antenna is located down on the fuselage between frames no.6 and 7. The installation also includes a circuit-breaker and a fuse through the power is supplied to the transceiver and a rockertype switch on the control wheel by means of which the transceiver is switched to the transition mode. The VHF I and INTERCOM I are fed directly from the storage battery if connected to on external power source. It is prevent from being damage if the external source characteristics are not suitable.
2. List of components No.
Name
1.
Circuit breaker VHF I, II
2.
VHF transceiver
3.
4.
Antenna
Fuse
Type (Dwg. No.)
Qty
Location
AZRGK 10
2
Overhead panel
LUN 3524.13
2
Rear control panel
5 QK 40501 (to serial No.2005)
1
Up between frames No. 7 and 8
5 QK 40516 (from serial No.2006)
1
Down between frames No. 6 and 7
4 CSN 354733F (1500)
2
Fuse panel
3. Operation The transceiver is put into readiness for operation by switching the switches BATTERY I, II circuit breakers VHF I, II and INTERCOM I, II circuit-breakers on the overhead panel. To turn on, rotate the OFF, PULL TEST knob clockwise. This knob serves moreover to set the listening level (rotating the knob left and right) and for audio test (pull out position of the volume control knob). Audio for headphones is selected by COM 1 and COM 2 push-buttons PHONE or for 2 loudspeakers placed near overhead control panel by push-button SPEAKER. The rotary switch on the right side of the audio selector box selects the desired transmitter which will be use for the transmission (position 1 or 2). The transceivers work permanently in a reception mode. The transmission mode is turned on by pressing the INT.-VHF switch on the control wheel on the sinusoid-marked side. A light “T” will appear between the “USE” and “STBY” displays on the transceiver in transmission mode. Under normal operating conditions the reception and transmission modes are independent for both pilots. EFFECTIVITY L 410 UVP-E
023.12.00 Page: 1001 Nov 1/11
MAINTENANCE MANUAL
FIG. 1001
VHF COMMUNICATION, PASSENGER ADDRESS AND INTERCOM SYSTEMS SCHEMATIC
EFFECTIVITY L 410 UVP-E
023.12.00 Page: 1002 Nov 1/11
MAINTENANCE MANUAL
VHF COMMUNICATION SERVICING 1. Check of the LUN 3524.13 transceiver operation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.00.A Routine
E.
Procedures (1) Perform operation check according to work procedure 023.40.00.A – Check of intercom operation.
2. Measurement of resistance of VHF transceiver antenna cable A.
Fixture, Test and Support Equipment
PU 500 measuring instrument – resistance meter
B.
Materials
Emery paper No.400 C1005/0080 Varnish red colour
C. Tools
Screwdriver No.713 6,5x130 Screwdriver special-purpose L410.9141-05 Hydraulic raising platform
D. Referenced information
023.12.00.B Periodical
E.
Procedures (1) Remove the LH and RH side covers of the control panel unscrewed 12 special screws by means of a screwdriver No. 713-6.5x130. (2) Tilt upholstery panels between frames No.7 and No.12 on the passenger cabin ceiling by means of an L 410.9141-05 special prepare screwdriver. (3) Provide a hydraulic raising platform and remove the laminated-plastic antenna cover located on the top of the fin having unscrew 24 screw by means of a screwdriver No. 713-6.5x130. (4) Check whether all the circuit-breakers and switches on the overhead panel are switche off. (5) Measurement of VHF transceiver antenna-cable resistance: •
EFFECTIVITY L 410 UVP-E
open-circuit measurment: the measured value musr equal to R=∞
Ω (Ohms)
023.12.00 Page: 1301 May 30/14
MAINTENANCE MANUAL •
short-circuit measurement: the measured value must equal to R=0
Ω (Ohms)
(6) Disconnect the cables from the transceiver and from the antenna located between frames No.7 and 8, as well as from the antenna located on the fin. (7) Measure the open-circuit resistance of the antenna cable between the pin and the body of the transceiver with resistance meter and check antenna value measured according to para 5. (8) Short circuit the pin with the antenna connector body – see measure the short-circuit resistance of the antenna cable between the pin and the transceiver connector body with resistance meter of the range “1 Ω” and check antenna value measured according to para 5. (9) Connect the cables to the transceiver to antenna located between frames No.7 and 8, and to the antenna located on the fin, trighten and secure the connectors. (10) Reinstall the antenna cover on the top of the fin and fasten it with 24 screws by means of a flat screwdriver (e.g. No. 713-6.5 x 130). Clean the ground (earthing) points by means of emery paper No.400 until metallic shine is obtained, and cover with C1005/0080 red varnish. Remove the hydraulic raising platform. (11) Close the upholstery panels between frames No.7 and 12 on the passenger cabin ceiling and fix them using a special-purpose L410 9141-05 screwdriver. (12) Reinstall the LH and RH side covers of the control panel and fasten by means of 12 special screws using a screwdriver No.713-6.5x130.
EFFECTIVITY L 410 UVP-E
023.12.00 Page: 1302 Apr 15/15
MAINTENANCE MANUAL VHF COMMUNICATION DESCRIPTION AND OPERATION 1. General The Very High Frequency (VHF) Communication (VHF COM) system is used for voice communication between aircraft and/or aircraft and a ground station. The aircraft is equipped with two VHF transceivers (KY 196 A and KX 165 A). A navigation system forms part of KX 165 A transceiver. The transceivers are located on the rear control panel. Connected to the transceivers are power and control wires and coaxial cables from antennas. The LH VHF I transceiver antenna is located up on the fuselage between frames No.7 and 8. The RH VHF II transceiver antenna is located down on the fuselage between frames no.6 and 7. The installation also includes a circuit-breaker and a fuse through the power is supplied to the transceiver and a rocker-type switch on the control wheel by means of which the transceiver is switched to the transition mode. The VHF I and INTERCOM I are fed directly from the storage battery if connected to on external power source. It is prevent from being damage if the external source characteristics are not suitable.
2. List of components No.
Name
1.
Circuit breaker VHF I / NAV I and VHF II
2.
VHF transceiver
3.
Antenna
NOTE:
Type (Dwg. No.)
Qty
Location
AZRGK 10
1+1
KY 196 A
1
KY 165 A
1
5 QK 40516
1
Up between frames No. 7 and 8
1
Down between frames No. 6 and 7
Overhead panel
Rear control panel
Description and operation KX 165A transceiver – see chapter 034
3. Operation The transceiver is put into readiness for operation by switching the switches BATTERY I, II, VHF II, VHF I / NAV I and INTERCOM I, II circuit-breakers on the overhead panel. To turn on, rotate the OFF, PULL TEST knob clockwise. This knob serves moreover to set the listening level (rotating the knob left and right) and for audio test (pull out position of the volume control knob).Audio for headphones is selected by COM 1 and COM 2 push-buttons PHONE or for 2 loudspeakers placed near overhead control panel by push-button SPEAKER. The rotary switch on the right side of the audio selector box selects the desired transmitter which will be use for the transmission (position 1 or 2). The transceivers work permanently in a reception mode. The transmission mode is turned on by pressing the INT.-VHF switch on the control wheel on the sinusoid-marked side. A light “T” will appear between the “USE” and “STBY” EFFECTIVITY
023.12.00
L 410 UVP-E9
Page: 2001 Nov 1/11
MAINTENANCE MANUAL displays on the transceiver in transmission mode. Under normal operating conditions the reception and transmission modes are independent for both pilots.
FIG. 2001
BLOCK DIAGRAM VHF COMMUNICATION PASSENGER ADDRESS
EFFECTIVITY
023.12.00
L 410 UVP-E9
Page: 2002 Nov 1/11
MAINTENANCE MANUAL VHF COMMUNICATION DESCRIPTION AND OPERATION 1. General The Very High Frequency (VHF) Communication (VHF COM) system is used for voice communication between aircraft and/or aircraft and a ground station. The aircraft is equipped with two VHF transceivers (KY 196 A and KX 165 A). A navigation system forms part of KX 165 A transceiver. The transceivers are located on the rear control panel. Connected to the transceivers are power and control wires and coaxial cables from antennas. The LH VHF I transceiver antenna is located up on the fuselage between frames No.7 and 8. The RH VHF II transceiver antenna is located down on the fuselage between frames no.6 and 7. The installation also includes a circuit-breaker and a fuse through the power is supplied to the transceiver and a rockertype switch on the control wheel by means of which the transceiver is switched to the transition mode. The VHF I and INTERCOM or INTERCOM I are fed directly from the storage battery if connected to on external power source. It is prevent from being damage if the external source characteristics are not suitable.
2. List of components No.
Name
1.
Circuit breaker VHF I / NAV I and VHF II
2.
VHF transceiver
3.
Antenna
NOTE:
Type (Dwg. No.)
Qty
Location
AZRGK 10
1+1
KY 196 A
1
KX 165 A
1
5 QK 40516
1
Up between frames No. 7 and 8
1
Down between frames No. 6 and 7
Overhead panel
Rear control panel
Description and operation KX 165A transceiver – see chapter 034
3. Operation The transceiver is put into readiness for operation by switching the switches BATTERY I, II circuit breakers VHF I / NAV I, VHF II and INTERCOM or INTERCOM I, II circuit-breakers on the overhead panel. To turn on, rotate the OFF, PULL TEST knob clockwise. This knob serves moreover to set the listening level (rotating the knob left and right) and for audio test (pull out position of the volume control knob). Audio for headphones is selected by COM 1 and COM 2 push-buttons PHONE or for 2 loudspeakers placed near overhead control panel by push-button SPEAKER. The rotary switch on the right side of the EFFECTIVITY L 410 UVP-E20
023.12.00 Page: 3001 May 30/14
MAINTENANCE MANUAL audio selector box selects the desired transmitter which will be use for the transmission (position 1 or 2). The transceivers work permanently in a reception mode. The transmission mode is turned on by pressing the INT.-VHF switch on the control wheel on the sinusoid-marked side. A light “T” will appear between the “USE” and “STBY” displays on the transceiver in transmission mode. Under normal operating conditions the reception and transmission modes are independent for both pilots.
FIG. 3001
BLOCK DIAGRAM VHF COMMUNICATION PASSENGER ADDRESS (THE VARIANT WITH ONE CIRCUIT BREAKER INTERCOM)
EFFECTIVITY L 410 UVP-E20
023.12.00 Page: 3002 May 30/14
MAINTENANCE MANUAL
FIG. 3002
BLOCK DIAGRAM VHF COMMUNICATION PASSENGER ADDRESS (THE VARIANT WITH TWO CIRCUIT BREAKERS INTERCOM I, II)
EFFECTIVITY L 410 UVP-E20
023.12.00 Page: 3003 May 30/14
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY L 410 UVP-E20
023.12.00 Page: 3004 May 30/14
MAINTENANCE MANUAL LUN 3524.13 TRANSCEIVER DESCRIPTION AND OPERATION 1. Purpose The LUN 3524.13 transceiver is intended for communication with ground station or other aircrafts.
2. Technical data Technical characteristics of the LUN 3524.13 transceiver are shown in the LUN 3524.13 transceiver maintenance manual.
3. Operation The operation of the LUN 3524.13 transceiver is described in detail in LUN 3524.13 transceiver maintenance manual.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1001 Nov 1/11
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1002 Nov 1/11
MAINTENANCE MANUAL
LUN 3524.13 TRANSCEIVER SERVICING 1. Check of VHF transceiver A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B Periodical
E.
Procedures (1) Check of external appearance – refer to the work procedure chart 023.12.01.B-1 (2) Check of AVC function – refer to the work procedure chart 023.12.01.B-2 (3) Receiver gain – refer to the work procedure chart 023.12.01.B-3 (4) Receiver sensitivity – refer to the work procedure chart 023.12.01.B-4 (5) Function of squelch – refer to the work procedure chart 023.12.01.B-5 (6) Output performance of the transceiver – refer to the work procedure chart 023.12.01.B-6 (7) Ability of modulation – refer to the work procedure chart 023.12.01.B-7 (8) Distortion of the audio signal – refer to the work procedure chart 023.12.01.B-8 (9) Monitoring – refer to the work procedure chart 023.12.01.B-9 (10) Carrier frequency – refer to the work procedure chart 023.12.01.B-10
2. Check of external appearance A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Magnifying glass with five-powered enlargement
D. Referenced information
023.12.01.B-1 Periodical
E.
Procedures (1) Workplace must have natural or artificial illumination, in accordance with valid rules for assembly workshops.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1301 May 30/14
MAINTENANCE MANUAL (2) One must check completeness of all parts of the VHF transceiver, of the surface finish, if individual parts of the VHF transceiver are not apparently damaged or if they do not bear traces of damage, caused by assembly or check. Further one must check panel illumination, inscription make, label make, arrest of commutators and switches. (3) Carry out a check of completeness and non-damage, see point 2 (4) Put the workplace into initial state.
3. Check of AVC function A.
Fixture, Test and Support Equipment
Z 763 Device for VHF transceiver test G4 017 HF generator V3-38 LF milivoltmetr C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories (YE-2T) S6-5 Frequency-meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-2 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to Fig.1301 DC current source
Volt-ampere-meter
Device for VHF transceiver test
Frequency meter
LF millivoltmetr
HF generator
FIG. 1301
LUN 3524.13
SCHEME OF TESTING DEVICE
(2) With connecting cord connect the VHF transceiver LUN 3524.13 to the device for testing of VHF transceiver. The antenna connector of VHF transceiver LUN 3524.13 connect with HF-coaxial cable to EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1302 Nov 1/11
MAINTENANCE MANUAL HF-outlet of the generator. Connect frequency meter and LF millivoltmeter to LH outlet clip. Button “LOAD” switch into “150Ω” position. Connect power source of DC current into “+28V” clip and a voltmeter parallel to source clips. (3) Switch on all instruments except the power source of the VHF transceiver and keep them on for half an hour. (4) AVC function check Output voltage may be in range (1.22 + 12.25 )V while input HF-voltage may change in range (10 + 10000)µV. (5) Switch “Noise -off” in optional position Plug in DC current source (28±1)V and after 5 minutes of feeding the VHF transceiver put from VF generator 127.5 MHz signal level of (20±5) µV modulated by (1000±50) Hz frequency with modulation depth of (30+5)%. Through volume regulator set receiver amplification to output voltage of 3.88 V ±10%. Keep changing the input signal in (10+10000) µV range, the output voltage of the receiver must change in (1.22+12.25)V range. (6) Put the measuring workplace into initial state NOTE:
Do not carry out if further measurement according to point 23.12.01.B-3 shall immediately follow.
4. Receiver gain A.
Fixture, Test and Support Equipment
Z 763 Device for VHF transceiver test G4 107 HF generator V3-38 LF milivoltmetr C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories for exangle
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-3 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-2 para 1, 2, 3.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1303 Nov 1/11
MAINTENANCE MANUAL NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-2 work procedure chart.
(2) Check of receiver gain On input signal level of (20±5)µV there must be the low-frequency voltage in receiver output greater than 3.88 V. (3) Switch “Noise -off” in optional position Plug in DC current source (28±1)V (feeding the VHF transceiver) through volume regulator set the LF volume to the maximum. On input HF-signal of 20µV modulated by 1 kHz frequency with (30+5)% modulation depth there must be a voltage greater than 3.88V on receiver output. Measure on frequencies 118.00 MHz, 127.500 MHz and 135.975 MHz. (4) Put the measuring workplace into initial state NOTE:
Do not carry out if further measurement according to point 23.12.01.B-4 shall immediately follow.
5. Receiver sensitivity A.
Fixture, Test and Support Equipment
Z 763 Device for VHF transceiver test G4 107 HF generator V3 38 LF milivoltmetr C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-4 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-2 para 1, 2, 3. NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-2 work procedure chart.
(2) Check of receiver sensitivity On input signal level of 5 µV there must be output voltage with signal 2x greater at minimum than the output voltage without signal.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1304 Nov 1/11
MAINTENANCE MANUAL (3) Set the volume regulator to maximum. Plug in DC current source (28+1)V (transceiver feeding). The switch “Noise -off” in Noise position. On receiver input put in from HF generator a signal modulated by (1000±50)Hz frequency with modulation depth of (30+5)% and of (5-0.5)µV level. Record the output voltage. Switch off the modulation and record the output voltage. The ratio of added output voltage with modulation and without modulation to voltage without modulation must be greater than 2:
U mod + Unoise ≥2 Unoise Measure at 118.000 MHz, 127.500 MHz, 135.975 MHz frequencies. NOTE:
Output voltage of the receiver must be in (1.84+7.75)V range.
(4) Put the measuring workplace into initial state NOTE:
Do not carry out if further measurement according to point 23.12.01.B-5 shall immediately follow.
6. Function of squelch A.
Fixture, Test and Support Equipment
Z 763 Device for VHF transceiver test G4 107 HF generator G3 34 LF generator V3 38 LF milivoltmetr C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-5 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-2 para 1, 2, 3. NOTE: Do not carry out if it follows immediately after measurement of 23.12.01.B-4 work procedure chart. (2) Action of squelch Squelch must operate within (4+8)µV range.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1305 Nov 1/11
MAINTENANCE MANUAL (3) Plug in DC current source (28±1)V (transceiver feeding), the switch “Noise-off” on transceiver panel set to OFF position. Set the VOLUME regulator to maximum. On receiver input put in a HF signal 127.5 MHz, modulated by (1000±50) Hz frequency with modulation depth of (30+5)%. The output voltage must not turn out under input HF signal lower than 4µV. Increase the input HF signal to 8µV level, the output voltage must appear on the receiver output by a jump. Make the measurement at 118.000 MHz and 135.975 MHz frequencies. (4) Put the measuring workplace into initial state. NOTE: Switch off all instruments from the mains and the transceivers from DC current source.
7. Output performance of the transceiver A.
Fixture, Test and Support Equipment
ITM 5 Modulation depth meter Z 763 Device for VHF transceiver test G3 34 LF generator V3 38 LF milivoltmetr S6 5 Distortion meter 2pcs Ch 3-54 Frequency meter C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-6 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to scheme – see Fig.1302
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1306 Nov 1/11
MAINTENANCE MANUAL
DC current source
Volt-ampere-meter
Distortion meter
Device for VHF Frequency meter
transceiver test
LUN 3524.13
LF millivoltmetr
Modulation
Distortion
depth
meter
Frequency meter
FIG. 1302
SCHEME OF CHECKING –MEASURING SET
(2) To clips of device for transceiver test connect LF generator. Disconnect high-frequency coaxial cable from HF generator and connect in to modulation depth meter instrument. To antenna current meter connect distortion and frequency meter. (3) Plug in all instruments but transceiver power source and keep them on for half an hour. (4) Check of output performance of the transceiver. (5) Transmitter output power must be 16W (that is 0.565 A at 50Ω) at the minimum. (6) According to work procedure chart 23.12.01.B-6, para. 1, 2 Plug in DC current source (28±1)V (transceiver feeding) on frequencies 118.000 MHz, 127.500 MHz and 135.975 MHz without transmitter modulation measure the output power that must be 16W at the minimum (minimum 0.565 A and 50 Ω). The button on device for transceiver test must be in “pushed” position. NOTE:
Maximum transmitting time 2 min. reception time 18 minutes (transmission – reception change ratio 9:1).
(7) Put the measuring workplace into the initial state. NOTE:
Do not carry out if further measurement according to work procedure chart 23.12.01.B-7 shall follow immediately.
EFFECTIVITY L 410 UVP-E
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MAINTENANCE MANUAL
8. Ability of modulation A.
Fixture, Test and Support Equipment
ITM 5 Modulation depth meter Z 763 Device for VHF transceiver test G3 34 LF generator C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories (YE-2T)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-7 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-6 para 1, 2. NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-6 work procedure chart.
(2) Transmitter ability of modulation The transmitter must be able of 85% depth of modulation by input voltage up to 250mV. (3) Plug in DC current source (28±1)V (transceiver feeding), push the button on the testing device for transceiver test to “TRANSMISSION” position. Through modulation voltage of maximum range 250mV (from generator connected to the clip) and of 1 kHz frequency from LF generator must be reached modulation depth of minimum 85% on 127.500 MHz frequency. NOTE:
Maximum transmitting time 2 min. reception time 18 minutes (transmission – reception change ratio 9:1).
(4) Put the measuring workplace into the initial state. NOTE:
Do not carry out if further measurement according to work procedure chart 23.12.01.B-8 shall follow immediately.
EFFECTIVITY L 410 UVP-E
023.12.01 Page: 1308 Nov 1/11
MAINTENANCE MANUAL
9. Distorting of audio signal A.
Fixture, Test and Support Equipment
Z 763Device for transceiver test ITM 5 Modulation depth meter G3 34 LF generator S6 5 Distortion meter C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories (YE-2T)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-8 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-6 para.1, 2. NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-7 work procedure chart.
(2) Check the distortion of the audio signal Distortion and noise level of demodulated transmitter audio signal must not exceed 25%, under 1 V input signal the distortion must not be greater than 35%. (3) According to work procedure chart 23.12.01.B-6, para. 1, 2 (4) Measure at 127.500 MHz frequency. Plug in DC power source (20±1)V (transceiver feeding). Push the button TRANSMISSION on the test device board. Modulate the transmitter through 1 kHz frequency up to modulation depth (85±3)% and record the needed level of modulation voltage. Measure the distortion after the demodulation of transmitter output voltage. Then modulate the transmitter through 350 Hz ±10% and 2500 Hz ±10% with LF signal input level equaling that of 1 kHz frequency modulation and after demodulation measure the distortion. It may not be greater than 25%. Repeat the measurement at (1±0.1)V modulation signal level. At this signal level the distortion may not be greater than 35%. NOTE:
Maximum transmitting time 2 min. reception time 18 minutes (transmission – reception change ratio 9:1).
(5) Put the measuring workplace into the initial state NOTE:
Do not carry out if further measurement according to work procedure chart 23.12.01.B-9 shall follow immediately.
EFFECTIVITY L 410 UVP-E
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MAINTENANCE MANUAL
10. Monitoring A.
Fixture, Test and Support Equipment
ITM 5 Modulation depth meter Z 763 Device for VHF transceiver test G3 34 LF generator C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories (YE-2T) S6 5 Distortion meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-9 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-6 para.1, 2 NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-8 work procedure chart.
(2) Check of monitoring At modulation signal frequency varying from 350 Hz ±10% to 2500 Hz ±10% the output voltage must vary in (1.94+12.25)V band. The minimum output must be 25mV on resistance 150Ω (Ohms) at modulation frequency 1 kHz and modulation depth (85±5)% (output 25mV on resistance 150Ω corresponds to 1.94 V voltage). Send to repair factory if the technical requirements are not met. (3) According to work procedure chart 23.12.01.B-6, para. 1, 2. (4) Measure at 127.500 MHz frequency, volume regulator on the maximum. Plug on DC power source +28 V (transceiver feeding). Push the button TRASMISSION on testing device board. Modulate the transmitter through 1kHz frequency with modulation depth of 85%. The output voltage corresponding to minimum output of 25 mW must be greater than 1.94 V on resistance 150Ω (Ohms). At modulation frequency varying from 350 Hz to 2500 Hz the output voltage must be in (1.94+12.25)V band. NOTE:
Maximum transmitting time 2 min. reception time 18 minutes (transmission – reception change ratio 9:1).
(5) Put the measuring workplace into the initial state
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Do not carry out if further measurement according to work procedure chart 23.12.01.B-10 shall follow immediately.
11. Check carrier frequency A.
Fixture, Test and Support Equipment
Ch3 54 Frequency meter C43 17 Volt-ampere-meter YE 2T DC current source 0-30V/10A plus accessories (YE-2T)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.B-10 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 23.12.01.B-6 para.1, 2 NOTE:
Do not carry out if it follows immediately after measurement of 23.12.01.B-8 work procedure chart.
(2) Check of carrier frequency -5
Frequency deviation from the chosen channel may not be greater than 2.5x10 . According to work procedure chart 23.12.01.B-6, para. 1, 2. Plug in DC power source (28±1)V (transceiver feeding). Push the button TRASMISSION on testing device board. Put the transmitter in action without modulation on frequencies 118.00 MHz, 127.500 MHz and 135.975 MHz. Measure the frequency deviation from the -5
frequency of chosen channel that shall not be greater than 2.5x10 of the measured channel. Note:
Maximum transmitting time 2 min. reception time 18 minutes (transmission – reception change ratio 9:1).
(3) Put the measuring workplace into the initial state. Cut off all instruments, the transceiver and DC power source.
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12. Check the correct connection of the aerial cables to the station A.
Fixture, Test and Support Equipment
No.697 6x120 screwdriver
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.01.C Periodical
E.
Procedures (1) Remove the left pilot’s seat (see section 025) (2) Disassemble the left side coverings of the rear control panel by screwing off 12 special screws by means of a screwdriver No.697-6x120. (3) Check the correct connection of the aerial cables to the station. (4) Set on the left side coverings of the rear central panel by screwing off 12 special screw by means of a screwdriver No. 697-6x120. (5) Set back the left side of the cockpit and the left pilot’s seat (see section 025).
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LUN 3524.13 TRANSCEIVER REMOVAL / INSTALLATION 1. Removal and installation of the transceiver LUN 3524.13 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Binding wire Ø 0.8mm
C. Tools
Screwdriver No.713 6.5x130
D. Referenced information
023.12.01.A Periodical
E.
Procedures (1) Disassemble the left and the right side coverings of the rear control panel by screwing off 12 special screws by means of screwdriver No. 713 6.5x130. (2) Check if all circuit breakers have been switched off at the overhead panel (3) Disconnect the 2 cabling sockets (4) Dismount the 2 pcs of transceivers by screwing off 8 screws by means of a screwdriver No.713 6.5x130 and draw them upwards. (5) Give the transceivers over to the laboratory (6) After having the transceivers back from the laboratory carry out their installation. (7) Set on the transceivers on the panel of the rear control panel and fix them by 8 screws by means of screwdriver No.713 6.5x130. (8) Connect the cabling sockets and secure them by binding wire against loosening (9) Set on the left and right side coverings of the rear central panel by screwing in of 12 pcs special screws by means of a screwdriver No.713 6.5x130.
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MAINTENANCE MANUAL KY 196A TRANSCEIVER DESCRIPTION AND OPERATION 1. Purpose The KY 196A transceiver is intended for communication with ground stations or other aircrafts.
2. Technical data Technical characteristics of the KY 196A transceiver are shown in the KY 196 A transceiver maintenance manual
3. Operation The operation of the KY 196A transceiver is described in detail in the KY 196 A transceiver maintenance manual.
FIG. 2001
KY 196 A TRANSCEIVER 1–
ON/OFF Volume Control Knob with detent “off” position (for audio test pull the volume control knob “cut”).
2–
Concentric frequency selector knobs (the outer larger knob changes the MHz portion of the frequency, the smaller inner knob causes changes of the kHz portion in 50 kHz steps when pushed “in” and 25 kHz when pulled “out”).
3–
The transfer button to activate the new frequency (by pressing the transfer button the frequency in the “STBY” window change with the frequency in the “USE” window and this new frequency tunes the radio for operation).
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MAINTENANCE MANUAL KY 196A TRANSCEIVER DESCRIPTION AND OPERATION 1. Purpose The KY 196A transceiver is intended for communication with ground stations or other aircrafts.
2. Technical data Technical characteristics of the KY 196A transceiver are shown in the KY 196 A transceiver maintenance manual
3. Operation The operation of the KY 196A transceiver is described in detail in the KY 196 A transceiver maintenance manual.
FIG. 3001
KY 196A TRANSCEIVER 1–
ON/OFF Volume Control Knob with detent “off” position (for audio test pull the volume control knob “cut”).
2–
Concentric frequency selector knobs (the outer larger knob changes the MHz portion of the frequency, the smaller inner knob causes changes of the kHz portion in 50 kHz steps when pushed “in” and 25 kHz when pulled “out”).
3–
The transfer button to activate the new frequency (by pressing the transfer button the frequency in the “STBY” window change with the frequency in the “USE” window and this new frequency tunes the radio for operation).
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5 QK 405 16 OR CI 268-5 ANTENNA DESCRIPTION AND OPERATION 1. Purpose The 5 QK 405 16 and/or CI 268-5 antenna is intended for the installation in aircrafts.
2. Technical data Basic technical data of the 5 QK 405 16 Antenna: Frequency range
100 - 150 MHz
Impedance RF
50 Ω (Ohms)
Basic technical data of the CI 268-5 Antenna: Frequency range
118 - 137 MHz
Impedance RF
50 Ω (Ohms)
3. Description Description of the 5 QK 405 16 Antenna: The antenna consists of a rod-type horizontal emitter and a basic vertical emitter. The two emitters are separated by an insulating element. Power is supplied by means of a coaxial connector situated on the mounting surface of the antenna. The hollow space inside the antenna houses a compensating circuit controlling the inherent impedance of the antenna. The compensating circuit consists of an inductance (a short length of a coaxial short-circuited line), a certain length of radio frequency coaxial cable and a mechanical support. The horizontal emitter is galvanically connected with the airframe. Description of the CI 268-5 Antenna: The antenna consists of super-tough nickel plated aluminium base plate with integral Nitrile O-ring and with a built-in notch filter, that allows installation in close proximity to GPS antennas without co-sight interference.
4. Operation The antenna transmits (receives) mostly vertically polarized electromagnetic energy in frequency bands from 100 to 150 MHz - valid for the 5 QK 405 16 Antenna and/or 118 to 137 MHz - valid for the CI 268-5 Antenna. It is adapted for a connection to a coaxial cable with impedance of 50 Ω (Ohms).
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5 QK 405 16 OR CI 268-5 ANTENNA SERVICING 1. Inspection of the antenna A.
Fixture, Test and Support Equipment
Steps (e.g. B097343N)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.02.A Periodical
E.
Procedures (1) Place the steps (e.g. B097343N) to the aircraft. (2) Check the antenna. The following defects are not permitted: bent horizontal emitter, damaged insulating element, loosened antenna or insulating element.
2. Check of the correct connection of the cable to the antenna A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
L 410.9141-05 screwdriver
D. Referenced information
023.12.02.B Periodical
E.
Procedures (1) Using the L 410.9141-05 screwdriver, open the ceiling upholstery in the passenger cabin between frames No. 7 and 12. (2) Remove the left pilot’s seat (refer to the Chapter 025) and floor panels on the left side of the cockpit. (3) Check whether the cable connectors at the antenna are properly connected, tightened and locked. (4) Reset the ceiling upholstery panels in the passenger cabin between frames No. 7 and 12 and lock them with the L 410.9141-05 screwdriver. (5) Set back the floor panels on the left side of the cockpit and the left pilot’s seat (refer to the Chapter 025).
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3. Inspection of the antenna A.
Fixture, Test and Support Equipment
Steps (e.g. B097343N) B961765N Assembly bogie or equivalent
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.12.02.C Periodical
E.
Procedures (1) Place the steps (e.g. B097343N) and B961765N assembly bogie (or equivalent) to the aircraft (2) Inspection of the bottom and upper communication antenna. The following defects are not permitted: •
bent horizontal emitter
•
damaged insulating element
•
loosened antenna or insulating element
(3) By using the steps (e.g. B097343N) go up on top side of the fuselage and check the upper antenna. Make sure that none of the defects listed in step (2) are present. (4) By using the B961765N assembly bogie check the bottom antenna. Make sure that none of the defects listed in step (2) are present. (5) Remove the steps and assembly bogie.
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5 QK 405 16 OR CI 268-5 ANTENNA REMOVAL / INSTALLATION 1. Removal and installation of the communication antenna A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Necessary tools from the tool kit
D. Referenced information
-
E.
Procedures (1) Antenna removal (a) Remove the ceiling upholstery panels between frames No. 7 and 12. (b) Remove the left pilot’s seat (refer to the Chapter 025) and floor panels on the left side of the cockpit. (c) Disconnect the coaxial cable from the antenna. (d) Unscrew the screws attaching the antenna. (e) Remove the antenna. (2) Antenna installation (a) Apply LUKOPREN compound to the seating of the antenna. Fasten the antenna to the aircraft. Tighten the screws thoroughly. Repair the damaged painting around the antenna. (b) The antenna must be perfectly electrically bonded to the aircraft skin by means of the fastening screws. NOTE:
The maximum permissible transition resistance between the antenna and the fuselage is 600 µΩ (micro Ohms).
(c) Connect the coaxial cable from the transceiver to the antenna outlet. (d) Attach the upholstery panels. (e) Set back the floor panels on the left side of the cockpit and the left pilot’s seat. (refer to the Chapter 025).
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5 QK 405 01 ANTENNA DESCRIPTION AND OPERATION 1. Purpose The 5 QK 405 01 antenna is intended for the installation in aircrafts.
2. Technical data Frequency range
100 - 150 MHz
Impedance
50 Ω (Ohm)
3. Description The antenna consists of a rod-type horizontal emitter and a basic vertical emitter. The two emitters are separated by an insulating element. Power is supplied by means of a coaxial connector situated on the mounting surface of the antenna. The hollow space inside the antenna houses a compensating circuit controlling the inherent impedance of the antenna. The compensating circuit consists of an inductance (a short length of a coaxial short-circuited line), a certain length of radio frequency coaxial cable and a mechanical support. The horizontal emitter is galvanically connected with the airframe. The passive element is situated behind the antenna which modulates characteristics of antenna.
4. Operation The antenna transmits (receives) mostly vertically polarized electromagnetic energy in frequency bands from 100 to 150 MHz. It is adapted for a connection to a coaxial cable with an impedance of 50 Ω (Ohm)
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5 QK 405 01 ANTENNA SERVICING 1. Inspection of the 5 QK 405 01 antenna A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Emery paper No.400 C1005/0080 Varnish red colour
C. Tools
Screwdriver No.697 6x120 Hydraulic raising platform
D. Referenced information
023.12.03.A Periodical
E.
Procedures (1) Put the hydraulic raising platform to the fin (2) Remove the laminated-plastic antenna cover located on the top of the fin unscrewing 24 screw by means of a screwdriver No. 697-6x120. (3) Remove the blind flange in the antenna unscrewing 2 screw by means of a screwdriver No. 697-6x120. (4) Check the antenna 5 QK 405 01. The following defects are not permitted: loosen screws, cracked and split insulating element or its loosen, loosen Z-V bond. (5) Check the antenna and make sure that none of the defects listed in para. 4 are present. NOTE:
Check tightened the Z-V bond using hand run in the hollow by the antenna.
(6) Reinstall the blind flange to hollow, laminated-plastic antenna cover screwing 24 screws by means of a screwdriver No. 697-6x120. Clean the earthing bond with emery paper No.400 and for screwing and tightening screws painted with C1005/0080 varnish red colour. (7) Remove the hydraulic raising platform
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5 QK 405 01 ANTENNA REMOVAL / INSTALLATION 1. Removal and installation of the 5 QK 405 01 antenna A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Spanners and screwdrivers of appropriate size from the tool kit
D. Referenced information E.
-
Procedures (1) Antenna removal (a) Remove the laminated-plastic antenna cover unscrewing 24 screw by means of a screwdriver No. 697-6x120. (b) Unscrew the eight screws attaching the antenna and throw the antenna up (c) Disconnect the coaxial cable from the antenna. (2) Antenna installation (a) Clean the surface under the screws of the antenna. (b) Connect the coaxial connector to the antenna (c) Screw down the antenna with 8 screws. (d) Set up the laminated-plastic antenna cover. Screw down the cover periphery with the screws. NOTE:
The maximum permissible transition resistance between the antenna and the fuselage is 600 µΩ (Ohm).
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PASSENGER ADDRESS AND ENTERTAINMENT DESCRIPTION AND OPERATION 1. General The passenger address system forms part of the intercommunication system and it’s description and operation is shown in section 023.40.00. The entertainment system can be optionally installed on the aircraft: •
PXE 7300 In-Flight Entertainment System (if installed) (refer to 023.31.00)
•
FD 932DVD-LP In-flight Entertainment System (if installed) (refer to 023.32.00)
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PXE 7300 IN-FLIGHT ENTERTAINMENT SYSTEM (if installed) DESCRIPTION AND OPERATION 1. General The High-Fidelity Stereo In-Flight Entertainment System with MP3/CD Player and FM/AM Radio Receiver PXE 7300 can be optionally on the airplane. The unit with control elements is located on the RH instrument panel. It also contains a high-fidelity stereo amplifier to provide the entertainment output to the aircraft audio system. Switching of the entertainment output is performed with COM4 and PA knobs on the audio control box located on the rear control panel. An 8-digit LED display of the PXE 7300 unit provides information about the systems modes and media in use. The display is automatically adjusted for ambient light conditions by a photocell. The PXE 7300 can save up to nine AM and nine FM frequencies for future recall. Frequencies can be tuned in the AM range 530 - 1710 kHz per 10 kHz steps and in the FM range 87.7 - 107.9 MHz per 200 kHz steps. The included passive AM/FM antenna is optimized for FM radio performance. Therefore, when used for AM reception, the operator may only receive the most powerful 3 to 5 AM stations. For optimum performance, the external FM/AM antenna is installed.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1
CD/MP3 player
PXE 7300
1
RH instrument panel
2
Circuit breaker IFE
AZRGK 5
1
overhead panel
3
Fuse
F/4.0A 1500A EN60127-2
1
fuse panel
4
Fuse
F/2.0A 1500A EN60127-2
1
fuse panel
5
Over-switch
1TL1-1
1
Rear control panel
6
Amplifier
17001-28v
1
frame 5a
7
Antenna
-
1
cockpit
8
Relay
TKE 52 PODGB
2
between frames 6 and 7
3. Description The PXE7300 System is a single panel mounted unit that contains a CD player with MP3 media capability and an AM/FM radio receiver. It also contains a high-fidelity stereo amplifier to provide the entertainment output to the aircraft audio system.
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4. Operation Operation and using in flight are described in Flight Manual.
FIG. 1
PXE 7300 - FRONT CONTROL PANEL
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PXE 7300 IN-FLIGHT ENTERTAINMENT SYSTEM (if installed) SERVICING 1. Check of PXE 7300 IFE system (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Insert disc, and verify that the player accepts the disk with about 1/2 of the diameter in the unit. The player should pull the disk smoothly and drop into place. (2) The player will begin to play, automatically about 20 seconds (after reading the disc). (3) If the unit is in disc mode, with CD inside at power-up, it will play (after reading the disc). (4) Verify that all Disc modes operate. (5) Push the “Eject” button and verify that the disc is ejected within about 10 seconds. (6) Verify radio operation on AM and FM (7) Verify that aux. Audio is presented to the output (if connected). (8) Evaluate the audio interface to be certain that the IFE audio is muted during intercom and radio communication. (a) If muting override is provided, evaluate the switch location and verify operation. (b) Evaluate the audio performance (c) Evaluate the audio level to verify that the music is adequate under flight conditions. (d) Evaluate the muting system to demonstrate that the music will be adequately muted if desired, by radio and intercom. (e) Evaluate the muting override control if equipped. (9) Evaluate failure remediation from crewmember location (a) Turn unit off (b) Locate and pull unit circuit breaker
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MAINTENANCE MANUAL (c) With the disc playing, with minimum volume, listen to the following audio sources (as equipped), adjusted to normal listening level: •
Comm 1, comm. 2, comm. 3, HF
•
Nav 1, Nav 2
•
ADF (1 and 2)
•
DME (1 and 2)
•
Marker
•
Any other audio sources
(10) Select FM Mode, and repeat step 6, listening for interference on the aircraft audio sources. Pay particular attention to the frequencies listed in table. FM
COM
107.3
118.000
107.5
118.200
107.7
118.400
107.9
118.600
FM/COM Cross Reference (11) Select AM Mode, and repeat step 6, listening for interference on the aircraft audio sources. (12) Select COM 1 for transmit. Tune COM 1 to 118.00, and the PXE7300 to 107.3 MHz. Transmit a test count and evaluate the unit display and audio output for inconsistencies (13) Repeat step 10 for COM 2, and other transmitters. (a) Tune Nav 1 to local station and perform a standard VOT test in accordance with 14 CRF 91.171. (b) Note the indicated VOR bearing on both systems. (c) Turn the PXE7300 on and off, and observe any change in the VOR indication that could be attributed to the PXE7300. NOTE:
For more detail information than is mentioned in this supplement see PXE 7300 IFE System Operation Manual P/N 200-973-0005 · Rev. 9 - April 2006 or later applicable version.
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FD932DVD-LP IN-FLIGHT ENTERTAINMENT SYSTEM (if installed) DESCRIPTION AND OPERATION 1. General The High-Fidelity Stereo In-Flight Entertainment System with DVD/CD/MP3 Player FD932DVD-LP (28V) or FD932DVD-LP-2 and 32” widescreen LCD FD 320CV is installed in the airplane. The DVD/CD/MP3 Player with control elements is located on the RH instrument panel and the FD320CV widescreen LCD th
is installed on the 7 bulkhead in the passenger cabin. The system also contains a high-fidelity stereo amplifier to provide the entertainment output to the aircraft audio system and to 19 passenger’s headphones connection places with the individual volume control.
2. List of components No.
Name
Qty
Location
1
IFE Circuit breakers DVD LCD
AZRGK 5
2
Overhead panel
2
Circuit breaker
KLIXON 7274-2-1
1
Circuit breakers panel
3
DVD/CD/MP3 Player
FD 932 DVD-LP or FD 932 DVD-LP-2
1
Right instrument panel
4
Flight display system
FD 320 CV (95213211)
1
Between frames 7 and 8
5
Amplifier
NAT MODEL 240 (95219610)
1
Between frames 6 and 7, right
6
Video amplifier
DAPS321 (95219627)
1
Between frames 5 and 6, right
7
Switch
1TL1-1
1
Rear control panel
8
Relay
B 073 576 N
2
Between frames 6 and 7, RH
9
Power filter
--
1
Between frames 4 and 5, behind instrument panel
10
Socket
CAN9 ZG (91619105)
12
In passenger compartment
11
Socket
CAN9 VG (91619106)
12
In passenger compartment
12
Headphones
AIR-LAND II (95235111) or AS-101 (95235114)
20
In passenger compartment
13
Phone stereo jack
SCJ-0354-5PU (92218206)
19
In passenger compartment
14
Potentiometer
PC1622NK010 (90770002)
19
In passenger compartment
15
Knob
PS1517SS (95032286)
19
In passenger compartment
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3. Operation Switching of the entertainment output is performed with COM4 and PA knobs on the audio control boxes located on the rear control panel. The volume and chosen program can be checked either pilot or copilot depending on the position of the IFE / PILOT OFF CO-PILOT switch located on the rear control panel through their headphones. An LED display of the DVD/CD/MP3 player provides information about the systems modes and media in use. The DVD/CD/MP3 player can use the “internal” media source (DVD or CD) or the external source through inputs on the front panel. The selection of these inputs is performed by using the MODE button on the front panel or by using the IR remote control. The display is automatically adjusted for ambient light conditions by a photocell. The DVD/CD/MP3 player will begin to play automatically when a disc is inserted. Pushing the upper or bottom part of the VOLUME knob will increase or decrease the volume. It is recommended to set the VOLUME knob of the FD932DVD-LP or FD932DVD-LP-2 unit to the maximum volume setting for correct passenger listening. The volume and chosen program can be checked either pilot or co-pilot depending on the position of the IFE / PILOT OFF CO-PILOT switch located on the rear control panel through their headphones. When a new disc is inserted, the display will show “Reading…” for up to 20 seconds, depending on the media and amount of information contained. The 19 passenger headphones connection places are located in the aircraft according to the fig. 3. Operation and using in flight are described in Flight Manual.
CAUTION:
ONLY THE HEADPHONES WITH THE IMPEDANCE EQUAL OR MORE 300 Ω CAN BE CONNECTED INTO THE PASSENGER’S HEADPHONES CONNECTION PLACES.
FIG. 1
FD932DVD-LP - FRONT CONTROL PANEL
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FIG. 2
FD932DVD-LP-2 - FRONT CONTROL PANEL
FIG. 3
PASSENGER HEADPHONES CONNECTION PLACES
NOTE:
a.
Double-seats connection places
b.
Single-seats connection places
For more detail information than is mentioned in this supplement see: - FD932DVD-LP (28V) DVD/CD/MP3 Player Installation and Operation Manual, 2006 or later applicable version. - FD932DVD-LP-2 Low-ProfileDVD/CD/MP3 Player Installation and Operation Manual, Rev F, Rev Date 07/19/2011 or later applicable version. - FD320CV Widescreen LCD Installation and Operation Manual, Rev. A, Jan 2007 or later applicable version.
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INTERCOMMUNICATION DESCRIPTION AND OPERATION 1. General The intercommunication system is used for intercommunication of the aircraft crew members. It allows also connection of the passenger address system.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Audio selector box
LUN 3591.11 or LUN 3591.13
2
Rear control panel
2.
Connection box
LUN 3591.22 or LUN 3591.23
2
Adjacent to the overhead panel
1
Between frames No.8 and 9 LH (if installed)
3.
Circuit breaker INTERCOM I, II
AZRGK 2
2
Overhead panel
4.
Circuit breaker PA (if installed)
AZRGK 2
1
Overhead panel
5.
Microswitch - transmitter - intercom
D 701
Headset and microphone
M 10-40 or GSSh-A-18 or GSSh-A-18E
1
6.
Left (right) control wheel 2 2 Pilot’s cockpit
2
7.
Loudspeaker (if installed)
AZR 3908 or ARE 3604 or RU 128E/4, (8)
1 1 1 1 2
Between frames No. 9 and 10, RH Between frames No. 10 and 11, LH Between frames No. 13 and 14, LH Between frames No. 15 and 16, RH Near control panel
8.
Amplifier (if installed)
LUN 3513
1
Between frames No.1 and 2, RH
9.
Relay (if installed)
B 073 576 N
2
frame No.2, RH
1
between frames No.6 and 7
1
Fuse panel
INTERCOM I
1
Fuse panel
INTERCOM II
1
Fuse panel
10.
Fuse PA
2 CSN 354733F/1500
11.
Relay (if installed)
B 076 031 N
1
Between frames No.6 and 7
12.
Push button (if installed)
205 K
1
Between frames No.8 and 9
EFFECTIVITY L 410 UVP-E
023.40.00 Page: 1001 May 31/12
MAINTENANCE MANUAL
3. Operation The system is put into operation by switching on the switches BATTERY I, II, VHF I, II circuit breakers and INTERCOM I, II in the overhead panel. The transceiver VHF is on the left side, VHF II is on the right side. The switching on the transceiver is performed by rotating the knob INTERCOM in the transceiver panel from the left caged position to the right. In the receiving mode audio signal is fed via the audio selector box, amplifier and connection box to the headphones. Both of the audio selector box are fed with audio signal parallel and a choice of signals is performed by VHF I, II switch in the audio selector box. On customer’s request a connection box located between frames No.8 and 9 on the LH side can be connected in parallel to the pilot’s connection box to provide for communication between a third member with the pilot’s. The transmitting mode is energized by pushing the key switch over on the pilot’s (copilot’s) control wheel on the sinusoid-marked side. The intercom mode is energized by pushing the key switch over on the pilot’s (copilot’s) control wheel on the telephone-marked side. The signal from the microphone is fed via the audio selector boxes to the headphones. If one of the audio selector boxes fails it is possible to switch over the failed audio selector box to operating audio selector box by the EMERG switch in the failed box. In such case both parties listen to common selected audio signals and their microphone circuits are parallel-connected during transmission. The intercom functions in a normal way. The passenger address system is put into operation by switching on the “PA” circuit-breaker on the overhead panel (at the same time the BATTERY I, II switches and INTERCOM I, II circuit breakers must be switched on). By switching the switch for microphone choice into the position PA and by pushing the push button marked with a telephone (sinusoid) symbol on the steering wheel of the left (right) pilot, sound collected by microphone is amplified and is transmitted over loud-speakers in the passenger compartment. A schematic drawing of the intercom system is shown in Fig.1001, Section 023.12.00 (page 1002)
EFFECTIVITY L 410 UVP-E
023.40.00 Page: 1002 Nov 1/11
MAINTENANCE MANUAL
INTERCOMMUNICATION SERVICING 1. Check of the intercom operation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.00.A Routine
E.
Procedures (1) Connect the headphones and the microphone to both connection boxes. (2) Check of the low frequency wiring and the VHF I and VHF II transceiver. (3) It is not permitted: The operation different from requirements described in items 4 to 8 (4) Switch on the BATTERY I, II switches, VHF I, II, INTERCOM I, II circuit breakers, VHF I switch on the audio selector box and switch over the rotary switch to the VHF I position. In all the headphones you will hear noise. Check the transceiver lighting. After 5 minutes the heat parameters of the transceiver get steady and it is possible to perform next checks. •
adjust the receiver to the highest sensitivity by switching off the noise squelch switch (SQ to 0 position). Select a few channels (by tuning from the lowest to the highest frequency). Receive signals both with low intensity and higher intensity. The volume shall rise with clockwise turning of the VOLUME knob.
•
check AVC function such a way you tune the signal of the local control tower or other aircraft on the local aerodrome. Reception intensity may rise maximally twice.
•
switch the noise squelch switch to the SQ position. You shall not hear any noise in the headphones.
(5) Transceiver transmission Perform this check after an agreement with an air traffic controller and in cooperation with local aerodrome radio tower or with other transceiver (select the channel with the same frequency). After pressing the intercom/transmit switch on the steering wheel and by speaking to the microphone you must hear your modulation in the headphones. The faultless operation is proved by conversation between the transceivers and by evaluating the report transmitted by
EFFECTIVITY L 410 UVP-E
023.40.00 Page: 1301 Nov 1/11
MAINTENANCE MANUAL an operator of the aircraft transceiver. The evaluation is carried out by operator either of the radio tower or other transceiver. (6) Switch the rotary switch on the audio selector boxes to the VHF 2, switch on the VHF 2 switch and perform the same check as with VHF 1 transceiver. (7) By pressing the inner side of the push button on the left pilot’s steering wheel the intercom will be connected and the noise will disappear. Perform the intercom check by speaking between the left and right participant. Set the volume with the potentiometers on the connection boxes. (8) The checks of using arbitrary of the two transceivers by either participant and checks of possibility of using whichever of the two audio selector boxes. Perform the checks described in items 4, 5 and 6 as follows: •
check the left hand transceiver from the place of the right hand participant by switching the VHF I switch on the right audio selector box at the same position of the EMRG switches on the both control boxes.
•
check the left hand transceiver from the place of the left hand participant by switching the VHF 2 switch at the same position of the EMRG switches on the both control boxes.
•
check both the transceivers when using the opposite audio selector boxes at switching over the EMERG switch on the box relevant to the checked transceiver
(9) Switch off the VHF I, II, INTERCOM I, II circuit breakers and BATTERY I, II switches. (10) Disconnect the headphones from the connection box and switch off all the switches on the connection boxes.
EFFECTIVITY L 410 UVP-E
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MAINTENANCE MANUAL
INTERCOMMUNICATION DESCRIPTION AND OPERATION 1. General The intercommunication system is used for intercommunication of the aircraft crew members. It allows also connection of the passenger address system.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Audio selector box
KMA 24 H-70
2
Rear control panel
2.
Connector panel
B 581 731 N
2
Adjacent to the overhead panel
C11 Phone Jack
M641/6-1
1 1 1 1
Vertical steering channel LH Vertical steering channel RH Cockpit Between frames 1 and 2, left *)
C12B Mike Jack
M641/5-1
1 1 1 1
Vertical steering channel LH Vertical steering channel RH Cockpit Between frames 1 and 2, left*)
Circuit breaker INTERCOM I INTERCOM II PA
AZRGK 2 AZRGK 2 AZRGK 5
1 1 1
or
3.
4.
5.
Overhead panel
Microswitch - transmitter - intercom
D 701
Left (right) control wheel
Headset and microphone
M 10-40
1
Pilot’s cockpit
Headset and microphone
H 10-13.4
3
Pilot’s cockpit
Loudspeaker
AZR 3908 or ARE 3604 or RU 128E/4, (8)
1 1 1 1 2
Between frames No. 9 and 10, RH Between frames No. 10 and 11, LH Between frames No. 13 and 14, LH Between frames No. 15 and 16, RH Near control panel
2 2
or
6.
*) If is installed Service personnel - pilot's communication on the airplane
EFFECTIVITY
023.40.00
L 410 UVP-E9
Page: 2001 May 31/12
MAINTENANCE MANUAL
3.
Operation The cable from the headphones with microphone is connected to the connector panel. There are two connectors on the panel – one for headphones the other one for microphone. The system is put into operation by switching on the BATTERY I, II switches and INTERCOM I (pilot) and INTERCOM II (copilot) on the overhead panel. The keying in of the intercom rocker push-button on the control wheel energizes a relay in the audio selector box the contacts of which interconnect the microphone-supplying circuit. The microphone signal is fed to the amplifiers in the audio selector boxes and from there to the headphones. The intercom desired listening level is set individually by pilot and copilot on their audio selector boxes by rotating the smaller concentric knob INTERCOM. If one of the audio selector boxes fails it is possible to switch over the failed audio selector box to operating audio selector box by microphone selector switch. In such case both parties listen to common selected audio signals and their microphone circuits are parallel-connected during transmissions. The intercom functions in a normal way. Thus the intercom system is essentially doubled including power supply from two independent bus-bars. The passenger address system is put into operation by switching on the “PA” circuit–breaker on the overhead panel (at the same time the BATTERY I, II switches and INTERCOM I, II circuit breakers must be switched on). By switching the switch for microphone choice into the position PA and by pushing the push button marked with a telephone (sinusoid) symbol on the steering wheel of the left (right) pilot, sound collected by microphone is amplified and is transmitted over loud-speakers in the passenger compartment.
EFFECTIVITY
023.40.00
L 410 UVP-E9
Page: 2002 Nov 1/11
MAINTENANCE MANUAL
FIG. 2001
BLOCK DIAGRAM OF AUDIO SELECTOR BOXES
EFFECTIVITY
023.40.00
L 410 UVP-E9
Page: 2003 Nov 1/11
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY
023.40.00
L 410 UVP-E9
Page: 2004 Nov 1/11
MAINTENANCE MANUAL
INTERCOMMUNICATION DESCRIPTION AND OPERATION 1. General The intercommunication system is used for intercommunication of the aircraft crew members. It allows also connection of the passenger address system.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Audio selector box
KMA 24 H-70
2
Rear control panel
2.
Socket
M 641/6-1 M 641/5-1
2
Frame 7, LH up, RH up
2
Frame 7, LH up, RH up
C11 Phone Jack
M641/6-1
1 1 1 1
Vertical steering channel LH Vertical steering channel RH Cockpit Between frames 1 and 2, left *)
C12B Mike Jack
M641/5-1
1 1 1 1
Vertical steering channel LH Vertical steering channel RH Cockpit Between frames 1 and 2, left*)
Circuit breaker INTERCOM I INTERCOM II PA
AZRGK 2 AZRGK 2 AZRGK 5
1 1 1
or
3.
4.
Overhead panel
Microswitch - transmitter - intercom
D 701
Headset and microphone
H 10-40
2
Pilot’s cockpit
Headset and microphone
H 10-13.4
3
Pilot’s cockpit
6.
Loudspeaker
AZR 3908 or ARE 3604 or RU 128E/4, (8)
1 1 1 1 2
Between frames No. 9 and 10, RH Between frames No. 10 and 11, LH Between frames No. 13 and 14, LH Between frames No. 15 and 16, RH Near control panel
7.
Fuse SPEAKERS
2,5 CSN 354733F/1500
2
Fuse panel
8.
Relay
TKE 52 PODG
1
Frame No.6
9.
Fuse INTERCOM
2 CSN 354733F/1500
2
Fuse panel
5.
LH and RH steering wheel 2 2
or
*) If is installed Service personnel - pilot's communication on the airplane
EFFECTIVITY L 410 UVP-E20
023.40.00 Page: 3001 May 31/12
MAINTENANCE MANUAL
3.
Operation The cable leading from the headphone set with the centre lead of protection from damage is connected to the panel with connectors. There are two sockets on the panel – one for headphones and another for the microphone. Intercom is put into operation by switching on the switches BATTERY I, II and circuit breaker INTERCOM or INTERCOM I, II switch which is located on the overhead panel. Switching on the switch INTERCOM in the steering wheel is switched on by a relay in the audio selector box which results in connecting through the microphone supply circuit. The signal from the microphone goes via amplifiers located in audio selector boxes and from there to the headphones. A pilot adjusts desired volume of the intercom himself by means of the smaller concentric knob INTERCOM at the audio selector box itself. In case that either of audio selector boxes fails there is possibility of switching over the switch for microphone choice so that the microphone and headphones will be connected direct to the transceiver VHF I. The intercom operates in usual way. Basically it means that the intercom is coupled including feeding of two independent bus-bars. The passenger address system with system of entertainment broadcasting for passengers is put into operation by switching on the circuit breaker PA on the overhead panel (at the same time the switches BATTERY I, II and circuit breaker INTERCOM must be switched on). By switching the switch for microphone choice into the position PA and by pushing the push button marked with a telephone (sinusoid) symbol on the steering wheel of the left (right) pilot, sound collected by microphone is amplified and is transmitted over loud-speakers in the passenger compartment.
EFFECTIVITY L 410 UVP-E20
023.40.00 Page: 3002 Nov 1/11
MAINTENANCE MANUAL
FIG. 3001
BLOCK DIAGRAM OF AUDIO SELECTOR BOXES (THE VARIANT WITH ONE CIRCUIT BREAKER INTERCOM)
EFFECTIVITY L 410 UVP-E20
023.40.00 Page: 3003 Nov 1/11
MAINTENANCE MANUAL
FIG. 3002
BLOCK DIAGRAM OF AUDIO SELECTOR BOXES (THE VARIANT WITH TWO CIRCUIT BREAKERS INTERCOM I, II)
EFFECTIVITY L 410 UVP-E20
023.40.00 Page: 3004 Nov 1/11
MAINTENANCE MANUAL
LUN 3591.11 or LUN 3591.13 AUDIO SELECTOR BOX DESCRIPTION AND OPERATION 1. Purpose The LUN 3591.11 or LUN 3591.13 audio selector box is used to direct a select audio frequency signals from the microphone, radio receivers, intercom and passenger address system.
2. Technical data The technical data is presented in the LUN 3591.11 or LUN 3591.13 audio selector box maintenance manual.
3. Operation The operation is described in the LUN 3591.11 or LUN 3591.13 audio selector box maintenance manual.
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1001 Nov 1/11
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1002 Nov 1/11
MAINTENANCE MANUAL
LUN 3591.11 or LUN 3591.13 AUDIO SELECTOR BOX SERVICING 1. Check of audio switch box LUN 3591.11 or LUN 3591.13 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B Periodical
E.
Procedures (1) Check of external appearance - refer to the work procedure chart 023.40.01.B-1 (2) Check of frequency characteristics- refer to the work procedure chart 023.40.01.B-2 (3) Distortion check - refer to the work procedure chart 023.40.01.B-3 (4) Check of level of the if load - refer to the work procedure chart 023.40.01.B-4 (5) Load change influence check - refer to the work procedure chart 023.40.01.B-5 (6) Check of voltage amplification coefficient of inputs from navigation and communication receivers - refer to the work procedure chart 023.40.01.B-6 (7) Check coefficient of voltage amplification from microphone input - refer to the work procedure chart 023.40.01.B-7 (8) Function check under decreased supply voltage - refer to the work procedure chart 023.40.01.B-8
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1301 May 30/14
MAINTENANCE MANUAL
2. Check of external appearance A.
Fixture, Test and Support Equipment
Magnifying glass No.5
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-1 Periodical
E.
Procedures (1) The instrument shall not be apparently damaged. One must check the surface finish if it does not bear traces of damage, caused by assembly or check. Further one must check inscription make, label make and arrest of commutators and switches. (2) Carry through a check of completeness and non-damage, see para 1.
3. Check of frequency characteristics A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-2 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to scheme – see Fig.1301
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1302 Nov 1/11
MAINTENANCE MANUAL
DC power source
Volt-ampere meter
LUN 3591.11
FIG. 1301
Z 579Testing
LF
device
generator
Distortion
LF
meter
milivoltmetr
LF milivoltmetr
SCHEME OF CHECK /TESTING SET LUN 3591.11 or 3591.13 – audio switch box (checked instrument)
(2) Put the function switches of the audio switch box into ON position. The outer function switch EMERG into OFF position and the HI, LO into LO position. The function switch on the testing device put into VHF 1 position, the loading impedance switch into 150 Ω (Ohms) position and switch KEY TRANSM and the switch KEY INTERK into off position, connect the 48-pin plug of the testing device to the connecting box socket. Connect the screened cable +28V from testing device to DC power source. The red end to the clip “+” and blue one to clip “-”. Connect LF power generator and LF milivoltmetr to clips on testing device marked LF-INPUTS. To HEADPHONES 1 clips connect if milivoltmetr No.2. To HEADPHONES 2 clips connect distortion meter. On the power source set through OUTPUT VOLTAGE-VOLTS switches the supply voltage to 27.5V. In order to measure accurate input current of the box connect to AMPEREMETER clips testing device outer ampere meter (range to 1A). In case it will not be used the clips must be shortcircuited. (3) Frequency characteristics check (4) The outer power may not differ more than 6dB, if the signal level on input is constant and if it’s frequency is being changed in (350 to 3000)HZ range. (5) Put on all measuring instruments on workplace set together according to par.1, 2 and keep them on for half an hour. (6) Put on testing device with 28V switch – the signal light EMERG must shine and after 5 minutes set 1 kHz frequency on the generator and increase the input voltage to such level, that voltage (12±1)V (corresponds to nominal output) reached on milivoltmetr No.2/connected to clips HEADPHONES 2. Lower the input voltage level of the generator in such a way that the output voltage (measured on milivotmetr No.2) reaches level (3.8±2)V (corresponds to 10% of nominal output). Keep changing input signal frequency on generator in (350 to 3000Hz) range while EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1303 Nov 1/11
MAINTENANCE MANUAL keeping a constant input voltage on LF millivoltmeter No.1 and watch the changes of output voltage on LF milivoltmetr No.2. They must be in (1.9 to 5.7)V internal (7) After measurement practice follows measurement according to work procedure chart 023.40.01.B-3.
4. Distortion check A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-3 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1, 2. (2) Distortion check (3) Output signal distortion in frequency band (350+3000)Hz ±10% may not be greater than 15% at nominal output and maximum 5% at 0.01 of the nominal output. (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1 and 2. Put all measuring instruments and keep them on for half an hour. NOTE:
Do not carry out if it follows immediately after measurement according to work procedure chart 023.40.01.B-2.
(5) Put on the testing device by 28 V switch – the EMERG lamp must be on. After five minutes wait generate on LF INPUTS of the testing device Z 579 a such signal from LF generator of 1kHz frequency that on LF milivoltmetr an output voltage of (12±0.5)V would show (corresponds to nominal output). Read the output signal distortion level on distortion meter. The frequency on LF generator keep changing in (350 to 3000)Hz range, keep a constant input level and watch distortion level on frequencies (350. 500, 1800 and 3000)Hz. The distortion must be in all cases less than 15%. Set the frequency of LF generator to 1kHz, the voltage decrease to such a level that the output voltage on LF milivoltmetr. No.2 is 12V±5mV (corresponds to 0.01 of nominal output). Change the frequency of LF generator from (350 to 3000)Hz, keep a constant input EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1304 Nov 1/11
MAINTENANCE MANUAL voltage and on distortion meter read the distortion level on frequencies (350, 500, 1000, 1800 and 3000)Hz. In all cases the distortion must be less than 5%. (6) After the practiced measurement follows a measurement according to work procedure chart 023.40.01.B-4.
5. Check the signal noise level A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-4 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1, 2. (2) Signal noise level check (3) The LF noise level on amplifier output without input signal must be 100 times lower at minimum the nominal input (lower than 120 mV). (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1 and 2. Put on all measuring instruments and keep them on for half an hour. NOTE:
Do not carry out if it follows immediately after work procedure chart 023.40.01.B-3.
(5) Put on the testing device by 28 V switch – the EMERG signal lamp must be on. After five minutes start with the measurement. Keep all switches on the commutating box LUN 3591.11 and Z 579 in the same position as in distortion check, disconnect LF generator and LF milivoltmetr No.1 from Z 579 clamp marked LF inputs. On LF milivoltmetr No.2, connect the clips HEADPHONES 1 read the noise voltage level. Set all possible combination of KEY INTERK switch positions and of Z 579 function switch and read successively all noise voltage levels. Switch all functions switch on LUN 3591.11 box to OFF position and read the noise voltage level. In no case may the noise voltage levels overcome the 0.12 V level. (corresponds to level 40dB lower when compared with nominal output).
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1305 May 30/14
MAINTENANCE MANUAL (6) After the practiced measurement follows measurement according to work procedure chart 023.40.01.B-5.
6. Load change influence check A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-5 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1, 2. (2) Check of load change influence. (3) Output signal level must be in range 12V (+40/-30)% and the distortion of output signal must be less than 25%, under conditions that load impedance is being changed in range (50 to 200)% of nominal level. (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-2, steps (1) and (2). Put on all measuring instruments and keep them on for half an hour. NOTE:
Do not carry out if it follows immediately after work procedure chart 023.40.01.B-4.
(5) Put on testing device by 28V switch - signal lamp EMERC. must be on. After five minutes set on LF generator such a level of input signal at 1 kHz frequency, that the output voltage on LF milivoltmeter No. 2 is 3.8V +/- 10% (corresponds to 10% of nominal output). On distortion meter read distortion level of output voltage. Change-over switch of the load resistor switch successively to 75Ω and 330Ω (Ohms) positions and repeat the measurement. Set the frequency of LF generator successively on 350Hz +/10% and 3000Hz +/- 10% levels and repeat the whole measurement. During whole measuring time keep a constant level of input signal on LF generator. The output voltage on LF milivoltmeter No. 2 must always be in 12V (+40/-30)% and it's distortion may in no case overreach 25% level. (6) After practiced measurement follows measurement according to work procedure chart 023.40.01.B-6.
EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1306 May 30/14
MAINTENANCE MANUAL 7. Check of voltage amplification coefficient of inputs from navigation and communication receivers A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-6 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1, 2. (2) Check of coefficient of input amplification from navigation and communication receivers. (3) Output signal amplification for attainment to nominal input level must be from 0.8 to 1.5 times. (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-3, par. 1. Put on all measuring instruments and keep them on for half an hour. NOTE:
Do not carry out if it follows immediately after work procedure chart 023.40.01.B-5.
(5) Put on the testing device by 28 V switch-signal lamp EMERG must be on. After five minutes switch the function switch on Z 579 to “VHF 1” position and on LF generator set such a level of input signal at 1kHz frequency , that the milivoltmetr No.2 would show output voltage (12+0.5)V (corresponds to nominal output). Read the input signal level on LF milivoltmetr and calculate voltage amplification by division
A=
U output U input
, where
U – output is voltage on LF milivoltmetr No.2 U – input is voltage on LF milivoltmetr No.1 Keep switching the function switch on Z 579 successively to positions VHF 2, NAV 1, NPV 2, ADF 1, ADF 2, MKR, HF and repeat the measurement of input and output voltage and calculation of voltage amplification of individual inputs. In all cases the coefficient of voltage amplification must stay in range from 0.8 to 1.5 times. EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1307 May 30/14
MAINTENANCE MANUAL (6) After practiced measurement follows measurement according to work procedure chart 023.40.01.B-7.
8. Check of coefficient of voltage amplification from microphone input A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-7 Periodical
E.
Procedures (1) Connect checking and measuring workplace according to work procedure chart 023.40.01.B-2, par.1, 2. (2) Check of coefficient of voltage amplification from microphone input. (3) Voltage amplification of input signal for nominal output must be greater more than 30 times. (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1 and 2. Further disconnect LF generator from LF input clips and connect it to “MIKE 1” clips. The switch KEY INTERCOM put to ON position. Put on all measuring instruments and keep them on for 30 minutes. NOTE:
Do not carry out if it follows immediately after measurement according to procedure chart 023.40.01.B-6.
(5) Put on testing device 28 V – the signal lamp EMERG must be on. After five minutes set on the LF generator such a input signal level at 1kHz frequency, that the output voltage on LF milivoltmetr No.2 will be of (12±1)V level. Read the input signal level on LF milivoltmetr No.1 and calculate voltage amplification volume from definition:
A=
U output U input
, where
The calculated value of coefficient of voltage amplification must be greater than 30. (6) Checking and measuring workplace put to a state according to work procedure chart 023.40.01.B-2 par. 1, 2. The measurement according to work procedure chart 023.40.01.B-8. EFFECTIVITY L 410 UVP-E
023.40.01 Page: 1308 May 30/14
MAINTENANCE MANUAL 9. Function check under decreased supply voltage A.
Fixture, Test and Support Equipment
Z 579 Testing device G3-34 LF generator V3-38 LF milivoltmetr YE-2T DC power source 0-30V/10A plus accessories S6-5 Distortion meter C43-17 Voltampere meter
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.01.B-8 Periodical
E.
Procedures (1) Prepare checking and measuring workplace according to work procedure chart 023.40.01.B-2, par.1, 2. (2) Function check under decreased supply voltage (3) Under supply voltage change to 22V the commutating box after 30 minutes of operation must comply to tests according to work procedure chart 023.40.01.B-3, 023.40.01.B-6 and 023.40.01.B-7. (4) Checking and measuring workplace according to work procedure chart 023.40.01.B-2, par. 1 and 2. Put on all measuring instruments and keep them on for half an hour. NOTE:
Do not carry out if it follows immediately after measurement according to 023.40.01.B-7.
(5) Put on testing device by “28V” switch – the signal lamp EMERG must be on. After 30 minutes lower the supply voltage on YE 2T source by OUTPUT VOLTAGE-VOLTS switches to level from 18 to 33V. Measure the distortion, check voltage amplification of navigation and communication inputs and check voltage amplification of microphone input the same way as indicated in preceding work procedures chart/see work procedure chart 023.40.01.B-3, 023.40.01.B-6, 023.40.01.B-7. All checked parameters must comply with above mentioned conditions. (6) After finishing the measurement put the workplace into the initial state, disconnect all instruments from the mains.
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LUN 3591.11 OR LUN 3591.13 AUDIO SELECTOR BOX SERVICING 1. Removal and installation of the audio switch box LUN 3591.11 or LUN 3591.13 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
No. 713 6.5x130 Screwdriver
D. Referenced information
023.40.01.A Periodical
E.
Procedures (1) Removal and installation of the audio switch box LUN 3591.11 or LUN 3591.13 (2) Disconnect the cabling sockets NOTE:
For a better access to carry out the disconnection of the socket connections of audio switch box LUN 3591.13 disassemble the transceiver LUN 3524.13 (on the rear control panel)
(3) Removal the 2 audio switch boxes by screwing off the 8 pcs of screws by a screwdriver No. 713 6.5x130 and shift them out in the upward direction (4) After having received the audio switch boxes back carry out the installation. (5) Set the audio switch boxes on the rear control panel and fix by 8 screws and the screwdriver No.713 6.5x130. (6) Connect the cabling socket and secure them by binding wire against their loosening.
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KMA 24 H-70 AUDIO SELECTOR BOX DESCRIPTION AND OPERATION 1. Purpose The KMA 24 H-70 audio selector box is used to direct and select audio frequency signals from the microphone, radio receivers, intercom and passenger address system.
2. Technical data The technical data is presented in the KMA 24 H-70 audio selector box maintenance manual.
3. Operation The operation is described in the KMA 24 H-70 audio selector box maintenance manual.
FIG. 2001
KMA 24 H-70 AUDIO SELECTOR BOX 1–
Intercom VOX voice activated Sensitivity Control, turned to fully clockwise detent position – hot mike operation, turned all the way counterclockwise past the detent - keyed microphone operation (utilized on L 410 UVP-E aircraft)
2–
Intercom Volume Control
3–
Speaker Audio Select Buttons
4–
Headphone Audio Select Buttons (COM 3 and 4 buttons are not utilized on L 410 UVP-E aircraft)
5–
Speaker AUTO Switch
6–
Microphone Selector Switch (EXT ramp hailer speaker position is not utilized on L 410 UVP-E aircraft)
7-
VOX Release Adjustment - VOX Release pot R267 is accessible through the small hole in the lower left corner of the front panel. Clockwise adjustment will increase the time that the intercom remains on after speech has ended. VOX Release should be adjusted to suit user preference.
EFFECTIVITY
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L 410 UVP-E9
Page: 2001 May 31/12
MAINTENANCE MANUAL
FIG. 2002
TOP VIEW OF KMA 24 H-70 AUDIO SELECTOR BOX NOTE:
Is very important checked the right position micro switches under sticky labels, e.g. during the replacement of KMA 24 H-70 Audio Selector Box DUAL / SINGLE - right position is DUAL CO-PILOT / PILOT - right position is depending on the use of
EFFECTIVITY
023.40.01
L 410 UVP-E9
Page: 2002 May 31/12
MAINTENANCE MANUAL
KMA 24 H-70 AUDIO SELECTOR BOX DESCRIPTION AND OPERATION 1. Purpose The KMA 24 H-70 audio selector box is used to direct and select audio frequency signals from the microphone, radio receivers, intercom and passenger address system.
2. Technical data The technical data is presented in the KMA 24 H-70 audio selector box maintenance manual.
3. Operation The operation is described in the KMA 24 H-70 audio selector box maintenance manual.
FIG. 3001
KMA 24 H-70 AUDIO SELECTOR BOX 1–
Intercom VOX voice activated Sensitivity Control, turned to fully clockwise detent position – hot mike operation, turned all the way counterclockwise past the detent - keyed microphone operation (utilized on L 410 UVP-E aircraft)
2–
Intercom Volume Control
3–
Speaker Audio Select Buttons
4–
Headphone Audio Select Buttons (COM 3 and 4 buttons are not utilized on L 410 UVP-E aircraft)
5–
Speaker AUTO Switch
6–
Microphone Selector Switch (EXT ramp hailer speaker position is not utilized on L 410 UVP-E aircraft)
7-
VOX Release Adjustment - VOX Release pot R267 is accessible through the small hole in the lower left corner of the front panel. Clockwise adjustment will increase the time that the intercom remains on after speech has ended. VOX Release should be adjusted to suit user preference.
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FIG. 3002
TOP VIEW OF KMA 24 H-70 AUDIO SELECTOR BOX NOTE:
Is very important checked the right position micro switches under sticky labels, e.g. during the replacement of KMA 24 H-70 Audio Selector Box DUAL / SINGLE - right position is DUAL CO-PILOT / PILOT - right position is depending on the use of
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LUN 3591.22 CONNECTION BOX DESCRIPTION AND OPERATION 1. Purpose The LUN 3591.22 connection box is intended for connection of the headset to the communication system.
2. Technical data Nominal supply voltage
21 V
Current consumption
0.06 A
Min. microphone input amplification •
selector switch in GSSh S-12A position
4 times at a frequency of 1kHz
•
selector switch in GSSh-A-18 position
16 times at a frequency of 3kHz
3. Operation Level of the signal coming to the headphones can be controlled by the VOL potentiometer (Fig. 1001) while the signal level from the microphone can be controlled by the MOD potentiometer (after removing a protective cover) Fig. 1001 – LUN 3591.22 connection box. Two GSSh-S-12A or GSSh-A-12A headsets can be connected to the connection box. When using GSSh-S-12A headset, the selector switch must be in the GSSh-S-12A position while for the GSSh-A18 headset it must be set to the GSSh-A-18 position. The connection box comprises two amplification stage composed of operational amplifiers. The first stage comprises an adjustable gain voltage amplifier, the second stage comprises a voltage amplifier having a constant gain but a modified frequency response characteristic for the GSSh-A-18 headset. The connection box also comprises a microphone feeding circuit and a volume control. The headset is plugged in a fire pin socket.
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FIG. 1001
LUN 3591.22 CONNECTION BOX
FIG. 1002
WIRING DIAGRAM OF THE CONNECTION BOX LUN 3591.22
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LUN 3591.22 CONNECTION BOX SERVICING 1. Check for proper function of LUN 3591.22 connection box A.
Fixture, Test and Support Equipment
Z 984 testing equipment P Z 984 accessories of the testing equipment Audio-frequency generator, up to 10 kHz, output voltage of 3.5V DC voltmeter, range of 10V, 100 scale divisions, accuracy class 1.5 Low-frequency voltmeter, measuring range of 10V, 100 scale divisions accuracy class 1 Milliammeter, measuring range of 100mA, 100 scale divisions, accuracy class 1.5. Ohmmeter, measuring range of 1kΩ, 100 scale divisions, accuracy class 2.5. Meter, measuring range of 0.1 to 20% input sensitivity of 100m, frequency range from 20Hz to 20kHz. Regulated DC power supply, voltage range from 0 to 30V/1A.
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.02.B Periodical
E.
Procedures (1) Prepare test equipments as shown in Fig. 1301
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FIG. 1301
BLOCK DIAGRAM OF TEST EQUIMPMENTS Legend to Fig. 1301: LUN 3991.22
- connection box (the unit to be tested)
Z 984 B
- testing equipment
G
- audio-frequency generator, up to 10kHz, output voltage of 3.5V
V1
- DC voltmeter , range of 10V
V2
- LF frequency voltmeter, measuring range of 10V, scale divisions–100, accuracy class 1
A
- milliammeter, measuring range of 10mA, scale divisions–100, accuracy class 1.5
Ω
- ohmmeter, measuring range of 1kΩ, scale divisions–100, accuracy class 2.5
M
- meter, measuring range from 0.1 to 20%, input sensitivity 100mA, frequency range from 20MHz to 20kHz
Z
- regulated DC power supply, voltage range from 0 to 30V/1A.
CAUTION:
THE C43-12 OHMETER TO BE CONNECTED ONLY FOR THE CHECK PER PARA. 12.
(2) Check of the LUN 3591.22 connection box (3) Requirements: (a) Microphone input voltage amplification: •
with the selector switch in GSSh-S-12A position: not less than 4 times at frequency of 1kHz
•
with the selector switch in GSSh-A-18 position: not less than 16 times at frequency of 3 kHz
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MAINTENANCE MANUAL (b) Distortion must not exceed 5% at nominal output voltage. (c) Current drain of not more than 60mA. (d) The frequency response characteristic must not exceed the values shown in the table below. Selector position
f[Hz]
A [dB]
GSSh-S-12A
350-3000
3
GSSh-A-18
1800
28
1000
28
(e) Microphone supply voltage must be within 7.5 and 9V. (f)
There must not be step changes in potentiometer resistance when rotating the volume control knob from one extreme position to the other.
(4) Visual appearance: the surface of the connection box must not be mechanically damaged. (5) Apply 1kHz signal (for selector position GSSh-S-12A) or 3kHz signal (for selector position GSSh-A-18) from the audio frequency generator to input No.1 of the 2984 testing equipment. The signal value to be such as to receive a voltage of 0.8V on the EXIT MODE outlet. Voltage amplification is calculated by means of the following formula:
A=
U OUTLET U INPUT
The result must correspond with the requirements indicated in para. 3a. NOTE:
The MODE controller located under a cover on the LUN 3591.22 is set to maximum gain.
(6) Check for distortion of the GSSh-S-12A headset. Apply a 200mV voltage of 1 kHz to input No.1 of the Z 984 testing equipment and by means of the microphone signal controller adjust an output voltage of 0.8Von the EXIT MODE jacks of the Z 984 testing equipment. Measure the distortion by means of the meter. Vary the frequency of the AF generator from 350Hz to 3000Hz while maintaining a constant input voltage of 200mV. Measure the distortion at a frequency of 350Hz, 500Hz, 1800Hz and 3000Hz. The result must correspond with the requirements indicated in para. 3b. (7) Check for distortion of the GSS-A-18 headset. Set the selector on the connection box to the GSS-A-18 position. Apply a 50mV/3kHz signal from the AF generator ENT jacks and by means of the microphone signal controller adjust an output voltage of 0.8V on the EXIT MODE jacks of the Z 984 testing equipment. Measure the distortion by means of the meter. Set the frequency of the AF generator to 500Hz, 1800Hz and 3000Hz while maintaining an output voltage of 0.5V. The result must correspond with the requirement of para.3b. EFFECTIVITY L 410 UVP-E
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MAINTENANCE MANUAL (8) Check for the current drain by means of a milliammeter plugged in the A-meter jacks of the Z 984 testing equipment. The current value must next the requirement of para.3c. (9) Check for frequency response characteristic of the GSSh-S-12A headset. Set the selector on the connection box to GSSh-S-12A position. Apply 200mV/1kHz signal from the AF generator through a capacitor to the microphone input of the Z 984 texting equipment. By means of the microphone signal controller adjust a voltage of 0.8V on the EXIT MODE jacks of the Z 984 testing equipment. While maintaining a constant input voltage vary frequency from 300 to 350 Hz and check for the output whose variation must not exceed the values indicated in para.3d. (10) Check for frequency response characteristic of the GSSh-A-18 headset. Set the selector on the connection box to GSSh-A-18 position apply 50mA/36Hz signal to the microphone signal controller adjust a voltage of 0.8V on the EXIT MODE jacks of the Z 984 testing equipment. While maintaining a constant input voltage, reduce the frequency and determine the gain. The frequency response characteristic must correspond with the requirements of para.3d. (11) Measure the microphone supply voltage by connecting a V1 DC voltmeter to the V-meter jacks of the Z 984 testing equipment. The voltage must be within the range indicated in para.3e. (12) Connect the ohmmeter to the TEST R 111 jacks of the Z 984 testing equipment. Rotate the volume control knob from one extreme position to the other and check by means of the ohmmeter that the requirement of para.3f is met. (13) Check the visual appearance of the connection box in accordance to para.4. (14) Set the test equipment to its original condition.
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LUN 3591.22 CONNECTION BOX REMOVAL / INSTALLATION 1. Removal and installation of LUN 3591.22 connection box A.
Fixture, Test and Support Equipment
Screwdriver No.697 6x120
B.
Materials
Lock wire dia. 8mm CSN 426410.91 material: 11343.0
C. Tools
Not applicable
D. Referenced information
023.40.02.A Periodical
E.
Procedures (1) Screw off 4 screws in the upper part of the vertical control channel on frame No. 7 using a screwdriver No. 697 6x120 and remove the covers of both connection boxes. (2) Removal of connection boxes located in the upper parts of vertical control channel on frame No.7. (a) Remove two aircraft electric wiring connectors from the connection boxes. (b) Screw off 4 screws from the connection boxes by means of a screwdriver No.697 6x120 and remove two connection boxes from their holders. (3) Remove of the connection box located between frames No.7 and 8 in the passenger cabin. (a) Screw off two screws from the connection box using a screwdriver No.697 6x120 and pull the box slightly out. (b) Disconnect the aircraft wiring connector and remove the connection box. (4) Installation of connection boxes to the upper part of the vertical control channel on frame No.7 (a) Locate the connection boxes in their holders and fasten them with 4 screws using a screwdriver No.697 6x120. (b) Connect the two aircraft wiring connectors and fasten down. (5) Installation of the connection box between frames No.7 and 8 in the passenger cabin. (a) Connect the aircraft electric wiring connector to the connection box and fasten down. (b) Locate the connection box in its holder and fasten with 2 screws using a screwdriver No.697 6x120. (6) Fix the two covers of the connection boxes with 4 screws by means of a screwdriver No.697 6x120.
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GSSH-A-18, GSSH-A-18E HEADSET DESCRIPTION AND OPERATION 1. General The headset operates as an electro-acoustics transducer intended to work in conjunction with the communication system. NOTE:
The GSSh-A-18E headset is fully interchangeable with the GSSh-A-18 headset. The only difference consist in a technical improvement – shielding of individual components of the headset has been in integrated to improve the headset immunity to interfering signals.
2. Technical data Max. supply voltage
10V
Frequency characteristics of microphone and earphones (±12dB) Resistance
200-400Hz
- microphone
(1kHz)
- earphones
(1kHz)
280±60dB
3. Description The electro-acoustic headset consists of earphones and a microphone. The earphones can be adjusted to fit the pilot’s head. The design of the earpiece provides for good sound insulation. The microphone suppresses environment noise. It is articulates to one of the earpieces by means of a bent arm. It is articulates to one of the earpieces by means of a bent arm. Both earphone and microphone insets are electrodynamics. The cable of earphone is ended with a plug.
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FIG. 1001
GSSH-A-18, GSSH-A-18E HEADSET WIRING DIAGRAM Mk1 – oxygen mask microphone Mk2 – headset microphone TØ – earphones UC – UK-15 PF integrated circuit (amplifier) R – resistor (to be selected during adjustment)
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GSSh-A-18, GSSh-A-18E HEADSET SERVICING 1. Inspection of GSSh-A-18 or GSSh-A-18E headset A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.03.A Routine
E.
Procedures (1) The following defects are not permissible: •
headset cable insulation damage (particulary at the earphone-side and plug-side ends), loose joint between the earphones and the microphone, mechanical damage
(2) Inspect the headset for defects indicated in para.1 above. (3) The loose joint is tightened in case of other defects the headset to be replaced.
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B 076 031 N RELAY CHANGE-OVER SWITCH DESCRIPTION AND OPERATION 1. Purpose The B 076 031 N (RP 318) relay change-over switch is intended for interconnection of the LUN 3591.11 connection boxes should one of the fail.
2. Technical data Max. operating voltage
125V
Max. operating current (output)
1A (15W)
Nominal closing voltage
27A
Closing current
14±2mA
3. Operation When voltage is supplied to pins No.1 and 16 (see Fig.1001) three 15N 599 19.7 relays will close. When voltage is supplied to pins No.15 and 14 the other three relay will close.
FIG. 1001
WIRING DIAGRAM OF B 076 031 N RELAY CHANGE-OVER SWITCH
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B 076 031 N RELAY CHANGE-OVER SWITCH REMOVAL / INSTALLATION 1. Removal and installation of B 076 031 N relay change-over switch A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Lock wire dia.0.8mm
C. Tools
Spanners and screwdrivers of corresponding sizes from the tool kit.
D. Referenced information E.
-
Procedures (1) Remove the RH ceiling upholstery panel in the cockpit. (2) Remove the lock wire and disconnect the connector. (3) Screw off four M4 screws fastening the change-over switch to a ceiling rib between frames No.6 and 7. (4) Attach the relay change-over switch to a ceiling rib between frames No.6 and 7 four M4 screws. (5) Plug in the connector, tighten and wirelock. (6) Reinstall the cockpit ceiling upholstery panel.
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LUN 3513 AMPLIFIER DESCRIPTION AND OPERATION 1. Purpose The LUN 3513 amplifier is intended for amplification of signals from the pilot’s microphones.
2. Technical data Supply voltage
28V
Current consumption
2A
Nominal power output (Rz=8Ω Ohms)
18W
3. Operation The amplifier consists of two MDA 2020 integrated circuits forming a bridge system. An energizing preamplifier is fitted with a MAA 741 operational amplifier which is located together with a voltage regulator on one printed circuit board. The amplifier is fed from a series voltage regulator with an electronic protection.
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LUN 3513 AMPLIFIER SERVICING 1. Check for proper function of LUN 3513 amplifier A.
Fixture, Test and Support Equipment
Regulated DC power supply from 0 to 30V/5A Digital AC, DC voltmeter, range of 50V, accuracy class 0.5 Distortion meter, range from 0.1% to 20%, frequency range from 100Hz to 10kHz, input voltage from 300mV to 20V Generator, range from 10 Hz to 20 kHz, accuracy class 0.5, output voltage of 1V Z 1098 testing equipment with accessories
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.05.B Periodical
E.
Procedures (1) Prepare a test wing as shown in Fig.1301 (2) Interconnect the jacks marked A-METER on the face panel by the Z 1098 testing equipment. (3) Check of the LUN 3513 interphone amplifier. (4) Permissible inaccuracy at normal temperature. Discortion of 1kHz output signal at power output of 18W must not exceed 5%.
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FIG. 1301
BLOCK DIAGRAM OF TEXT WIG Legend to Fig. 1301: LUN 3513
- interphone ampllifier (the unit to be texted)
Z
- regulated DC power supply, voltage range from 0 to 30V/5A
V1,V2
- digital DC, AC voltmeter, range of 50V, accuracy class 0.5
M
- distortion meter, measuring range from 0.1% to 20%, frequency range from 100Hz to 10kHz, input voltage of 300mV to 20V
G
- audio frquency generator, range from 10Hz to 20kHz, accuracy class 0.5, output voltage of 1V
Z1098
- testing equipment
(5) Check for non-linear distortion of the output signal as follows: Apply a nominal supply voltage of 27V to the amplifier inlet (the voltage to be checked in both BASIC and REVERSE positions of the selector). Apply a resistance load of 8±0.5Ω (Ohms) to the amplifier outlets. Apply a 1000Hz signal of the audio-frequency generator to the amplifier inlet. The signal level must be such as to receive a power output of 18W (i.e. voltage of 12V at a resistance of 8Ω). The measurement to be taken with the selector in E1 position and checked with selector in E3 and E5 position. Use the non-linear distortion meter to take the measurements. The inacuracy of the measured distortion value not exceed the value given in para. 4. (6) After finishing the measurement put the workplace into the initial state.
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LUN 3513 AMPLIFIER REMOVAL / INSTALLATION 1. Removal and installation of LUN 3513 amplifier A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.40.05.A Periodical
E.
Procedures (1) Remove the cover between frames No.1 and 2 on the RH side (2) Removal and installation of LUN 2513 amplificier (3) Removal of LUN 3513 amplifier (a) Release the plug and remove it from the socket. Release the nut by hand, tilt down the wing bolt and remove the amplifier. (b) Put the amplifier in a polyethylene bag and in a box and hand over to the next laboratory. (4) Reinstallation of the LUN 3513 amplifier after it has been checked at the test laboratory. (a) Check that the serial number of the amlifier is the same as indicated in the amplifier certification. (b) Install the amplifier into a mount, tilt the swing bolt in the fork of the amplifier and tighten it. Plug in the amplifier. (c) Reinstall the cover between frames No.1 and 2 on the RH side.
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ARZ 3908 LOUDSPEAKER DESCRIPTION AND OPERATION 1. Purpose The ARZ 3908 loudspeaker is used to emit the audio signal amplified by the amplifier.
2. Technical data Maximum power input
21 V
Rated impedance
0.06 A
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STATIC DISCHARGING DESCRIPTION AND OPERATION 1. General Normal operation of the radiocommunication and navigation equipment of the aircraft is endangered by interferences originating in various electric power appliances and devices, such as electric motors, generators, relays, contactors etc., as well as by interferences due to accumulated static electricity. In order to minimize these interferences, the aircraft is protected by: •
electrical bonding of aircraft assemblies (see section 024.60.00)
•
installation of static dischargers
2. Static discharging The static dischargers provide for discharging static electricity charges from the aircraft surface into the atmosphere. Their number and location is shown in Fig. 1, typical installation and design of the static discharger is shown in Fig. 2, 3.
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FIG. 1
LOCATION OF STATIC DISCHARGERS (1) Rudder - 2 pcs; (2) Elevator - 2 pcs; (3) Ailerons - 4 pcs; (4) Stabilizer tips - 2 pcs; (5) Fuselage tail cone - adjacent to position light - 1 pcs; (6) Wing tips - 2 pcs; (7) Wing tips fuel tanks - 2 pcs
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FIG. 2
STATIC DISCHARGERS ON WING AND TAIL UNIT – TYPICAL INSTALLATION (1) Holder; (2) Pipe; (3) Wire; (4) Cube; (5) Bushing; (6) Funnel; (7) Bolt
FIG. 3
STATIC DISCHARGER ON FUSELAGE TAIL CONE (1) Holder; (2) Pipe; (3) Wire; (4) Cube; (5) Bushing; (6) Funnel; (7) Washer
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STATIC DISCHARGING SERVICING 1. Inspection of the static dischargers A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.60.00.A Periodical
E.
Procedures (1) Provide the steps (e.g. B097365N). (2) Place the steps to the right and left wingtip and inspect the dischargers. The following defects are not permitted: corroded or otherwise damaged static discharges. Number of static discharges: •
2 pieces on each aileron, LH and RH
•
1 piece on each wingtip fuel tank, LH and RH
(3) Place the steps to the stabilizer tips and inspect the dischargers. The following defects are not permitted: corroded or otherwise damaged static discharges. Number of static discharges: •
1 piece on each elevator, LH and RH
•
1 piece on each stabilizer tip, LH and RH
(4) Place the steps to the rudder and the fuselage rear section and inspect the dischargers. The following defects are not permitted: corroded or otherwise damaged static discharges. •
2 pieces on the rudder
•
1 piece on the fuselage tail cone (at the position light)
(5) Remove the steps.
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2. Removal of the static dischargers, cleaning their seating areas and installation them again back A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N, B097300N), Multimeter (e.g. EXTECH MG302 or equivalent) Brush
B.
Materials
Grade 000 emery paper Cloth Technical petrol S 1005 lacquer
C. Tools
No. 697 - 4.5x120 screwdriver No. 697 – 6x120 screwdriver
D. Referenced information
023.60.00.B Periodical
E.
Procedures (1) Place the steps (e.g. B097365N and B097300N) to the tail and wing. (2) Place the steps to the right and left wingtip and carry out the maintenance of the static dischargers in accordance with paragraph (5) to (10). Number of static discharges: •
2 pieces on each aileron, LH and RH
•
1 piece on each wingtip fuel tank, LH and RH
The following defects are not permitted: uncleaned contact surface of any of the static dischargers. (3) Place the steps to the stabilizer tips and the elevator and carry out the maintenance of the static dischargers in accordance with paragraph (5) to (10). Number of static dischargers: •
1 piece on each elevator, LH and RH
•
1 piece on each stabilizer tip, LH and RH.
The following defects are not permitted: uncleaned contact surface of any of the static dischargers. (4) Bring the steps to the rudder and the fuselage rear section and carry out the maintenance of the static dischargers in accordance with paragraph (5) to (10). Number of static dischargers: •
2 pieces on the rudder
•
1 piece in the fuselage tail cone (at the position light).
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MAINTENANCE MANUAL The following defects are not permitted: uncleaned contact surface of any of the static dischargers. (5) Using the No. 697 - 4.5x120 screwdriver remove the appropriate static discharger by unscrewing its three fastening screws. (6) Clean contact surface of the static discharger in accordance with the following procedure paragraph (7) and (8). (7) Polish the contact surface to metallic lustre using Grade 000 emery paper. The area treated in this way must be everywhere overlapping the static discharger seating by at least one millimeter. (8) Degrease the polished surface using a clean cloth soaked in technical petrol. (9) Within maximum one hour since the cleaning, fit the appropriate static discharger to its place using the No. 697 - 4.5x120 screwdriver. NOTE:
Be careful to use the screws (including nuts and chamfered washers) in exactly the same arrangement as before the static discharger removal. Replace defective screws, nuts and chamfered washers by new ones.
(10) Measure the contact resistance between static discharger and ground with use the multimeter. (value of contact resistance must be max 600µΩ) (11) After the installation coat the remaining metal-polished spots and protruding screw heads and nuts with S 1005 protective lacquer. (12) Remove the steps.
3. Inspection of the all bonding strips of moving parts. Check of the reliability of their fixations A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N) Steps (e.g. B097300N) B961765N (L410.9615) bogie
B.
Materials
C. Tools
Not applicable No. 697 - 6x120 screwdriver No. 698 - 8x160 screwdriver
D. Referenced information
023.60.00.C Periodical
E.
Procedures (1) Prepare: •
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the steps (e.g. B097365N) for the inspection of the aileron and tail unit areas
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MAINTENANCE MANUAL •
the steps (e.g. B097300N) for the inspection in the areas of wing flap slots, wing flaps, fuselage-to-wing attachment, tail cone and engine nacelles
•
the B961765N (L 410.9615 bogie) for the inspection in the area of the landing gear
(2) Remove the front end cover of the left and right landing gear nacelles by unscrewing 12 + 12 screws using the No. 698 - 8x160 screwdriver. (3) Remove the rear part of the LH side cover (a part of the wing-to-fuselage fairing) by unscrewing 36 screws using the No. 698 - 8x160 screwdriver. (4) Remove a part of the tail unit fairings by unscrewing 70 screws using the No. 697 - 6x120 screwdriver. (5) Remove the access hole lids on the lower LH and RH side of the stabilizer in the area of the rear hinges by unscrewing 4 + 4 screws using the No. 697 - 6x120 screwdriver. (6) Remove the fuselage tail cone as follows: Remove the B096107N (L410.9230) rudder clamp. Unscrew the 24 screws of the cone using the No. 698 - 8x160 screwdriver and the 14 screws using the No. 697 - 6x120 screwdriver. With an assistance of another worker pull the cone away from the fuselage as far as the length of the bonding strip allows. After the inspection fasten the tail cone to the fuselage. (7) Open the nose cone by releasing three locks and fix it in the open position. (8) Open the nose landing gear doors proceeding as follows: Lying on the L 410.9615 bogie loosen and pull out the safety pin of the door control tie (front landing gear bay). Open the doors. (9) Loosen and tilt down the lower engine cowls in accordance with the work procedure outlined in chapter 054. (10) Visual check of the bonding strips between the assemblies specified in the explanatory notes to fig. 301, 302 and 303. The following defects are not permitted: broken, cut, frayed or otherwise mechanically damaged bonding strips, corroded screw joints of the bonding strips. Replace the defected bonding strip for a new one. After replace, measure the contact resistance between bonding strip and ground with use the multimeter. (Permissible values of contact resistances between conductively interconnected parts are stated in the section 024.60.00).
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FIG. 301
ELECTRICAL BONDING OF AIRCRAFT ASSEMBLIES - PART I Legend for fig. - see page 306
FIG. 302
ELECTRICAL BONDING OF AIRCRAFT ASSEMBLIES - PART II Legend for fig. - see page 306
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FIG. 303
ELECTRICAL BONDING OF AIRCRAFT ASSEMBLIES - PART III Legend for fig. - see page 306
Legend to Fig. 301, 302 and 303: Item. No.
ALL
Number of inspection points
1.
Wing-fuselage
2.
Wing flap slat - wing, at ribs No. 10, 15, 20
3+3
3.
Aileron hinge - wing
3+3
4.
Wing flap - wing flap slat at ribs No. 4a,10,15,20
4+4
5.
Stabilizer - fuselage
2
6.
Stabilizer hinge - elevator
2
Stabilizer - elevator
6
Fin - rudder hinge
2
Rudder - hinge
2
Rudder - fin
1
Rudder - fuselage
1
8.
Fuselage - nose landing gear doors
2
9.
Engine - engine mount, LH,RH
2+2
10.
Strut - engine mount, LH,RH
8+8
11.
Fuselage - nose landing gear
1
Fuselage - main landing gear
1+1
7.
EFFECTIVITY
Pairs of electrically bonded assemblies
2
12.
Fuselage - nose cone
4
13.
Fuselage - tail cone
2
14.
Fin - antenna fairing
2
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(11) Fit the front covers of the left and right engine nacelle (12 + 12 screws) using the No. 698 - 8x160 screwdriver. (12) Re-install the removed part of the wing-to-fuselage fairing (36 screws) using the No. 698 - 8x160 screwdriver. (13) Fit the tail unit fairings (70 screws) using the No. 697 - 6x120 screwdriver. (14) Fit the access hole lids on the stabilizer (4+4 screws) using the No. 713 - 6.5x130 screwdriver. (15) Fit the fuselage tail cone (24 screws using the No. 698 - 8x160 screwdriver, 14 screws using the No. 697 - 6x120 screwdriver). Fit the B 069 107 rudder clamp. (16) Tilt down the fuselage nose cone and secure it with 3 locks. (17) Shut the nose landing gear doors, insert and secure the safety pin of the door control tie. (18) Remove the propeller bridle L 410M.9241, close the lower engine cowl with assistance of another worker, lock the eight locks and secure them using the No. 697 - 6x120 screwdriver. Block the propeller with the L 410M.9241 bridle again. (19) Remove the B 097 365 N and B 097 300 N steps and the L 410.9615 bogie.
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COCKPIT VOICE RECORDER (if installed) DESCRIPTION AND OPERATION 1. General The cockpit voice recorder (model specification is optional) ensures the pilot and copilot voice signal recording from VHF communication, intercom and passenger address system. •
installation of the A 100 A Cockpit voice recorder (if installed) - see section 023.71.00
•
installation of the FA 2100 Cockpit voice recorder (if installed) - see section 023.72.00
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COCKPIT VOICE RECORDER (if installed) SERVICING 1. Battery check / Battery replacement of the DK 120 or ELP-362D underwater acoustic beacon A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Lithium battery kit for DK 120 (P/N 810-2007K) Lithium battery kit for ELP-362D (P/N B362-06192-2)
C. Tools
Spanner wrench and other user tool from tools kit
D. Referenced information
023.70.00.A Periodical
E.
Procedures (1) Remove the toilet (if installed) or cover from frame No. 21 panel. (2) Check the battery replacement date label of the underwater acoustic beacon located adjacent to the cockpit voice recorder. If the date has expired, remove the beacon from the mounting cradle. (3) Secure the beacon with vice - clamp, if available, or grasp the body of the beacon. NOTE:
Do not clamp the beacon in a vice, except in the approved vice-clamp.
(4) Using a spanner wrench, remove the end cover marked "BATTERY ACCESS" unscrewing antilock-wise. NOTE:
Spanner wrench should be held firmly in contact with the battery end cap.
(5) Remove shock cushion from battery end of beacon if not removed with the end cap. (6) Top the body in your hand to remove the old battery and shock cushion. (7) Insert the shock cushion into the beacon ensuring that it has reached the bottom. (8) Pull back each of the two outer corners with tweezers, then apply one drop of DUCO cement, or equivalent, under each outer corner. (9) Press the corners down against, the inner surface of the beacon case. Allow at least 20 minutes of drying time. (10) Install a new battery. If the battery in without collar, ensure the end marked "INSERT THIS END".
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CAUTION:
INSTALLING BATTERY WITH INCORRECT POLARITY WILL CAUSE PERMANENT DAMAGE TO THE BEACON. EVEN TEMPORARY INCORRECT POLARITY CAN CAUSE SUBSEQUENT EXCESSIVE CAPACITOR LEAKAGE WHICH MAY RESULT IN A NEW BATTERY BEING DEPLETED WITHIN A FEW DAYS.
WARNING:
INCORRECT BATTERY POLARITY IS PRACTICALLY A SHORT CIRCUIT ACROSS THE BATTERY. IN SAME CASES THIS CAN CAUSE THE BATTERY TO EXPLODE.
(11) Remove the old O-ring from the cover. Do not use a screw driver or sharp tool because of a damage of damaging the O-ring groove. (12) Clean the threads and the O-ring groove in the body and cover thoroughly by wiping with solvent. (13) Apply a thin coating of furnished O-ring lubricant to new O-ring, O-ring groove and threads. Carefully install new O-ring on battery cap. (14) Position rubber shock cushion over contact spring and on the inside of the battery cap. (15) Replace the end cap and tighten until the cap flange contacts the body. Use hand force only on the spanner wrench. (16) Install the beacon to mounting cradle. (17) Reinstall the toilet or cover to frame No. 21. Addresses of underwater acoustic beacon manufactures are as follows: DK120
ELP-362D
Dukane Corporation, (Cage No. 94970),
Benthos, Inc.
Sea Com Division, 2900 Dukane Drive,
49 Edgerton Drive, North Falmouth
St. Charles, II. 60174
MA 02556 USA
www.dukcorp.com/Seacom
www.benthos.com (User’s Manual P/N 001815)
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2. Check of the cockpit voice recorder operation A.
Fixture, Test and Support Equipment
600 Ω impedance earphones
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.70.00.C Periodical
E.
Procedures (1) Self - test •
Connect earphones of 600 Ω impedance to the HEADSET jack of the control console.
•
Depress and hold the TEST button on the control console for at least 5 seconds.
•
Check that a 600 Hz modulated audio signal can be heard in the earphones while the button is depressed.
•
If no faults have been found during the test the test indicator pointer will move to the green field of the display.
(2) Recording check •
Connect earphones of 600 ohm impedance to the HEADSET jack of both control console and the cockpit voice recorder.
•
Cover the area microphone with palm of hand so that it will not pick up voice messages directed to the other microphones.
•
Conduct a check message using the headset and oxygen mask microphone.
•
Make sure that the message can be simultaneously heard in the earphones connected to the control console and in the earphones connected to the cockpit voice recorder.
•
Disconnect the captain’s microphone.
•
Connect the second pilot’s microphone, depress the (transmitter/intercom) and transmit a check message using both the headset and oxygen mask microphone of the second pilot.
•
Make sure that the message can be simultaneously heard in the earphones connected to the control console and in the earphones connected to the cockpit voice recorder.
•
Disconnect the second pilot’s microphone.
•
Uncover the area microphone. Transmit a message using the area microphone.
•
Make sure that the message can be simultaneously heard in the earphones connected to the control console and in the earphones connected to the cockpit voice recorder.
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MAINTENANCE MANUAL (3) Erasure check •
Connect earphones of 600 ohm impedance to the HEADSET jack on the control console
•
Make sure that airplane is properly braked.
•
Apply the parking brake.
•
Depress the ERASE button on the control console and hold it for a period of at least 2 seconds.
•
Make sure that a modulated audio signal can be heard in the earphones connected to the control console.
(4) Check of erasure inhibit function with brake released •
Release the parking brake.
•
Depress and hold the ERASE button on the control console for at least 2 seconds.
•
Make sure that no audio signal can be heard in the earphones while the ERASE button is depressed error when it is released.
•
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Restore the airplane to its original condition
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DK 120 OR ELP 362D UNDERWATER ACOUSTIC BEACON (if installed) DESCRIPTION AND OPERATION 1. Purpose DK 120 or ELP-362D underwater acoustic beacon is fixed on the cockpit voice recorder (if installed). The purpose of the DK 120 or ELP-362D underwater acoustic beacon is to transmit a signal to enable location of an airplane crashed into water.
2. Technical data Operating Frequency:
37.5 kHz (± 1 kHz)
Acoustic Output, Initial:
1060 dynes/cm rms pressure at 1 meter (160.5 dB).
Acoustic Output, after 30 days
700 dynes/cm rms pressure at 1 meter ( 157.0 dB).
Pulse Length:
10 ms
Pulse Repetition Rate
0.9 pulses per seconds
Useful life:
6 years
Operating Life:
30 days minimum
Operating Depth:
20,000 feet (6,096 m)
Actuation:
Fresh or salt water
Size:
1.3 in. (3.3 cm) diameter x 3.92 in. (9.95 cm) long.
Weight:
6.7 oz. (190 g)
Power Source:
Lithium Battery, Field Replaceable
FAA Authorized:
TSO-C121
NOTE:
2
2
Lithium battery is field replaceable by the user.
3. Accessories for DK 120
for ELP-362D
TS 200 Acoustic Test Set
ATS-260 Acoustic Test Set
Lithium Battery Kit 810-2007K
Lithium Battery Kit B362-06192-2
Dukane Spanner Wrench P/N 810-325
Torque adapter for battery replacement P/N 008407
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FIG. 1
DK 120 UNDERWATER ACOUSTIC BEACON
FIG. 2
DK 120 UNDERWATER ACOUSTIC BEACON EXPLODED VIEW SHOWING RELATIVE LOCATION OF BATTERY AND RELATED PARTS
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DK 120 OR ELP 362D UNDERWATER ACOUSTIC BEACON (if installed) SERVICING 1. Battery replacement of the DK 120 or ELP-362D underwater acoustic beacon A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
023.70.01.A Periodical
E.
Procedures Battery check / replacement is described in work procedure 023.70.00.A.
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A 100 A COCKPIT VOICE RECORDER (if installed) DESCRIPTION AND OPERATION 1. General The voice recorder ensures the pilot and copilot voice signal recording from VHF communication, intercom and passenger address system. The A 100 A voice recorder is installed in a short casing and in compliance with international regulations is orange-colour painted.
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
Voice recorder
A 100 A
1
Between frames No. 22 and 23 RH side down
2.
Control console
A 151 B
1
Rear control panel
3.
Circuit breaker VOICE RECORDER AZRGK 10
1
Overhead panel
4.
Pressure switch
0.7S LUN 1492.04-8
1
LH landing gear nacelle
5.
Microphone
A 55 B
1
Next to the overhead panel, LH side
6.
Fuse
6.3 CSN 354733F/ /1500
1
On fuse panel
7.
Impact switch
6895-1-5-5
1
Between frames 22nd and 23rd
8.
Relay
TKE 52 PODGB
1
On 2nd frame
3. Operation The system stand by mode is turned on by switching on the BATTERY I, II switches and VOICE RECORDER circuit breaker located on the overhead panel. The system is switched on automatically by 0.7 S LUN 1492.04-8 pressure switch installed in the hydraulic system (parking brake circuit). The voice recorder is equipped by impact switch which will interrupt voice recorder operating in case crash.
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FIG. 1
BLOCK DIAGRAM OF A100 A VOICE RECORDER
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FA 2100 COCKPIT VOICE RECORDER (if installed) DESCRIPTION AND OPERATION 1. General The cockpit voice recorder provides for conditions record of all communications transmitted or received by radio, of audio signals of navigation receivers, of audio warning signals transmitted by various airborne system, and of voice communications of flight crew members. These voice communications are recorded on four separate channels during all flight phases. The FA2100CVR is a Line Replaceable Unit (LRU) that simultaneously records four separate channels of cockpit audio, converts the audio to a digital format, and stores the data in a solid state memory. The following are the four cockpit audio inputs:
Audio Chanel 1 – Pilot
Audio Chanel 2 – Co-pilot
Audio Chanel 3 – free (not used)
Audio Chanel 4 – Cockpit Area Microphone (CAM)
Abbreviations and Acronyms AMM
Airplane Maintenance Manual
CSMU
Crash Survivable Memory Unit
GSE
Ground Support Equipment connector
L-3AR
L-3 Communications Aviation Recorders (FA 2100 Manufacturer)
LRU
Line Replaceable Unit
PI
Portable Interface
RAU
ROSE Analyzing Unit
RI
Recorder Interface
ROSE
Read Out Support Equipment
ULD
Underwater Location Device
1.1. FA 2100 Recorder Unit The FA2100CVRs are housed in ARINC 404A, 1/2-ATR short cases (refer to Figure 1). The chassis and Crash Survivable Memory Unit (CSMU) are painted international orange. Two reflective stripes are located on the CSMU. The FA2100CVR consists of a chassis and front panel, three Printed Wiring Assemblies (Aircraft Interface PWA, Audio Compressor PWA, and Acquisition Processor PWA), and the Crash Survivable Memory Unit (CSMU). The CSMU contains the solid state flash memory used as the recording medium. An Underwater Locator Device (ULD) (- refer to the AMM section 023.70.01), also referred to as an underwater acoustic beacon, is mounted horizontally on the front of the EFFECTIVITY ALL
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MAINTENANCE MANUAL CSMU and is also used as a the recorder's carrying handle. The ULD is equipped with a battery. Life limit of the battery is mentioned on the ULD shield. The ULD meets or exceeds the requirements of FAA TSO–C121. The Ground Support Equipment (GSE) connector is located on the front of the FA2100CVR. This connector provides the interface from the recorder to GSE for checkout of the recorder, or to transfer data to a readout device. The FA2100CVR is connected to aircraft wiring via a 57-pin, DPXBstyle connector.
FIG. 1
FA2100 COCKPIT VOICE RECORDER UNIT
The cockpit voice recording system comprises the following:
FA 2100 voice recorder
S151 / S161 control unit
S055 / S056 remote microphone
6895-D-2-5-5-X inertial switch
0.7 S LUN 1492.04-8 pressure switch (if installed)
In the event of an airplane crash the voice recorder is switched off automatically by the inertia switch.
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MAINTENANCE MANUAL 2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1
Circuit breaker
AZRGK-5 or KLIXON 7277-2-5
1
Between frames No. 1 and 2
2
Control unit
S 151 (S151-0030-00) or S 161 (S161-0030-00)
1
Rear control panel
3
Microphone
S 055 (S055-0065-00) or S 056 (S056-0047-00)
1
Center instrument panel
4
Voice recorder (120 min.)
FA 2100 (2100-1020-02)
1
Between frames No. 22 and 23
5
Inertial switch
6895-D-2-5-5-X (91079085)
1
Between frames 22nd and 23rd
6
Fuse or Circuit breaker
1 CSN 354733F/1500 or KLIXON 7277-2-1
1
Fuse panel
7
Relay
TKE 52 PODGB
2 1
Between frames No. 7 and 8 Between frames No. 10 and 11
8
Relay (if installed)
B 073 576 N
1
Frame 21
9
Connector CVR DATA OUT (if installed)
CAN 26 Z
1
Frame 21
10
Circuit breaker CVR POWER (if installed)
KLIXON 7277-2-1
1
Frame 21
11
Pressure switch (if installed)
0.7S LUN 1492.04-8
1
LH landing gear nacelle
3. Operation The system standby mode is turned on by switching on the BATTERY , , switches and INTERCOM , , circuit breakers located on the overhead panel. The cockpit voice recorder is not provided with a separate element to switch it on. It is switched on when electrical power is supplied or when the flight data recorder is switched on. The cockpit voice recorder is not provided with a separate element to switch it off. It is switched off when electrical power is removed. Switch off the BATTERY , , switches and INTERCOM , , circuit breakers located on the overhead panel. The recorded data can be read or downloaded in accordance with procedure as described in section SERVICING. st
The cockpit voice recorder system can be provided with the CVR DATA OUT connector (on the 21 frame) for the recorded data reading or downloading into the airplane - see Fig. 2 - on request of the operator. NOTE:
More information are described in "Installation and Operation Instruction Manual Model FA2100 CVR" P/N 165E1846-00, Rev. 14 from March 2010, or later appropriate revision and Airplane Flight Manual.
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FIG. 1
BLOCK DIAGRAM OF COCKPIT VOICE RECORDING SYSTEM
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FIG. 2
INSTALLATION OF THE CVR DATA OUT CONNECTOR (IF INSTALLED) (1) Connector CVR DATA OUT; (2) Circuit breaker CVR POWER; (3) Sockets
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FA 2100 COCKPIT VOICE RECORDER (if installed) SERVICING 1. CVR Data Readout or Download A.
Fixture, Test and Support Equipment
Refer to the Steps (1), (2) and (3)
B.
Materials
Not applicable
C. Tools
Necessary tools from the tool kit
D. Referenced information
-
E.
Procedures Recorded data can be downloaded from CVR memory with possibilities mentioned in step (2) or (3).
CONTENTS OF THE PROCEDURE: (1) Downloading Cable Installation (2) Download with RAU unit (a) RAU pre setting (b) ROSE – New Aircraft Configuration (c) Download with RAU unit using CICC/2 Computer Interface Communication Cable P/N 17TES0070 / 17TES0072 or CICC/3 Computer Interface Communication Cable 17TES0075 / CAT5 (3) Download with Portable Interface Unit (a) Download with Portable Interface (PI) unit, P/N 17TES0043 or Download with Portable Interface/2 (PI/2) unit, P/N 17TES0062 (b) Conversion of .cvr file downloaded via PI or PI/2 Portable Interface with ROSE Software and play back.
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MAINTENANCE MANUAL PROCEDURE: (1) Downloading Cable Installation For downloading or readout (play back) data in the aircraft from recorder memory the downloading cable P/N 17TES0078 must be installed as shown in Figure 301. Before the downloading cable installation make sure that CVR power is switched off (circuit breakers on the overhead panel BATTERY I, II, INTERCOM I, II or/and RECORDER).
FIG. 301
“ON-AIRCRAFT” SETUP EXAMPLE FOR DATA DOWNLOAD FA2100CVRS USING A DOWNLOADING CABLE 17TES0078 AND PORTABLE INTERFACE (PI) 17TES0043
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MAINTENANCE MANUAL NOTE:
Note: Downloading cable installation is necessary for all procedures described in Step (2) or (3).
NOTE:
st
If connector CVR DATA OUT and circuit breaker CVR POWER (on 21 frame – refer to the A-Option in the Fig. 2) is installed, downloading cable 17TES0078 installation is not required. st
If connector CVR DATA OUT and sockets for interconnection (on 21 frame – refer to the B-Option in the Fig. 2) is installed, downloading cable 17TES0078 installation is not required. For interconnection of sockets use wiring with two "banana"-plugs. (2) Download with RAU unit: For data downloading from CVR memory is required:
Downloading Cable P/N 17TES0078 and
ROSE Analysis Unit (RAU), P/N: 17TES0055 (or equivalent laptop) with ROSE/RI Software, Version 3.9 or higher, P/N: 17TES0321 (CDROM) and
ROSE/RI Software manual 165E1696-02 or higher and
Computer Interface and Communications Cable CICC/2, P/N: 17TES0070 and Cable Adapter 17TES0072 or
Computer Interface and Communications Cable CICC/3, P/N: 17TES0075 with CAT5 Crossover Ethernet Cable P/N: 024-98-00368
NOTE:
For ROSE/RI software installation and hardware requirements see procedure mentioned in AMM section 031.35.00 - Work procedure 031.35.00.A, Steps (1), (2) and (3).
(a) RAU pre setting In RAU unit running system Windows XP Professional, SP3 click on Start – All Programs – Accessories – Windows Explorer. In Windows Explorer window click on option Tools and next to Folder Option. In new window Folder Option click on option View and activate Show hidden files and folders and deactivate Hide extension for known file types as shown in Figure 302.
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FIG. 302
WINDOWS EXPLORER SETTINGS Next click on button Apply and next click on button OK. (b) ROSE – New Aircraft Configuration 1. Run ROSE software and login as administrator (see Work procedure 031.35.00.A, Step (4-h)) 2. In ROSE Main Menu click on button Select Aircraft Configuration. 3. In window Aircraft Configuration click on button New and create new aircraft configuration for corresponding aircraft serial number as shown in Figure 303 where: a. Enter a New Configuration Name – insert new database name where last four numbers are corresponding with last four numbers of aircraft serial number b. Configuration Description – insert text as shown in figure 303
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MAINTENANCE MANUAL Aircraft Information field: c. Make and Model: – insert aircraft model d. Serial Number(s): – insert aircraft serial number e. Tail Number(s): - insert tail number or aircraft registration mark Flight Data Recorder Information field: f. Make and Model: – select from the list: L-3 Communications (Fairchild), FA2100, g. Part Number: - select from the list: 2100-1020-() h. Data Type: select from the list: 717 i. Click OK
FIG. 303
AIRCRAFT CONFIGURATION MENU – NEW CONFIGURATION
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MAINTENANCE MANUAL (c) Download with RAU unit using CICC/2 Computer Interface Communication Cable P/N 17TES0070 / 17TES0072 or CICC/3 Computer Interface Communication Cable 17TES0075 / CAT5 1.
Make sure that downloading cable as requested in Step (1) is installed.
2.
Connect Interface cable CICC/2 between FDR unit and RAU as shown in Figure 304 or Interface cable CICC/3 between FDR and RAU as shown in Figure 305.
FIG. 304
“ON AIRCRAFT” SETUP FOR FA2100 RECORDERS USING A COMPUTER INTERFACE COMMUNICATIONS CABLE/2 (CICC/2)
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FIG. 305
“ON AIRCRAFT” SETUP FOR FA2100 RECORDERS USING A COMPUTER INTERFACE COMMUNICATIONS CABLE/3 (CICC/3) 3.
Switch on the circuit breakers BATTERY I, II and INTERCOM I on the overhead panel.
4.
Run ROSE software on the RAU.
5.
Click on Select Aircraft Configuration and chose appropriate Configuration Database corresponding with aircraft serial number. If doesn’t exist corresponding Configuration Database create it in accordance with procedure in Step (2-b).
6.
In ROSE Main Menu click on Recorder Interface, select appropriate CICC cable and click Connect.
7.
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Recorder Status should be as shown in Figure 306.
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MAINTENANCE MANUAL
FIG. 306
RECORDER STATUS 8.
In ROSE Main Menu click on button Import/Export Flight Data and in window Flight Data File Control click on button Import New Data as shown in Figure 307
FIG. 307
FLIGHT DATA FILE CONTROL MENU 9.
In the window Flight Data File Control in the field Enter New File Name insert filename of the new file. In the field New File Type select ROSE raw frame type, as Source of Data select option Flight Recorder. In Data Dump Option select Dump All Audio Data (this option means that full memory of the CVR will be downloaded) or Dump All Data from Last Hrs Mins (this option means that this option will create a local data file containing the user-specified number of hours and minutes of data from either the currently-connected recorder) as shown in Figure 308.
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FIG. 308
FLIGHT DATA FILE CONTROL MENU 10.
Whenever all above mentioned option is set click on button OK. On screen will appear window Flight Data Process transferring audio data from recorder memory to local disc as shown in Figure 309.
FIG. 309
PROCESS OF AUDIO DATA TRANSFERRING FROM CVR MEMORY TO LOCAL DISC 11.
If the data transferring process finish then will appear window as shown in Figure 310 and click on button Yes and then a Decompress Audio Data menu will appear as shown in Figure 311.
FIG. 310
DUMP DATA COMPLETE
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FIG. 311
DECOMPRESS AUDIO DATA MENU 12.
Select the channels to decompress then select the Start button to begin the decompression. A Decompression status message will appear at the bottom of the menu as shown in Figure 312.
FIG. 312
DECOMPRESS AUDIO DATA 13.
If decompression process is finished, will appear window of the successfully decompression as shown in Figure 4-13
FIG. 313
DECOMPRESS PROCESS COMPLETED
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MAINTENANCE MANUAL 14.
Close all windows of ROSE program.
15.
Switch-off circuit breakers BATTERY I, II, and INTERCOM I on the overhead panel.
16.
Disconnect CICC/2 or CICC/3 cable and remove 17TES0078 Downloading Cable from the aircraft. Install back CVR unit to the mounting rack.
17.
Run program Windows Explorer and select directory path:
C:\Program Files\L-3 Com\ROSE\Data_Files\CVR_FA2100 as shown in Figure 314
FIG. 314
EXAMPLE OF LOCATION OF THE .WAV FILES 18.
Play back .wav files with Windows Media Player to hear audio data of each channel. Audio data are recorded to channels as follows:
CVR_1428_test_H1.wav – audio channel - Pilot
CVR_1428_test_H2.wav – audio channel - Co-pilot
CVR_1428_test_H3.wav – not in use
CVR_1428_test_H4.wav – cockpit area microphone (CAM)
NOTE:
Dumped compressed file (.cvr) and audio channels decompressed files (.wav) are automatically downloaded and converted to folder name which corresponding with Aircraft Configuration Selection in ROSE Main menu.
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MAINTENANCE MANUAL (3) Download with Portable Interface Unit: For compressed audio data downloading from CVR memory is required ROSE Analyzing Unit – RAU:
Downloading Cable P/N 17TES0078 and
Portable Interface (PI) Kit P/N 17TES004 and Portable Interface (PI) Operator’s Manual P/N 165E1630-00 or
Portable Interface 2 (PI/2) Kit P/N 17TES0062 and Portable Interface/2 (PI/2) Operator’s Manual P/N 165E1630-01
(a) Download with Portable Interface (PI) unit, P/N 17TES0043 or Download with Portable Interface/2 (PI/2) unit, P/N 17TES0062 1.
Make sure that downloading cable as requested in Step (1) is installed
2.
Connect Portable Interface (PI) or Portable Interface/2 (PI/2) through GSE connector to CVR unit FA2100. How to connect portable interface to flight recorder follows instruction mentioned in 165E1630-00 Operator’s Manual for (PI) and 165E1630-01 Operator’s Manual for (PI/2).
3.
Switch on the circuit breakers BATTERY I, II and INTERCOM I on the overhead panel.
4.
In accordance with instruction mentioned in PI or PI/2 Operator’s Manual:
download compressed data (data file with extension .cvr) to the PI or PI/2 memory card, usb flash, etc.
playback audio data
5.
Switch-off circuit breakers BATTERY I, II, and INTERCOM I on the overhead panel.
6.
Disconnect PI or PI/2 from CVR unit and remove 17TES0078 Downloading Cable from the aircraft. Install back CVR unit to the mounting rack.
(b) Conversion of .cvr file downloaded via PI or PI/2 Portable Interface with ROSE Software and play back. 1.
Start RAU unit with Rose software and
2.
In ROSE Main Menu select appropriate Aircraft Configuration corresponding to serial number of the aircraft
3.
If appropriate Aircraft Configuration doesn’t exist, create it in accordance with Step (2-b).
4.
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Copy downloaded file with PI or PI/2 to the RAU local disc to the appropriate directory.
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MAINTENANCE MANUAL 5.
In ROSE main menu click on button Utilities and then click on button Create Wavefiles as shown in Figure 315
FIG. 315
UTILITIES MENU 6.
In window Compressed Audio File Path select .cvr file for transferring to .wav file. If file is selected click on Open button and will appear the Decompress Audio Data menu as shown in Figure 311.
7.
Follow procedures 12, 13, 14, 17 and 18 from Step (2-c) to play back .wav files (audio channels).
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FA 2100 COCKPIT VOICE RECORDER (if installed) REMOVAL / INSTALLATION 1. Removal and installation of the FA 2100 CVR Unit A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Necessary tools from tool kit
D. Referenced information
-
E.
Procedure (1) Removal of the FA 2100 Cockpit Voice Recorder (a) Before un-installation CVR unit switch off all switches and circuit breakers (b) Open the main door, install the entrance steps. (c) Remove the toilet (if installed) according WP mentioned in Chapter 38. (d) Un-screw the two securing ratchet nuts and pull out the CVR unit (located between frames No. 22 -23) from the CVR main frame. (2) Installation of the FA 2100 Cockpit Voice Recorder (a) Set the CVR unit to the CVR Main frame. (b) Tighten a two securing ratchet nuts (c) Perform the work procedure 023.70.00.C. (d) Install the toilet (if installed) according WP mentioned in Chapter 38.
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ELECTRICAL POWER
MAINTENANCE MANUAL
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MAINTENANCE MANUAL CHAPTER 24 ELECTRICAL POWER CONTENTS Subject
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GENERAL 024.00.00 Description and Operation General Maintenance practices General Servicing Check of the electric equipment in the passenger cabin ceiling between the frames No. 8 and 9 and between the frames No. 1 and 2 Inspection of the plug-and-socket connections Check of the condition of negative terminals Inspection of the electrical equipment in space between frames No. 8 and 10 and behind the fire walls of the engine nacelles Inspection of the wiring cables connection plug-socket (without dismantling) and the terminal blocks Check of the starter-generators voltage setting Check of the operation of all circuit breakers not operating as switches
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AC GENERATION POWER Description and Operation General List of components Description Operation Servicing Check of the operation of inverters 36 V Check of the operation of inverters 115 V Check of the automatic switching of inverters 36 V Check of the inverters 115 V automatic switching-over Check of the over-switching of the inverters 26 V (if installed)
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LUN 2450 OR LUN 2450-8 THREE-PHASE INVERTER Description and Operation Purpose Technical data Operation Removal / Installation Removal and installation of LUN 2450 or LUN 2450-8 three-phase inverter
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Removal / Installation Removal and installation of the LUN 2460 inverter LUN 2102-8 OR LUN 2102.01-8 ALTERNATOR Description and Operation Purpose Technical data Operation Servicing Check of the fixing and measure the insulation resistances of the LUN 2102-8 or the LUN 2102.01-8 alternator Check of the LUN 2102-8 or LUN 2102.01-8 alternator Removal / Installation Removal/Installation of the LUN 2102-8 or LUN 2102.01-8 alternator LUN 2147-8 OR LUN 2147.01-8 OR LUN 2147.02 REGULATOR Description and Operation Purpose Technical data Operation RS 5 (8) (A 100) DISTRIBUTION BOX (if installed) RS 6 (8) (A 100) DISTRIBUTION BOX (if installed) Description and Operation Purpose Technical data Operation
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RP 5 (8) (A 131) RELAY SWITCH (IF INSTALLED) B571084N RELAY SWITCH (IF INSTALLED) Description and Operation Purpose Technical data Operation
024.20.08
1
ALL
TKD 303 DOD, TKD 133 DOD CONTACTOR Description and Operation Purpose Technical data Operation
024.20.09
1 1 1 1 1
ALL
TKD 501 DOD CONTACTOR Description and Operation Purpose Technical data Operation
024.20.10
1 1 1 1 1
ALL
EFFECTIVITY: ALL
1 1 1 1
024-CONTENTS Page: 2 May 30/14
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
TKE 52 PODG, TKE 54 PODG RELAY Description and Operation Purpose Technical data Operation
024.20.11
1 1 1 1 1
ALL
15N 599 19.7 RELAY Description and Operation Purpose Technical data Operation
024.20.12
1 1 1 1 1
ALL
B073576N OR B073576N /G RELAY Description and Operation Purpose Technical data Operation
024.20.13
1 1 1 1 1
ALL
B073245N RELAY Description and Operation Purpose Technical data Operation
024.20.14
1 1 1 1 1
ALL
VF 0.4 - 45, VF 0.4 - 150 VOLTMETER Description and Operation Purpose Technical data Fault Isolation Removal / Installation Installation of VF 0.4 - 45, VF 0.4 - 150 voltmeters Adjustment / Test Check of VF 0.4 - 45, VF 0.4 - 150 voltmeters
024.20.15
1 1 1 1 101 401 401 501 501
ALL
SPC-5(C) STATIC INVERTER Description and Operation Purpose Technical data
024.20.16
1 1 1 1
ALL
DC CURRENT SOURCES Description and Operation General List of components Operation Servicing Inspection of switches in the pilot cockpit
024.30.00
1 1 1 1 3 301 301
ALL
LUN 2132.02-8 STARTER - GENERATOR Description and Operation Purpose Technical data Operation Servicing Functional check of the LUN 2132.02-8 starter - generator
024.30.01
1 1 1 1 1 301 301
ALL
EFFECTIVITY: ALL
024-CONTENTS Page: 3 Nov 15/13
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
LUN 2167.03-8 REGULATOR Description and Operation Purpose Technical data Operation Servicing LUN 2167.03-8 regulator functional check Removal / Installation Removal and installation of the LUN 2167.03-8 regulator
024.30.02
1 1 1 1 1 301 301 401 401
ALL
DMR - 400 DSP DIFFERENTIAL RELAY Description and Operation Purpose Technical data Operation Servicing Inspection of the contacts of the DMR-400 DSP differential relay
024.30.03
1 1 1 1 1 301 301
ALL
20 NKBN-25 OR SAFT P/N 26108 ACCUMULATOR BATTERY 024.30.04 Description and Operation Purpose Technical data Servicing Check of the voltage of accumulator batteries Inspection of the accumulator batteries Inspection of the accumulator battery bay between the No. 1-2 frames Charging of the accumulator batteries Preservative of the accumulator battery bay Removal / Installation Removal and installation of the accumulator batteries
1 1 1 1 301 301 302 302
ALL
VARTA / HAWKER 20 FP 25 H1C (T-R) ACCUMULATOR 024.30.05 BATTERY Description and Operation Purpose Technical data Servicing Monthly checks on aircraft of the VARTA / HAWKER accumulator batteries Quarterly maintenance of the VARTA / HAWKER accumulator batteries Annual maintenance of the VARTA / HAWKER accumulator batteries Testing the temperature sensor (if installed) Removal / Installation Removal and installation of the accumulator batteries
1
EFFECTIVITY: ALL
303 304 401 401 ALL
1 1 1 301 301 302 308 315 401 401
024-CONTENTS Page: 4 May 30/14
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
TKS 201 DOD, TKS 401 DOD CONTACTOR Description and Operation Purpose Technical data Operation
024.30.06
1 1 1 1 1
ALL
TKD 511 DOD CONTACTOR Description and Operation Purpose Technical data Operation
024.30.07
1 1 1 1 1
ALL
LUN 2743.XX-8 VOLTAMMETER Description and Operation Purpose Technical data Servicing Check of the LUN 2743.XX-8 voltammeter Removal / Installation Removal and installation of the LUN 2743.01-8 voltammeter
024.30.08
1 1 1 1 301 301 401 401
ALL
ShA - 440 (8) SHUNT Description and Operation Purpose Technical data Servicing Inspection of the ShA - 440(8) shunt
024.30.09
1 1 1 1 301 301
ALL
RG–CIS25 VALVE REGULATED LEAD – ACID AIRPLANE BATTERY (IF INSTALLED) Description and Operation General Purpose Technical data Servicing Check of the voltage of RG-CIS25 accumulator batteries Inspection of the RG-CIS25 accumulator batteries Charging of the RG-CIS25 accumulator batteries Removal / Installation Removal and installation of the RG-CIS25 accumulator batteries
024.30.10
1
ALL
EXTERNAL POWER Description and Operation General Technical data Operation Servicing Ground power unit connecting Ground power unit disconnection
024.40.00
EFFECTIVITY: ALL
1 1 3 3 301 301 301 302 401 401 1 1 1 1 1 301 301 301
ALL
024-CONTENTS Page: 5 Nov 20/15
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
ShRAP 500 EXTERNAL POWER SOURCE SOCKET Description and Operation Purpose Technical data Operation Servicing Check of the ShRAP 500 external power source socket
024.40.01
1 1 1 1 1 301 301
ALL
ELECTRICAL LOAD DISTRIBUTION Description and Operation General Servicing Check of the operation of the automatic switching of bus bars Measurement of the voltage values at the connection of A 71 and A 72 contactors
024.50.00
1 1 1 301 301
ALL
CIRCUIT BREAKING ELEMENTS-FUSES, CIRCUIT BREAKERS Description and Operation General Technical data Operation
024.50.01
V 016 OR V 016.01-8 ELECTROMAGNETIC RELEASING SWITCH Description and Operation Purpose Technical data Description Operation Servicing Functional check of the V 016 or V 016.01-8 electromagnetic releasing switch
024.50.02
CONDUCTORS Description and Operation General Marking of instruments and conductors
024.50.03
1 1 1 1
ALL
BRIDGING AND EARTHING Description and Operation Purpose Technical data
024.60.00
1 1 1 1
ALL
EFFECTIVITY: ALL
302 1
ALL
1 1 1 1 1
ALL
1 1 1 1 1 301 301
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MAINTENANCE MANUAL
GENERAL DESCRIPTION AND OPERATION 1. General The main sources of the electrical power for the aircraft are two starter - generators having voltage of 28 V, each having the power output of 5.6 kW. As an emergency source are used two NiCd batteries having voltage of 24 V and each capacity of 25 Ah. Electrical appliances for alternating current are supplied with the power from two LUN 2450 static inverters having voltage 3x36 V / 400 Hz, two PC - 250 static inverters having voltage 115 V / 400 Hz and 26 V / 400 Hz (one of which is a stand - by inverter) and two LUN 2102 or LUN 2102.01 alternators having voltage 3x115 V / 200 Hz. Inverters are supplied from the direct current board network of 28 V. During ground servicing, the aircraft can be connected to a DC external power source of 27 to 29 V.
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INTENTIONALLY LEFT BLANK
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MAINTENANCE MANUAL
GENERAL MAINTENANCE PRACTICES 1. General A.
B.
The components removed from the aircraft for laboratory test must be inspected for: •
visible mechanical damage of the body
•
corrosion of plug-and-socket connectors, terminals, pushbuttons
•
deformation of plug-and-socket connector pins
•
deposits of dirt
•
evidence of fluid leaks
When removing a unit (a component) from the aircraft (for laboratory test or replacement), its place of installation, connector or pipe mating parts must be inspected for: •
mechanical damage (cracks) of the place of installation
•
wear of the attachment holes
•
corrosion and deformation of plug-and-socket connector pins
•
dents
•
ruptures
•
deformation of pipe connecting parts
•
damage of connector and pipe union nut threads
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GENERAL SERVICING 1. Check of the electric equipment in the passenger cabin ceiling between the frames No. 8 and 9 and between the frames No. 1 and 2 A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Z 37.9110-10 Screwdriver No. 697-6x120 Screwdriver No. 697-4.5x120 Screwdriver L 410.9141-05 Screwdriver
D. Referenced information
024.00.00.A Periodical
E.
Procedures (1) Check if the external ground power source has been disconnected and if the switches BATTERY I, II on the overhead panel are shut off. (2) Remove 2 covers between frames No. 1 and 2 on RH side after unscrewing 18 universal quick locks by means of Z 37.9110-10 screwdriver and 13 screws by No. 697-6x120 screwdriver. (3) Remove the contactors box cover after unscrewing 6 screws by means of No. 697-4.5x120 screwdriver in the space between No. 1 and 2 frame on the RH side. (4) Remove the upholstery of the passenger cabin ceiling in the space between No. 8 and 9 frame by unscrewing 4 quick-locks by means of L 410.9141-05 screwdriver. (5) Remove the cover of the contactors panel between the 8 and 12 frame on the RH side by unscrewing 3 screws by means of No. 697-4.5x120 screwdriver. (6) Inspect the state of electric installation in space between the 1 and 2 frame at the RH side. The following defects are not permitted: •
broken or worn conductor
•
corrosion on electric connections
•
burning on electric connections
•
loosened coupling material
•
loosened units (devices)
•
cracking at a securing varnish
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MAINTENANCE MANUAL •
cracked or loosened clamps
(7) Check the state of electric installation between the 8 and 9 frame. The following defects are not permitted: •
broken or worn conductor
•
corrosion on electric connections
•
burning on electric connections
•
loosened coupling material
•
loosened units (devices)
•
cracking at a securing varnish
•
cracked or loosened clamps
(8) Fit on the upholstery in the passenger cabin ceiling by means of L 410.9141-05 screwdriver. (9) Fit on the cover of the contactors panel between the 8 and 9 frame by screwing on 6 screws by means of No. 697-4.5x120 screwdriver. (10) Fit on the cover of the contactors box between the 1 and the 2 frame, at the RH side, by screwing on 6 screws by means of No. 697-4.5x120 screwdriver. (11) Cover up the space between the 1 and 2 frame, at the RH side, by setting up 2 covers and screwing on 18 universal quick locks, by means of Z 37.9110-10 screwdriver and 13 screws by means of No. 697-6x120 screwdriver.
2. Inspection of the plug-and-socket connections A.
Fixture, Test and Support Equipment
Steps (e.g. B097365N)
B.
Materials
dia. 0.5 mm Lock wire ONL 3450 Perforated tape ONL 3451.1 Button
C. Tools
No. 697-3.5x100 Screwdriver No. 697-6x120 Screwdriver Z 37.9110-10 Screwdriver Flat-nosed pliers
D. Referenced information
024.00.00.B Periodical
E.
Procedures (1) Put the steps (e.g. B097365N) to the aircraft.
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MAINTENANCE MANUAL (2) Dismount the front aerodynamic wing-fuselage fillet by unscrewing 33 screws by means of No. 697 - 6x120 and Z 37.9110-10 screwdrivers. (3) Dismount the covers of the mounting holes on the wing fillets (LH, RH) by screwing-off 40 screws by No. 697 - 6x120 screwdriver. (4) Loosen and tilt down the lower covers of LH and RH engine nacelles. (5) Dismount the tail cover of the fuselage - screw off 69 screws by Z 37.9110-10 screwdriver. (6) Check of the P - S connections: •
in space of the aerodynamic wing-fuselage fillet V1, V2, V3, V4, V5, V10, V19, V20, V25, V26
•
in space of the wing-engine fillet (LH, RH) V5, V6, V7, V8, V11, V12, V15, V16, V225, V226
•
in space of the engine (LH, RH) V33, V34, V227, V228
•
in space at the 27 frame: V14, V21, V212
One-by-one unlock and disconnect the plug-and-socket connections and check them. The following defects are not permitted: Damaged (punctured) covers of the plug-and-socket connections, corrosion of the plug-and-socket connections, blackened and oxidized pins and bushings of the plug-and-socket connections. Replace the damaged P-S connections by new ones, remove the corrosion and the blackening according to work procedure. Work procedure: "Sealing of connectors" is mentioned in AMM section 020.20.00. NOTE:
When checking make sure the external ground power source is disconnected.
(7) Loosen 4 screws of the frame aerial of the radio-compass (if installed) by No.697 – 3.5x100 screwdriver and check the connector according to step (6). (8) Reconnect all plug-and-socket connections, their securing with a locking wire ∅ 0.5, and the setting on of its coverings and fixing by ONL 3450 perforated tape with ONL 3451.1 button. (9) Install the radio-compass (if installed) frame aerial (4 screws), clean the framing points with emery cloth No.400, cover the aerial by a laminate covering (20 screws) – and provide a perfect sealing. (10) Re-install the wing-fuselage aerodynamic fillet (33 screws), covers in the wing-engine aerodynamic fillet (LH, RH) 40 screws, the tail covering of a fuselage (69 screws) by means of Z 37.9110-10 screwdriver - shut and fix the lower covers of LH and RH engine nacelles. (11) Remove steps.
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3. Check of the condition of negative terminals A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
ALKAPRENE Adhesive
C. Tools
No. 697-6x120 Screwdriver, CSN 230611-14x17 Wrench
D. Referenced information
024.00.00.C Periodical
E.
Procedures (1) Dismount the RH pilots’ seat according to work procedure in the chapter 025. Wrench off partly the carpet on the foot board of the pilots’ floor on the right side. Dismount the periphery cover from the floor by screwing off 36 screws by No. 697 - 6x120 screwdriver. (2) Release and tilt down the lower covers of LH and RH engine nacelles. (3) Inspect the negative terminals: •
V 93, V 94 (on the bottom side of the wing in space of the LH hand and RH hand engines)
•
V 211-1-2 (below the floor of the RH pilot)
•
V 73-1 (between the 1 and 2 frame on the LH side, under accumulators)
(4) Check the state of the framing points V 93, V 94, V 211-1-2, V 73-1 by CSN 230611 - 14x7 wrench. The following defects are not permitted: loosened nuts, corrosion. Tighten loosened nuts and remove the corrosion according to work procedure. (5) Cover the opening in the pilots’ floor - 36 screws by No. 697 - 6x120 screwdriver stick back the wrenched off carpet with ALKAPRENE, mount back the right hand pilots’ seat into four pins, secure it by the plugs. (6) Close and fasten the lower covers of the LH and RH engine nacelles.
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4. Inspection of the electrical equipment in space between frames No. 8 and 10 and behind the fire walls of the engine nacelles A.
Fixture, Test and Support Equipment
Steps (e.g. B097300N), Steps (e.g. B097365N), Hand lamp
B.
Materials
Technical petrol Duster cloth
C. Tools
No. 697-6x120 Screwdriver 8x10 CSN 230611.6 Two-sided wrench Z 37.9110-10 Screwdriver
D. Referenced information
024.00.00.D Periodical
E.
Procedures (1) Put steps (e.g. B097300N and B097365N) to the aircraft. (2) By means of No. 697-6x120 dismount the rear covers (1) - refer to the fig. 301, on the upper skin of the left wing, the front (2) and the rear (3) covers of the upper skin on the right wing. (3) By means of 8x10 CSN 230611.6 two-side open-end wrench and of Z 37.9110-10 adapted wrench unscrew and take off the screws which fix the rear covering of the engine nacelle (LH and RH) (4), (5). (4) By means of the hand lamp check the openings on the upper skin of the wing - the space between the 8 and 10 rib. The following defects are not permitted: dirty space, damaged and non-fixed aggregates and electric equipment between the 8 and 10 rib of the LH and RH wing and dirty space behind the fireproof wall of the engine nacelle. Remove the uncleanness by technical petrol, fasten the non-fixed aggregates and electric equipment and repair or replace the damaged ones. NOTE:
The cleanliness, damage and fixing of the electric equipment and aggregates should be especially checked.
(5) Check the space behind the fireproof wall. Check if there is any dirty space behind the fireproof wall of the engine nacelle. Remove the uncleanness by technical petrol, fasten the non-fixed aggregates and electric equipment and repair or replace the damaged ones. NOTE:
The cleanliness, damage and fixing of the electric equipment and aggregates should be especially checked.
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MAINTENANCE MANUAL (6) By means of 8x10, CSN 230611.6 two-side open-end wrench and of Z 37.9110-10 adapted wrench tighten the screws fixing the rear covering of the LH and RH engine nacelles. (7) By means of No. 697-6x120 screwdriver tighten the screws fixing the rear covers on the upper skin of the left wing, as well as the front and rear covers on the upper skin of the right wing. (8) Remove steps.
FIG. 301
LOCATION OF COVERS
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5. Inspection of the wiring cables connection plug-socket (without dismantling) and the terminal blocks A.
Fixture, Test and Support Equipment
Steps (e.g. B097300N) Assembly floor into the space behind 21 bulkhead
B.
Materials
2
PYROPLAST Textile (0.5 m ) ONL 3450 Perforated tape (2 m) ONL 3451 Button (10 pcs) ∅ 0.5 mm Binding wire (3 m)
C. Tools
L 410.9141-05 Screwdriver L 410.9141-06 Screwdriver Z 37.9110-10 Screwdriver No. 697-4.5x120 Screwdriver No. 697-6x120 Screwdriver
D. Referenced information
024.00.00.E Periodical
E.
Procedures (1) Open successively the spaces between frames No. 7 and 16 in the passenger cabin ceiling, remove the upholstered coverings by means of L 410.9141-05 screwdriver. (2) Release the ceiling panel - loosen 8 screws by No. 697-4.5x120 screwdriver in the pilots’ cockpit and tilt it down. (3) Dismount the toilet according to the work procedure in the chapter 38 and load the assembly floor. (4) Loosen (by hand) 2 pieces of side adjusting screws fixing the instrument panels and tilt it down. (5) Put steps (e.g. B097300N) to the engine nacelle (LH and RH) release the lower cover of the engine nacelles and tilt it down. (6) Remove the coverings of the nose part of the fuselage on the right side - from the 2 to the 4 frame - by loosening 18 quick - locks by Z 37.9110-10 screwdriver and 13 screws by No. 697 - 6x120 screwdriver. (7) Successively check the plug-and-socket connections, cables and terminal blocks in the spaces which had been made accessible. The following defects are not permitted: Damaged insulation of the conductors, bad fixing cables, loosened plug-and-socket connections, damaged binding wire, loosened conductors in the terminal blocks and at the circuit breakers. Repair the damaged insulation of the conductors, the cables touching the sharp edges should be protected by the textile PYROPLAST, fasten the free cables by ONL 3450 perforated tape and
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MAINTENANCE MANUAL ONL 3451.1 button, fasten the loosened plug-and-socket connections, replace the damaged binding by a new locking wire. (8) Install the coverings on the nose part of the fuselage - between the 2 and 4 frames on the RH side - fasten the 18 quick locks by Z 37.9110.10 screwdriver and 13 screws by No. 697 - 6x120 screwdriver. (9) Shut and fasten the lower cover of the LH and RH engine nacelles and remove steps. (10) The instrument panel should be put in its place and 4 screws fastened by hand. (11) Take out the assembly floor behind the 21 frame and install the toilet according to work procedure in the chapter 038. (12) Close up the ceiling panel and fasten it by 8 screws by means of No. 697 - 4.5x120 screwdriver. (13) Close the upholstered coverings of the passenger cabin ceiling by the locks by means of L 410.9141-05 screwdriver.
6. Check of the starter-generators voltage setting A.
Fixture, Test and Support Equipment
Mobile digital voltmeter 0 to 50 V External ground power supply
B.
Materials
C. Tools
Not applicable L 410.9141-05 Screwdriver Z 37.9119-10 Screwdriver No. 710-5x150 Screwdriver
D. Referenced information
024.00.00.F Periodical
E.
Procedures (1) Connect the external ground power source. (2) The check should be carried out at running engines. Start the both engine according to the Airplane Flight Manual, chapter 4. (3) Dismount the upholstery of the passenger cabin ceiling in space between 9 and 10 frame by screwing 5 locks by L 410.8141-05 screwdriver. (4) During engines running stay in the pilots’ cockpit. The voltage of the starter generators must be 28.5 ± 0.1 V at revolutions of nG = 80 % and at the load of the board network of 30 to 40 A. By means of a potentiometer set the voltage on the A3 (A4) voltage regulator, by means of No. 697-6x210 screwdriver.
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MAINTENANCE MANUAL (5) When the engines are running, switch on the switch GENERATOR L, located in the overhead panel. After the starter-generator had been connected to the board power network, the signaling cell GENERATOR L located on the central warning display shuts off. The switch GENERATOR R is shut off. By means of a digital voltmeter measure the voltage between the clamp GEN of the A 5 differential relay and the frame of the aircraft V 97. The voltage must be 28.5 ± 0.1 V at the revolutions of nG = 80 % and at the board network load 30 to 40 A (according to the speedometer and the voltmeter). (6) Switch on the switch GENERATOR R in the overhead panel. . After the starter-generator had been connected to the board power network, the signaling cell GENERATOR R located on the central warning display shuts off. Shut off the switch GENERATOR L. Carry out the voltage measuring by means of a digital voltmeter the clamp GEN of the A 6 differential relay and the frame of the aircraft V 97. The voltage must be 28.5 ± 0.1 V at the revolutions of nG = 80 % and at the board network load 30 to 40 A (according to the speedometer and the voltmeter). By means of a potentiometer set the voltage on the A 3 (A 4) voltage regulator, by means of No. 697 - 6x210 screwdriver. (7) Stop the both engines according to the Airplane Flight Manual, chapter 4. (8) Switch off all circuit breakers and switches in the overhead panel. (9) Fasten the upholstery on the passenger cabin ceiling by screwing-on 5 locks by L 410.9141-05 screwdriver. (10) Disconnect the external ground power supply.
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7. Check of the operation of all circuit breakers not operating as switches A.
Fixture, Test and Support Equipment
Bulb 28 V / 15 W with conductors and tips Lamp tester
B.
Materials
C. Tools
Not applicable L 410.9141-05 Screwdriver Z 37.9110-10 Screwdriver
D. Referenced information
024.00.00.G Periodical
E.
Procedures (1) Remove the RH cover between the 1 and 2 frame by means of Z 37.9110-10 screwdriver. (2) Within the space of the passenger cabin dismount the upholstered ceiling panels in space between the 7 and 11 frame by L 410.9141-05 screwdriver. (3) Connect the external ground power supply. The following defects are not permitted: When checking a circuit breaker in a circuit, the circuit is disconnected when the circuit breaker has been shut off. When the circuit is not braked (disconnected) replace the circuit breaker. (4) Switch on the switches BATTERY I, II and the circuit breakers WARNING DISPLAY ELECTRO - AIRFRAME, ENGINE LH, ENGINE RH on the overhead panel. When the circuit is not braked (disconnected) replace the circuit breaker. (a) Check of the circuit breaker A 109 (from the 8 to 9 frame on the left). Switch on the switch INVERTER I 36 V on the overhead panel, the inverter LUN 2450 between the 3 and 4 frame will switch on, by switching-off the A 109 circuit breaker the inverter will shut off, by switching on again it switches on again too. The signaling cell INVERTER I 36 V lights according to the situation - whether the inverter is switched off or switched on (it is also possible to check the voltage by the voltmeter on the instrument panel by means of the voltmeter change-over switch on the RH control panel). After having finished the check, shut off the switch INVERTER I 36 V on the overhead panel. (b) Check of the A 110 circuit breaker (the 7 to 8 frame on the right). Switch on the switch INVERTER II 36 V on the overhead panel. The sequence of check is stated in step (4-a). After having finished the check, shut off the switch INVERTER II 36 V. Simultaneously perform the check according to step (4-k). (c) Check of the A 121 circuit breaker (the 8 to 9 frame on the right). The inverter selection switch must be in the AUT position. Switch on the switch INVERTER I 115 V on the overhead panel, LUN 2460 inverter will
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MAINTENANCE MANUAL switch on, by shutting of A 121 circuit breaker the inverter will shut off, by switching on again it switches on again too. The signaling cell INVERTER I 115 V light according to the inverter is switched on or off (it is also possible to check the voltage by the voltmeter on the instrument panel by means of a voltmeter change-over switch on the RH control panel). After having finished the check, shut off the switch INVERTER I 115 V on the overhead panel. (d) Check of the A 122 circuit breaker (the 7 to 8 frame on the right) Switch on the switch INVERTER II 115 V and INVERTER I 115 V on the overhead panel. Signaling cell INVERTER II 115 V will extinguish. Shut off the INVERTER I 115 V again signaling cell INVERTER I 115 V will light on. Switch off the circuit breaker A 122 signaling cell INVERTER II 115 V will switch on. After having finished the check shut off the switch INVERTER II 115 V and switch on the A 122 circuit breaker. Simultaneously perform the check according to step (4-o). (e) Check of the C 17 Circuit breakers (the 8 to 9 frame on the left hand side). C 18 (the 7 and 8 frames on the right hand side). Switch on the change-over switch SEARCHLIGHTS I into the position TAXIING, one searchlight will light on. Turn off the circuit breaker C 17, the searchlight will extinguish, switch on it again and give the change-over switch on the overhead panel to its initial position. Switch on the change-over switch SEARCHLIGHTS II to the position TAXIING two searchlights will light on. Shut off the circuit breaker C18 – the searchlights will extinguish switch on it again. Give the change-over switch on the overhead panel to its initial position. (f)
Check of the M 377 Circuit breaker (the 7 to 8 frame on the right side ). Switch on the circuit breaker WATER INJECTION on the overhead panel. Move the Power Control Levers into the max. power position. Push the button WATER INJECTION - ON the pump in the right gear nacelle starts running ( the contactor M 378 switching on the 10 frame on the right ) - indication by hearing. The water injection circuit will be interrupted by switching off the M 337 circuit breaker. Switch the circuit breaker on again. Push down the WATER INJECTION - OFF button, shut off the WATER INJECTION circuit breaker on the overhead panel. NOTE:
If the water tank is empty, check must be done within 5 seconds.
(g) Check of the M 201, M 202 Circuit Breakers (the1 to 2 frame on the right ). Switch over the change-over switch FIRE-EXTINGUISHING on the test panel of the LH control panel to the position left I. The signal bulb on the test panel will turn on. When the M 201 circuit breaker has been shut off, the signal bulb will turn off. Switch the circuit breaker on again. Set up a change-over switch to the position right I. The signaling bulb on
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MAINTENANCE MANUAL the test panel will light on again. The signaling bulb will light off by the circuit breaker M202 shut off. Switch the circuit breaker on again, set the change-over switch to its zero position. NOTE:
The pyro-cartridges must be stored in the fire extinguishing flasks.
(h) Check of the A 37, A 38 Circuit Breakers (the1 to 2 frame on the right ) Apply a bulb 28V / 15 W to the conductor 175 A from the conductor A 23 (8 and 9 frame on the left) against the frame - the bulb will be lighting. The bulb will turn off by shutting the A 37 circuit breaker off. Switch the circuit breaker on again, apply the bulb to the conductor 253 A from the relay A 31 (the 8 and 9 frame on the left) against the frame - the bulb will be lighting. When the circuit breaker A 38 has been shut off, the bulb will turn off. Switch the circuit breaker on again. (i)
Check of the A 68 Circuit Breakers (the 1 to 2 frame on the right), A 44, A 52 (the 7 to 8 frame on the right). Apply to the conductor 384 A from the contactor A 49 (8 to 9 frame on the right) a bulb against the frame - the bulb will be lighting. Switch off successively the A 68, A 44 and A 52 circuit breakers and switch them on again - the bulb will turn off and will turn on. Let the circuit breakers in the switched on position.
(j)
Check of the Circuit Breaker A 67 (the 1 to 2 frame on the right), A 43, A 55 (the 7 to 8 frame on the right). Apply a bulb to the conductor 380 A from the contactor A 50 (the 8 to 9 frame on the right) against the frame - the bulb will be lighting. Switch off successively the A 67, A 43 and A 55 circuit breakers and switch them on again - the bulb will turn off and will turn on. Let the circuit breakers in the switched on position.
(k) Check of the A 60 circuit breaker (the 7 to 8 frame on the right). The check should be done together with the check according to step (4-b). When the circuit breaker A 60 has been shut off, the inverter 3x36 V stops running. Switch on the circuit breaker again. (l)
Check of the A 58 circuit breaker (the 7 to 8 frame on the right). Apply a bulb to the conductor 245 A from the contactor A 23 (the 8 to 9 frame on the right) against the frame, the bulb will turn on. When the circuit breaker A 58 has been shut off, the bulb will turn off. Switch on the circuit breaker again.
(m) Check of the A 61 circuit breaker (the 7 to 8 frame on the right). Apply a bulb to the conductor 210 A from the contactor A 50 (the 8 to 9 frame on the right) against the frame, the bulb will turn on. When the circuit breaker A 61 has been shut off, the bulb will turn off. Switch on the circuit breaker again.
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MAINTENANCE MANUAL (n) Check of the A 12 circuit breaker (the 7 to 8 frame on the right). Apply a bulb to the conductor 358 A from the conductor A 13 (the 8 to 9 frame on the right) against the frame, the bulb will turn on. When the circuit breaker A 12 has been shut off, the bulb will turn off. Switch on the circuit breaker again. (o) Check of the A 56 circuit breaker (the 7 to 8 frame on the right). The check should be done together with the check according to step (4-d). When the circuit breaker A 56 has been shut off, the inverter 115 V will stop revolving. Switch on the circuit breaker again. (p) Check of the A 57 circuit breaker (the 7 to 8 frame on the right). Apply a bulb to the conductor 214 A from the contactor A 49 (the 8 to 9 frame on the right) against the frame, the bulb will turn on. When the circuit breaker A 57 has been shut off, the bulb will turn off. Switch on the circuit breaker again. (q) Check of the A 59 circuit breaker (the 7 to 8 frame on the right). Apply a bulb to the conductor 246 A from the contactor A 24 (the 8 to 9 frame on the right) against the frame, the bulb will turn on. When the circuit breaker A 59 has been shut off, the bulb will turn off. Switch on the circuit breaker again. (r) Shut off the switches BATTERY I, II and the circuit breakers CENTRAL WARNING DISPLAY - ELECTRO, - AIRFRAME, - ENGINE LH, - ENGINE RH on the overhead panel and check if all checked circuit breakers are in position "switched on". (s) Check of the A 63, A 64 circuit breakers (the 10 to 11 frame). Apply a bulb tester to the circuit breakers A 63 and after to A 64. When the circuit breaker has been shut off, the circuit will be interrupted and the bulb will turn off. Switch on the circuit breakers back again. (5) Install back the covers to the 1 to 2 frame on the right, by means of Z 37.9110-10 screwdriver and the upholstered coverings in the space between the 7 to 11 frame. (6) Disconnect the external ground power supply.
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INTENTIONALLY LEFT BLANK
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AC GENERATION POWER DESCRIPTION AND OPERATION 1. General The aircraft source of alternating power supply are two LUN 2450 static inverters having 3x36 V / 400 Hz, two PC 250 or LUN 2460 static inverters having 115V/400Hz and 26V/400 Hz one of them serving as a stand by, two LUN 2102 or LUN 2101.01 alternators of voltage 3x115/200V, 300 to 507Hz and two SPC-5(C) static inverters 26V AC / 400 Hz (if installed).
2. List of components No.
Name
Type (Drwg. No.)
Qty
Location
1.
Inverter 36V AC/400 Hz
LUN 2450 or LUN 2450-8
2
Between 2 and 4 frame
2.
Switch INVERTER 36 V I
VG-15K-2S
1
Overhead panel
3.
Switch INVERTER 36 V II
VG-15K-2S
1
Overhead panel
4.
Voltmeter
VF 0.4-45
1
Instrument panel
5.
Voltmeter change-over switch of the inverters 36 V
B082070N P4(8)
1
Right control panel
6.
Fuse INVERTER 3x36 V I INVERTER 3x36 V II
2 CSN 354733 F/1500 2 CSN 354733 F/1500
1 1
Left side between 8 and 9 frame Left side between 8 and 9 frame
7.
Fuse APPARATURES
2 CSN 354733 F/1500
2
Left side between 8 and 9 frame
8.
Distribution box
RS-5 (8) B570440N (if installed)
1
RH control panel
RS-5 (8) B574112N (if installed) RS-6 (8) B571176N (if installed) RS-6 (8) B574172N (if installed) 9.
Fuse VOLTMETER-INVERTERS 36 V I VOLTMETER-INVERTERS 36 V II
0.4 CSN 354733 F/1500 0.4 CSN 354733 F/1500
3 3
Fuse panel Fuse panel
10.
Circuit breaker INVERTER 36 V I
AZRGK 40
1
Left side between 8 and 9 frame
11.
Circuit breaker INVERTER 36 V II
AZRGK 40
1
Between 7 and 8 frame on the right side
12.
Contactor
TKD 501 DOD
2
Between 2 and 3 frame
13.
Inverter 115 V AC/400 Hz
PC 250 (if installed) or LUN2460-8 (if installed)
2
Between 2 and 4 frame on the left side
14.
Circuit breaker INVERTER 115 V I
AZRGK 20
1
Left side between 8 and 9 frame
15.
Circuit breaker INVERTER 115 V II
AZRGK 20
1
Right side between 7 and 8 frame
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No. 16.
Name
Qty
Location
Fuse INVERTER 115 V I INVERTER 115 V II
2 CSN 354733 F/1500 2 CSN 354733 F/1500
1 1
Right side between 8 and 9 frame Right side between 8 and 9 frame
17.
Switch INVERTER 115 V I
VG-15K-2S
1
Overhead panel
18.
Switch INVERTER 115 V II
VG-15K-2S
1
Overhead panel
19.
Fuse VOLTMETER I VOLTMETER II
0.4 CSN 354733 F/1500 0.4 CSN 354733 F/1500
1 1
Left side between 3 and 4 frame Left side between 3 and 4 frame
20.
Relay change-over switch
RP 5 (8) B570410N (if installed) B571084N (if installed)
1
Left side between 3 and 4 frame
21.
Voltmeter change-over switch for alternators and circuit breakers
B580338N
1
Right control panel
22.
Voltmeter
VF 0.4-150
1
Instrument panel
23.
Change-over switch INVERTER SELECT 115 V
B082068N
1
Right control panel
24.
Fuse INVERTER 115 V I INVERTER 115 V II
1.6 CSN 354733 F/1500 1.6 CSN 354733 F/1500
1 1
Left side between 3 and 4 frame Left side between 3 and 4 frame
25.
Contactor
TKD 501 DOD
2
In the front of 3 frame
26.
Fuse 26 V / 400 Hz (if installed)
4 CSN 354733 F/1500
2
Between 3 and 4 frame
27.
Relay (if installed)
TKE 52 PODG
1
Between 3 and 4 frame
28.
Alternator
LUN 2102-8 or LUN 2102.01-8
2
Engine nacelle
29.
Regulator
LUN 2147-8 or LUN 2147.01-8 or LUN 2147.02
2
RH side between 16 and 17 frame
30.
Electromagnetic releasing switch ALTERNATOR-RH
V 016 or V 016.01-8
1
Overhead panel
31.
Electromagnetic releasing switch ALTERNATOR-LH
V 016 or V 016.01-8
1
Overhead panel
32.
Distribution box
RS 4 (8) (B570340N)
1
RH side between 15 and 16 frame
33.
Fuse L GEN 200 / 115 V P
6.3 CSN 354733 F/1500
2
Left side between 8 and 9 frame
34.
Signal cell INVERTER I 36 V
1
Signaling panel
35.
Signal cell INVERTER II 36 V
1
Signaling panel
36.
Signal cell INVERTER I 115 V
1
Signaling panel
37.
Signal cell INVERTER II 115 V
1
Signaling panel
38.
Signal cell ALTERNATOR-LEFT
1
Signaling panel
39.
Signal cell ALTERNATOR-RIGHT
1
Signaling panel
40.
Static inverter 26V AC/400Hz (if installed)
SPC-5(C)
2
Between 2 and 3 frame, LH side
41.
Over switch (if installed) INV I / INV I - II / INV II
MS35058-21
1
LH control panel
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Type (Drwg. No.)
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No.
Name
Type (Drwg. No.)
Qty
Location
42.
Circuit breaker (if installed)
KLIXON 7277-2-4
2
4 frame, LH side
43.
Circuit breaker (if installed)
KLIXON 7277-2-1.5
2
Between 2 and 3 frame, LH side
44.
Rectifier (if installed)
B250C1500
2
Between 2 and 3 frame, LH side
45.
Diode block (if installed)
LUN 3312-03
1
Under front baggage compartment
46.
Relay (if installed)
B073576N or B073576N /G
4
Between 2 and 3 frame, LH side
47.
Contactor (if installed)
TKD 501 DOD
2
Before 4 frame, LH side
3. Description NOTE: A.
The electric wiring diagrams are stated in the list of aircraft Wiring Manual.
The supplying of devices from LUN 2450 inverters. At normal state the inverter I supplies the following devices (applies to the aircraft in which the second inverter installed is Model PC 250):
engine devices of the LH engine
fuel gauge LH,
pressure gauge LH,
wing tip tank gauge LH,
gyro compass II,
icing indicator.
Inverter II supplies the following devices:
B.
engine devices of the RH engine,
fuel gauge RH,
pressure gauge RH,
wing tip tank fuel gauge RH,
hydraulic pressure gauge,
turn indicator I.
The supplying of devices from the LUN 2450 inverters. At the normal state the inverter I supplies the following devices (applies to the aircraft in which the second inverter is Model LUN 2460):
engine devices of the LH engine,
fuel gauge LH,
gyro compass II,
turn indicator II,
icing indicator.
Inverter II supplies the following devices:
engine devices of the RH,
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turn indicator I.
C. The supplying of instruments from the PC-250 inverters (if installed). At the normal state the inverter I supplies the following devices:
turn indicators (115 V ),
horizon RH (115 V ),
gyro compass I, II (115 V ),
NAV I (36 V )
ADF I, II (26 V )
weather radar (115 V ) - if installed
vertical gyro (115 V ) - if installed
In case of damage of inverter I these devices are supplied by inverter II. D. The supplying of instruments from the LUN 2460 inverters (if installed). At the normal state the inverter I supplies the following devices:
E.
turn indicators,
horizon RH,
gyro compass I
The supplying of instruments from the LUN 2102 or LUN 2102.2 alternators. At the normal state the windows heating circuit is supplied by the RH engine alternator and the propellers de-icing circuit by the LH engine alternator. In case of damage one of alternators the windows heating and the propellers de-icing circuit are automatically connected to the working alternator.
F.
The supplying of instruments from the SPC-5(C) static inverters 26V AC (if installed). At the normal state the inverter I and II supplies the following devices:
EFI-890R Electronic Flight Information System I, II (if installed),
AHRS I, II Attitude Heading Reference System (if installed),
TCAS (if installed),
FDR (e.g. FA-2200 MADRAS) Flight Data Recorder (if installed)
Weather Radar (e.g. RDR 2000) - (if installed)
EGPWS (if installed)
Flight Data Computer (KCP-220), Air Data Computer (KDC-222), GAD-42 Adapter, AP Relay (SR 263) - if Autopilot system is installed
In case of damage of static inverter I or II, is necessary manually over switched the switch (located on the left control panel) to the Position INV I or INV II. After this the devices are powered from inverter I or II.
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4. Operation A.
LUN 2450 inverters switching on. After the switches BATTERY I, II and the circuit breaker CENTRAL WARNING DISPLAY - ELECTRO are switched on, then, among other, signaling cells INVERTER I 36 V and INVERTER II 36 V on the signal panel are also lighted on. By switching on the switch INVERTER I 36 V at the overhead panel the signal cell INVERTER I 36 V will light off and all electric devices 3x36 V / 400 Hz are supplied by the INVERTER I. By switching on the switch INVERTER II 36 V at the overhead panel the signal cell INVERTER II 36 V on the signal panel will light off and all electric devices connected to the INVERTER II are supplied by voltage of value 3x36 V / 400 Hz from this inverter. In case of damage one of inverters the corresponding cell and appliances on the central warning display lights on and the electric devices are automatically connected to second working inverter. The individual electrical appliances are connected to the inverters voltage through the distributing box RS 5 (RS 6). In the distributing box are mounted circuits for the inverters damage signaling and for automatic change-over switching of electric appliances to the working inverter in case of damage one of them. Check of the individual inverters phases voltage 3x36 V / 400 Hz is provided by means of the change-over switch of the inverters 36 V - voltmeter on the right control panel and by the voltmeter VF 0.4 - 45. NOTE:
There must be switched on circuit breakers INVERTER I, II 36 V between 7 and 8 frame on the left side, to secure the inverters supplying.
B.
PC 250 inverters switching on (if installed) When the switches BATTERY I, II and the circuit breaker CENTRAL WARNING DISPLAY - ELECTRIC are switched on, then among other, signal cells INVERTER I 115 V and INVERTER II 115 V on the central warning display are also lighted on. By switching on the switches INVERTERS I, II 115 V at the overhead panel the signal cells INVERTERS I 115 V and INVERTER II 115 V on the central warning display will light off; the devices are supplied by INVERTER I. Then INVERTER II is shut off and stand-by (out of function). In case of a breakdown of INVERTER I the signal cell INVERTER I 115 V on the signal panel will light on and INVERTER II will be automatically switched on and supplies all electric appliances 115 V / 400 Hz (26 V / 400 Hz). Voltage 115 V / 400 Hz from inverter is supplied to a relay change-over switch B 571 084N with built-in signal circuits serving to breakdown signaling and automatic switch over from one inverter under breakdown to the functioning one. From the relay change-over switch the voltage is supplied through the distribution box to the individual electric appliances. Voltage 26 V / 400 Hz from invertors is supplied to the A 139 relay which is switched over as per operating inverter appliances 26 V / 400 Hz are connected to this relay. The change-over switch INVERTER SELECT 115 V in POSITION AUT. server to select inverters switching on.
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in position AUT - INVERTER I is functional, in case of its breakdown, INVERTER II is made functional and the devices are automatically switched over to INVERTER II. Inverter breakdown is signaled on the central warning display.
in position I
- INVERTER I is functional, in case of its breakdown is signaled on the central warning display.
in position II
- INVERTER II is functional, in case of its breakdown the AC devices are out of function. The breakdown is signaled on the central warning display.
NOTE:
The normal position of the switch is AUT. In case of breakdown in the automatics, the pilot selects another position of the switch after pulling up the fuse.
Voltage checking of inverters 115 V / 400 Hz is performed by means of inverters 115 V and alternators voltmeter switch (on the right control panel) and by the voltmeter VF 0.4 - 150 on the right side of instrument panel. NOTE:
To secure the inverters supplying, there must be switched on the circuit breakers of INVERTER 115 V I, II between the 7 and 8 frame.
C. LUN 2460 inverters switching on (if installed) When the switches BATTERY I, II and the circuit breaker CENTRAL WARNING DISPLAY - ELECTRO are switched on and the engines are running, then, among other, signal cells INVERTER I 115 V and INVERTER II 115 V on the central warning display are also lighted on. By switching on the switches INVERTER I, II 115 V at the overhead panel the signal cells INVERTER I 115 V and INVERTER II 115 V on the central warning display will light off; the devices are supplied by INVERTER I. Then INVERTER II is shut off and stands by (out of function). In case breakdown of INVERTER I the signal cell INVERTER I 115 V on the signal panel will light on and INVERTER II will be automatically switched on and supplies all electric appliances 115 V/400 Hz. Voltage 115 V/ 400 Hz from inverter is supplied to a relay change-over switch RP 5(8), with built-in signal circuits serving to breakdown signaling and automatic switch over from one inverter under breakdown to the functioning one. From the relay change-over switch the voltage is supplied through the distribution box to the individual electric appliances. The change-over switch INVERTER SELECT 115 V in POSITION AUT. serves to select inverters switching on.
in position AUT - INVERTER I is functional, in case of its breakdown, INVERTER II is made functional and the devices are automatically switched over to INVERTER II. Inverter breakdown is signaled on the central warning display.
in position I
- INVERTER I is functional, in case of its breakdown is signaled on the central warning display.
in position II
- INVERTER II is functional, in case of its breakdown the AC devices are out of function. The breakdown is signaled on the central warning display.
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The normal position of the switch is AUT. In case of breakdown in the automatics, the pilot selects another position of the switch after pulling up the fuse.
Voltage checking of inverters 115 V / 400 Hz is performed by means of inverters 115 V and alternators voltmeter switch (on the right control panel) and by the voltmeter VF 0.4 - 150 on the right side of instrument panel. NOTE:
To secure the inverters supplying, there must be switched on the circuit breakers of INVERTER 115 V I, II between the 7 and 8 frame.
D. LUN 2102 or LUN 2102.01 alternators switching on When the switches BATTERY I, II and the circuit breaker CENTRAL WARNING DISPLAY - ELECTRO are switched on and the engines are running, then, among other, signal cells ALTERNATOR - LH and ALTERNATOR - RH on the central warning display are also lighted on. By switching on the switch ALTERNATOR - LH the signal cell ALTERNATOR - LH on the signal panel will light off and the windows heating circuit is supplied by voltage 115 / 200 V. By switching on the switch ALTERNATOR-RH the signal cell ALTERNATOR-RH on the central warning display will light off the propellers de-icing circuit is supplied by voltage 115 / 200 V. The voltage from alternators is supplied to the de-icing systems through the distribution box RS - 4. In the distribution box are mounted the alternators breakdown signaling circuit and the circuit of the automatic switch-over the de-icing system to working alternator. Voltage check of the alternators phases is performed by the voltmeter change-over switch of the alternator and of the inverters 115 V (on the right control panel) and by the voltmeter VF 0.4 - 150 on the right side of instrument panel). E.
SPC-5(C) static inverters 26V AC switching on (if installed) Static inverters 26V AC are switched on by means the switches BATTERY I, II, the circuit breaker CENTRAL WARNING DISPLAY - ELECTRO and INVERTER I, II 36 V. In case of damage one of inverters the corresponding BUS I (II) 26V AC signal cells will be illuminating on the central warning display -electro. When amber BUS I 26V AC signal cell is illuminated (loss of the left PFD power), the INV I / I + II / II switch on the left control panel lift the shelter and switch to INV II position - Both PFD and other powered devices are now powered from BUS II 26 V AC. When amber BUS II 26V AC signal cell is illuminated (loss of the right PFD power), the INV I / I + II / II switch on the left control panel lift the shelter and switch to INV I position - Both PFD and other powered devices are now powered from BUS I 26 V AC.
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FIG. 1
DEVICES OF AC - CURRENT SOURCES ARRANGEMENT (1),(2) LUN 2450 inverter; (3) VF-0.4-45 voltmeter; (4) RS-5 (8) (B 570 440 N) or RS 6 (B 571 176 N) distribution box; (5),(6) TKD 501 DOD contactor; (7),(8) PC-250 inverter or LUN 2460 inverter; (9) RP 5 (8) (B 570 410 N) or B 571 084 N relay change-over switch; (10) VF-0.4-150 voltmeter; (11),(12) TKD 501 DOD contactor; (13) LUN 2102 or LUN 2102.01 alternator; (14),(15) LUN 2147 or LUN 2147.01 regulator; (16) RS-4 (8) (B 570 340 N) distribution box
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FIG. 2
DEVICES OF AC - CURRENT SOURCES ARRANGEMENT (DETAIL A - FROM FIG. 1) Legend for figure – refer to the fig. 1
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FIG. 3
DEVICES OF AC - CURRENT SOURCES ARRANGEMENT (DETAIL B - FROM FIG. 1) Legend for figure – refer to the fig. 1
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FIG. 4
BLOCK DIAGRAM OF SPC-5(C) STATIC INVERTERS 26V AC (IF INSTALLED)
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FIG. 5
BLOCK DIAGRAM OF INVERTERS 36V AC Symbols e.g. A109, A91, A110 etc. - Refer to the Wiring Manual
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AC GENERATION POWER SERVICING 1. Check of the operation of inverters 36 V A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.20.00.A Routine
E.
Procedures (1) Connect the ground power unit. (2) Switch on the switches BATTERY I, II and the circuit breaker CENTRAL WARNING DISPLAY ELECTRO on the overhead panel. (3) Switch on the gradually the switches INVERTERS 36 V AC I, II on the overhead panel. When the inverters are switched on the cells of relevant inverter on the central warning display will turn off. (4) Measure the voltage between individual phases of the inverters I and II. Gradually switch over the selector INVERTERS 36 V to the positions: I
2-3
II
2-3
I
1-3
II
1-3
I
1-2
II
1-2
At the same time check the voltage of the voltmeter located on the right side of the instrument panel. Voltage between individual phases must be 36 V 54.5V V . If values not corresponded with required value, remove the inverter and hand it over to the workshop or replace it. (5) Shut off switches INVERTERS 36 V AC I, II, BATTERY I, II and the circuit breaker, CENTRAL WARNING DISPLAY - ELECTRO. (6) Disconnect the ground power unit.
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2. Check of the operation of inverters 115 V A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.20.00.B Routine
E.
Procedures (1) Connect the ground power unit. (2) Switch on the switches BATTERY I, II and the circuit breakers CENTRAL WARNING DISPLAY - ELECTRO on the overhead panel. (3) Switch on the gradually the switches INVERTERS 115 V AC I, II on the overhead panel. When the inverters are switched on the cell of the relevant inverter on the central warning display will turn off. During this test, the switch INVERTER SELECTION on the right control panel is set up into the position 1 or 2 respectively. Switch on the circuit breakers GYRO COMPASS I and GYRO HORIZONT II. Switch over the voltmeter change-over switch on the switch panel on the right control panel to positions INVERTERS 115 V I, II. At the same time check the voltage of voltmeter on the right side of instrument panel. Voltage of inverters must be 115 V
14 V 15 V
.
If values not corresponded with required value, remove the inverter and hand it over to the workshop or replace it. (4) Switch off the switches INVERTER 115 V AC I, II, BATTERY I, II, GYRO HORIZON II and the circuit breakers CENTRAL WARNING DISPLAY - ELECTRO, GYRO COMPASS I. (5) Disconnect the ground power unit.
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3. Check of the automatic switching of inverters 36 V A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
L 410.9141-05 Screwdriver
D. Referenced information
024.20.00.C Periodical
E.
Procedures (1) Loosen, by means of L 410.9141-05 screwdriver, the panel locks on the passenger cabin ceiling between the 7 and 12 frame and tilt the panels down. (2) Turn on the switches BATTERY I, II, the circuit breaker CENTRAL WARNING DISPLAY ELECTRO, INVERTERS 36 V AC I, II on the overhead panel. The signal cells INVERTER 36 V AC I and II on the central warning display will not illuminated. The red warning flags on the torque (TQ) indicators will go out of view. (3) Shut off the circuit breaker INVERTER 36 V I (A 109) between the 8 and 9 frame on LH side. There will illuminate the signal cell INVERTER 36 V AC I on the central warning display. When the instrument supplied from INVERTER I will not be automatically switched over to INVERTER II, the red warning flags on the torque (TQ) indicators will come into view. (4) Switch on the circuit breaker INVERTER 36 V I (A 109) between the 8 and 9 frame on LH side. The signal cell INVERTER 36 V AC I on the central warning display will not illuminated. (5) Shut off the circuit breaker INVERTER 36 V II (A 110) between the 7 and 8 frame on the RH side. The signal cell INVERTER 36 V AC II on the central warning display will illuminate. If the instruments supplied from INVERTER II will not be automatically switched over to INVERTER I, the red warning flags on the torque (TQ) indicators will come into view. (6) Switch on the circuit breaker INVERTER 36 V AC II (A 110) between the 7 and 8 frame on the RH side. The signal cell INVERTER 36 V AC II on the central warning display will not illuminated. (7) Switch off all the switched circuit breakers and switches on the overhead panel. (8) Tilt up the upholstered overhead panels between the 7 and 8 frame and secure the locks by means of L 410.9145-05 screwdriver.
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4. Check of the inverters 115 V automatic switching-over A.
Fixture, Test and Support Equipment
Optionally: Multimeter 2 pcs (e.g. EXTECH MG 302)
B.
Materials
C. Tools
Not applicable L 410.9141-05 Screwdriver; Necessary tools from tool kit
D. Referenced information
024.20.00.D Periodical
E.
Procedures (1) Loosen, by means of L 410.9141-05 screwdriver, the panel locks on the passengers cabin ceiling between the 7 to 12 frame and tilt it down. *) Optionally (if the A037 Radio altimeter is not installed): Tilt the instrument panel for entrance assurance to the V274 terminal board (refer to the Wiring Manual) and connect the multimeter#1 between pin No. 1 and ground; and multimeter#2 between pin No. 4 and ground (2) Switch on the switches BATTERY I, II, INVERTERS 115 V AC I, II and the circuit breaker CENTRAL WARNING DISPLAY - ELECTRO on the overhead panel. (3) Set the change-over switch INVERTERS 115 V SELECTION on the right hand control panel to the position AUT. In this position the INVERTER I 115 V is switched on and the cell INVERTER I 115 V AC as well as the cell INVERTER II 115 V AC on the signal panel do not light. Switch on the circuit breaker RADIO ALTIMETER on the overhead panel and check the radio-altimeter warning flag shifting in. (4) The assistant will shut off the circuit breaker INVERTER I 115 V AC between the 8 to 9 frame on the left. The cell INVERTER I 115 V AC on the central warning display will turn on and INVERTER II 115 V AC will be automatically switched on. The warning flag on the radio-altimeter must not be shifted out. *) Optionally (if the A037 Radio altimeter is not installed): System voltage drop measured with use the multimeter#1 and multimeter#2 (connected as described in step 1) is not permitted (5) Shut off the circuit breaker, RADIO ALTIMETER, the switched INVERTERS 115 V AC I, II and BATTERY I, II on the overhead panel. The assistant will switch on the circuit breaker INVERTER I 115 V AC between 8 and 9 frame on the left. (6) Tilt up the ceiling upholstery panels between the 7 and 12 frame and secure the locks by means of L 410.9141-05 screwdriver.
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5. Check of the over-switching of the inverters 26 V (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.20.00.E Periodical
E.
Procedures (1) Switch on the EFI-890R System (if installed) and all other EFIS information source (attitude, course): Switch on the switches/circuit breakers BATTERY I, II, CENTRAL WARNING DISPLAY ELECTRO, INVERTERS 36 V AC I, II, PFD I, II, DCP I, II, CHP, DCU, AHRS I, II, AP (if installed) on the overhead panel. (2) Inverters 26V AC over-switch - refer to the fig. 301 - is in middle position (INV I-II). Switch off the INVERTER 36V I circuit breaker on the overhead panel. Copilot's Primary Flight Display (PFD II), AHRS II and AUTOPILOT (if is AP TRANSFER switch/annunciator in RT position) must be in operation. Repeated for the INVERTER II: Switch off the INVERTER 36V II circuit breaker on the overhead panel. Pilot's Primary Flight Display (PFD I), AHRS I and AUTOPILOT (if is AP TRANSFER switch/annunciator in LT position) must be in operation.
FIG. 301
INVERTERS 26 V AC OVER-SWITCH (LOCATED ON THE LEFT CONTROL PANEL) (3) Switch the Inverters 26V AC over-switch to the position (INV I). Switch off the INVERTER 36V II circuit breaker on the overhead panel. Primary Flight Displays (PFD I, II), AHRS I, II and AUTOPILOT must be in operation. Repeated for the INVERTER I: Switch off the INVERTER 36V I circuit breaker on the overhead panel. Primary Flight Displays (PFD I, II), AHRS I, II and AUTOPILOT must be shut down.
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(4) Switch the Inverters 26V AC over-switch to the position (INV II). Switch off the INVERTER 36V I circuit breaker on the overhead panel. Primary Flight Displays (PFD I, II), AHRS I, II and AUTOPILOT must be in operation. Repeated for the INVERTER II: Switch off the INVERTER 36V II circuit breaker on the overhead panel. Primary Flight Displays (PFD I, II), AHRS I, II and AUTOPILOT must be shut down. (5) Switch off all the switched circuit breakers and switches on the overhead panel.
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LUN 2450 OR LUN 2450-8 THREE-PHASE INVERTER DESCRIPTION AND OPERATION 1. Purpose The LUN 2450 or LUN 2450-8 static three-phase inverter is determined to invert direct current voltage 27 V to AC three phase voltage 3x36 V / 400 Hz.
2. Technical data Nominal supply voltage
27 V
Nominal current
29 A
Nominal line output voltage
3x36 V
Nominal output frequency
400 Hz
Nominal power
500 VA
3. Operation The inverter is composed of two units working like a power pulse static inverters with bridge connection, current feedback and balancing diodes. Output voltages magnitude is regulated by the pulse width modulation. Sine wave is obtained by means of output resonant filters. The three phase system of line output voltages is obtained from the Scott connection of output transformed in both inverter power units. To achieve the required parameters of line output voltage, there is used a comparative circuit shifting the starting pulses of second unit. There is mounted the failure signalling circuit in the inverter. When failure occurs this circuit gives the signal to switching over to the stand-by inverter. NOTE:
LED diode on the inverter is determined to inverter function check in the production factory.
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LUN 2450 OR LUN 2450-8 THREE-PHASE INVERTER REMOVAL / INSTALLATION 1. Removal and installation of LUN 2450 or LUN 2450-8 three-phase inverter A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
0.5 mm Binding wire
C. Tools
Z 37.9110-10 Screwdriver No. 697 - 6x120 Screwdriver 8 CSN 230651.7 Barrel spanner 8 CSN 230659.7 Handle CSN 230332 Combination pliers
D. Referenced information E.
-
Procedures (1) By means of Z 37.9110-10 screwdriver loosen the screws, remove the cover between the 2 and 4 frame on the left hand side. (2) By means of No. 697 - 6x120 screwdriver loosen 4 M4 screws fixing the thermoregulators panel. (3) By means 8 CSN 230651.7 barrel spanner and the 8 CSN 230659.7 handle, loosen 4 screws fixing 7 diode block and 4 screws fixing the SS-3 signaling box. (4) Inverters removal (a) Unlock and unscrew the plug-and-socket connections. (b) By means of 8 CSN 230651.7 barrel spanner and the 8 CSN 230 659.7 handle loosen 4 screws M5 fixing the inverters and remove it. (5) Inverters installation (a) Set the inverter into the frame and by means of 8 CSN 230651.7 barrel spanner with the 8 CSN 230659.7 handle screw on 4 screws M5 fixing the inverter. (b) Connect the plug-and-socket connections and secure them by means of a binding wire 0.5 mm. (6) Set on the thermoregulator panel and by means of No. 697 - 6x120 screwdriver screws on 4 fixing screws. (7) By means of 8 CSN 230651.7 barrel spanner with the 8 CSN 230659.7 handle screw on the fixing screws of the diode blocks and the SS-3 signaling box. (8) By means of Z 37.9110-10 screwdriver mount on the cover between the 2 and 4 frame on the left.
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LUN 2460 INVERTER DESCRIPTION AND OPERATION 1. Purpose The LUN 2460 static inverter is determined to invert direct current voltage 27 V to alternating current voltage 115V/400Hz.
2. Technical data Nominal supply voltage
27 V
Nominal current
28 A
Nominal output voltage
115 V
Nominal output frequency
400 Hz
Nominal power
500 VA
3. Operation The inverter power unit works on the principle of pulse static inverter with bridge connection, current feed back and balancing diodes. Output voltages magnitude is regulated by the pulse width modulation. Sine wave is obtained by means of output resonant filters. Signaling circuit mounted on the inverter gives the signal to switching over the standby inverter and signals the short-circuit mode on the independent output.
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LUN 2460 INVERTER REMOVAL / INSTALLATION 1. Removal and installation of LUN 2460 inverter A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
∅ 0.5 mm Binding wire
C. Tools
Z 37.9110-10 Screwdriver 8 CSN 230651.7 Barrel spanner 8 CSN 230659.7 Handle 10 CSN 230651.7 Barrel spanner 10 CSN 230659.7 Handle CSN 230382 Combination pliers
D. Referenced information E.
-
Procedures (1) By means of Z 37.9110-10 screwdriver loosen the cover between the 2 and 4 frame (2) By means of 8 CSN 230651.7 barrel spanner and the 8 CSN 230659.7 handle screw off 4 screws M5 fixing 7 diode blocks and dismount them. (3) Inverters removal (a) By means of 10 CSN 230651.7 barrel spanner and the handle 10 CSN 230659.7 screw off 4 screws M6 from the inverter suspensions. (b) Unlock and disconnect the plug-and-socket connections and remove the inverters. (5) Inverters installation (a) Set on the inverters and by means of 10 CSN 230651.7 barrel spanner and the 8 CSN 230659.7 handle screw on them to the suspension. (b) Connect the plug-and-socket connections and secure them by means of a binding wire ∅ 0.5 mm. (6) By means of 8 CSN 230651.7 barrel spanner and the 8 CSN 230659.7 handle screw on the diode blocks to their suspensions. (7) By means of Z 37.9110-10 screwdriver mount on the cover between the 2 and 4 frame on the left.
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LUN 2102-8 OR LUN 2102.01-8 ALTERNATOR DESCRIPTION AND OPERATION 1. Purpose In connection with LUN 2147-8 or LUN 2147.01-8 or LUN 2147.02 regulator the LUN 2102-8 or LUN 2102.01-8 alternator supplies the aircraft deicing systems.
2. Technical data Nominal voltage
115 / 200 V AC
Nominal power
3 kVA at all temperature range of cooling air 3.7 kVA at temperature lower then 10°C
Operational revs. range
6000 to 10150 RPM
Output frequency range
300 to 507 Hz
Short-time overload
4.5 kVA for period of 5 min 6 kVA for period of 5 sec
3. Operation Alternator is designed as a non-brushing two - stage cascade of main alternator and of AC exciter with rotating rectifier. Commonly with built in deferential protection current transformer the alternator creates one assembling unit. LUN 2102-8 or LUN 2102.01-8 alternator in the LUN 2147-8 or LUN 2147.01-8 or LUN 2147.02 regulator assembly, including transformer M 160 and protection power elements, secures:
constant AC voltage lever 115 / 200 V in full range overload, revolutions and ambient temperature at admissible tolerance
limited overload in operation on the ground with self-cooling
nominal overload with combined cooling in operation during the flight
reliable alternator exciting without battery connection at revolutions n = 6000 RPM
protection against dangerous overvoltage
protection against phase voltage unbalance
connection and disconnection from the network in dependence on alternator voltage
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LUN 2102-8 OR LUN 2102.01-8 ALTERNATOR SERVICING 1. Check of the fixing and measure the insulation resistances of the LUN 2102-8 or the LUN 2102.01-8 alternator A.
Fixture, Test and Support Equipment
Insulation tester (e.g. EXTECH 380366 or MG 302)
B.
Materials
0.8 mm Binding wire
C. Tools
Torque wrench Combination pliers (e.g. CSN 230382)
D. Referenced information
024.20.04.A Periodical
E.
Procedures (1) Attach steps (e.g. B097300N) to the engine nacelle. (2) Release the tiltable cover locks of engine nacelle and tilt down the cover. (3) Check of alternator attachment on the drive unit. (4) Inspect of fastening the cooling air intake piping. (5) Alternator insulation resistance check. Insulation resistance must not be lower then 20 MΩ (Mega Ohms) at the 1000 V. (6) Inspect whether alternator is not mechanically damaged, screws are sufficiently tightened and securing pads and wires are intacted. (7) By means of torque wrench, check tightening of the nut on the quick-closing clamp, fastening the alternator to the drive unit. The nut on a clamp must be tightened by tightening moment of 2 Nm. (8) Check the fastening of cooling air intake piping to the alternator inlet branch. (9) Disconnect P - S connecting and measure the insulation resistances
to measure the operation winding insulation resistance, connect the measuring apparatus between the clip No. 3 and the frame
to measure the exciting winding insulation resistance connect the measuring apparatus between the clip No. 6 and a frame.
In both cases the insulation resistance must correspond to the value stated in step (5). (10) Connect the P - S connections and secure them by a binding wire. (11) Set up the tiltable cover of the engine nacelle into its position and fasten it by locks. (12) Clear away steps. EFFECTIVITY ALL
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2. Check of the LUN 2102-8 or LUN 2102.01-8 alternator A.
Fixture, Test and Support Equipment
Compressed air source
B.
Materials
Not applicable
C. Tools
8 CSN 230626 Open-single-ended wrench No. 697 - 6x120 Screwdriver 300 CSN 230110 Hammer or woody mallet
D. Referenced information
024.20.04.B Periodical
E.
Procedures (1) Inspect the securing of torsional rod securing, the stator and rotor. Grip a free rod end and alternatively by tension and thrust in axial direction at force approximately 20 N, check the right securing of torsional rod in the shaft cavity.
FIG. 301
LUN 2102-8 OR LUN 2102.01-8 ALTERNATOR (1) Torsional rod; (2) Shield; (3) Flange; (4) Screw; (5) Locking washer; (6) Spring shim block; (7) Bearing; (8) Rotating rectifier; (9) Main alternator exciting winding; (10) AC exciter winding
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(2) Check the stator and the rotor according following steps: (a) Release the lock washers (5) of screws (6), loosen the screws by a stated wrench and dismount a shield by light beating to shield (3) through the wooden plate. CAUTION:
PERFORM THE BEATING ALTERNATIVELY ALONG THE FLANGE CIRCUMFERENCE, TO PREVENT SHIELD STICKING.
After shield removal take off a rotor and a spring shim block (6). (b) By compressed air clean out rotor and stator from impurities. (c) Inspect and check the state of bearing. Bearings (7) must not be mechanically damaged and there must not be any traces of grease leakage. Exchange the bearings if they are damaged. (d) Inspect the intactness of outlets connection of rotating rectifier (8) individual elements. (e) Check if the winded rotor bundles of the main alternator exciting winding (9) and at AC exciter winding (10), the slot wedges do not protrude and if the windings front bandage of both rotor bundles are not damaged. (f)
Set up the rotor to its original position and slip on the spring shim block. Mount on the shield with keeping conditions stated in para.2 subpara.(a), tighten the screws and secure the lock washers.
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LUN 2102-8 OR LUN 2102.01-8 ALTERNATOR REMOVAL / INSTALLATION 1. Removal/installation of the LUN 2102-8 or LUN 2102.01-8 alternator A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
0.8 mm Binding wire
C. Tools
Z 37.9110-10 Screwdriver No. 697 - 6x150 Screwdriver 5.5x7 CSN 230611.6 Open-double-ended wrench 8 CSN 230626.6 9 CSN 230626.6 17 CSN 230626.6 22 CSN 230626.6 Open-double-ended wrench Type 321 / 160 Flat pliers No. 3013 Lateral nippers TMK 05 (set) Torque wrench
D. Referenced information
024.20.04.C Periodical
E.
Procedures (1) Attach the B 097 300 N steps to the engine nacelles. (2) Open the tiltable cover of the engine nacelle according to work procedure stated in chapter 054. (3) Dismount the lower cover by No. 697 - 6x120 screwdriver. (4) Dismount the inside lateral cover by Z 37.9110-10 screwdriver. (5) All circuit breakers and switches must be switched off before beginning of work. (6) LUN 2102 alternator removal (a) Unlock and disconnect a distributing piping of the fireproof system (2 pcs) by a wrench 22 and17. (b) Disconnect the collector of a fireproof system on the LH and RH engine strut by means of a wrench 22. (c) Release the lock of starter-generator sleeve by No.9 wrench and by No. 697- 6x150 screwdriver.
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MAINTENANCE MANUAL (d) Unlock and disconnect the hose to oil pressure transmitter on the fireproof wall by No. 17 wrench. (e) Loosen 2 screws on the oil cooler bracket by No. 697 – 6x150screwdriver and by No. 17 wrench. (f) Unlock and unscrew P - S connections of the alternator. (g) Release the sleeve fixing the alternator by means No. 8 wrench. (h) Take out the alternator with help of an assistant which holds the alternator (blind the hole). (7) LUN 2102 alternator installation (a) Release the coupling fixing the sleeves of starter-generator air inlet by No. 9 wrench and mount on the air inlet branch between the strut of engine bed and the alternator. (b) Release the coupling of the sleeve for the alternator fastening and open the sleeve. (c) Grease lightly the alternator shaft by CIATIM 201 and insert it into a gearing with help of an assistant and push it to the flange. Set up the alternator so that the clearance between the branch of alternator cooling and the upper strut of oil cooler would be 15 mm. Fasten the sleeve and tighten it by a moment Mk = 2 Nm by means of a torque wrench. Connect and secure it by a P - S connection. (d) Set-up the starter-generator inlet so that the clearance between a starter-generator inlet and an alternator would be from 2 to 3 mm. Tighten the sleeve fixing a starter-generator air inlet by a prescribed moment Mk = 2 Nm. (e) Set-up the distributing piping of the fireproof system between the fireproof wall of the front and rear air frame by No. 19 and 22 wrench. (f)
Set-up the air distribution of alternator and starter-generator cooling. Tighten the locks fixing a sleeve by No. 8 wrench.
(g) Connect the fireproof system collector in the back engine part by a No. 22 wrench and fasten it by screws M 4x12 in sleeves at the LH and RH engine strut by means of a screwdriver No. 697 – 6x150. (h) Set-up oil cooler and alternator cooling brackets and tighten the screws M 4x12 by means of No. 697 - 6x150 screwdriver and by No. 7 wrench. (i)
Set-up and fasten by No. 14, 17, 22 wrench the distributing piping alternator extinguishing system and the distributing piping of the fireproof system between the front fireproof wall and rear air frame and secure them.
(8) Fasten the inside lateral cover by Z 37.9110-10 screwdriver and the lower cover by No. 697 - 6x150 screwdriver. Close the lower tiltable cover according to the work procedure stated in chapter 054. EFFECTIVITY ALL
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LUN 2147-8 OR LUN 2147.01-8 OR LUN 2147.02 REGULATOR DESCRIPTION AND OPERATION 1. Purpose LUN 2147-8 or LUN 2147.01-8 or LUN 2147.02 regulator is generator (alternator) control unit determined for the LUN 2102-8 or LUN 2102.01-8 alternator supply exciting and protection. Regulator holds its input voltage of 115 to 119 V in whole range of load, operating revolutions and temperature on the ground and during the flight. NOTE:
LUN 2147.02 regulator is replacement for the LUN 2147.01-8 regulator.
2. Technical data A.
B.
Basic data •
Input voltage
3x115 V AC, 28 V DC
•
Output exciting voltage lower then
28 V
•
Output exciting current lower then
3A
Overvoltage protection values: The protection must not switch off up to voltage of 128 V. Protection must switch off in the output voltage range of 128 to 134 V in 2 to 5 sec.
C. Protection values against the overload: In case of alternator overloading the protection must secure its field suppression. The protection must be disconnected with time lag of 5 to 7 sec if increase of alternator current is higher then 17.5 to 20 A in the arbitrary phase. D. Short circuit protection values: Protection must secure a field suppression of alternator to 0.6 sec in case of output voltage loss is lower then 95 to 105 V and handing of cut-off pulse over when the output voltage value exceed at the same time 17.5 to 20 A. Protection must at the same time prevent excitation in case of null alternator revolutions. E.
Circuit values of control voltage contactor: The circuit must secure connection of alternator output to a bus bar if its output voltage exceeds 112 to 115 V and its disconnection from a bus bar in case the voltage is lower then 110 to 107 V. Alternator switching on and switching off is realized with the delay approx. 1 sec.
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MAINTENANCE MANUAL 3. Operation Regulator consists of regulation part, overvoltage and differential current protection circuits and circuit of voltage controlled contractor. Regulator operates in the pulse mode. Regulator output voltage is of square wave.
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MAINTENANCE MANUAL RS 5 (8) (A 100) DISTRIBUTION BOX (if installed) RS 6 (8) (A 100) DISTRIBUTION BOX (if installed) DESCRIPTION AND OPERATION 1. Purpose RS 6 (8) and RS 5 (8) distribution boxes are a part of supply system a three-phase alternating current 36 V / 400 Hz and a single phase alternating current There are these types of the distribution boxes used on particular aircrafts: RS 6 (8) (Drwg. No. B571176N) distribution box - fuses are installed RS 6 (8) (Drwg. No. B574172N) distribution box - KLIXON circuit breakers are installed RS 5 (8) (Drwg. No. B570440N ) distribution box – fuses are installed, used on L 410 UVP-E. RS 5 (8) (Drwg. No. B574112N) distribution box – KLIXON circuit breakers are installed. NOTE:
Using of the distribution box RS 5 (8) or RS 6 (8) is depend on installing of the inverter PC 250 or LUN 2460 in the aircraft.
2. Technical data Nominal switched and supply voltage: •
DC
27 V
•
AC
3x36 V / 400 Hz 1x115 V / 400 Hz
Operating supply voltage: •
DC
24 to 29.4 V
•
AC - phase
115 to 119 V
3. Operation The distribution box is plug in the circuit three phase alternating current 36 V / 400 Hz and of single phase alternating current 115 V / 400 Hz inverters and ensures: •
switching over of 3x36 V AC inverter I, II bus bars to that if the inverter I (II) fails, the load from its bus bar connected to the bus bar of the operating inverter
•
transformation of 36 V AC voltage to 113 V AC required to feeding the attitude gyroscope
•
protection of bus bars
•
supply and protection of electrical appliances
NOTE:
Refer to the schematic on Fig. 1 and 2 for the operation of distribution boxes.
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FIG. 1
RS 5 (8) (Drwg. No. B570440N) DISTRIBUTION BOX WIRING DIAGRAM PS1 - PS3 printed wiring B 570 420 N; RE1, RE2 Contactor TKD 133 DOD; RE3 relay TKE 54 PODG; RE4, RE5 relay TKE 52 PODG; RE6, RE7 TKD 103 DOD; P06 - P029 fuse CSN 354733F/1500; TR transformer
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FIG. 2
RS 6 (8) (Drwg. No. B571176N) DISTRIBUTION BOX WIRING DIAGRAM PS1 - PS3 printed wiring B 570 420 N; RE1, RE2 Contactor TKD 133 DOD; RE3 relay TKE 54 PODG; RE4, RE5 relay TKE 52 PODG; RE6, RE7 TKD 103 DOD; P06 - P029 fuse CSN 354733F/1500; TR transformer
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FIG. 3
RS 5 (8) (Drwg. No. B 574 112 N) DISTRIBUTION BOX WIRING DIAGRAM PS1 - PS3 printed wiring B 570 420 N; RE1, RE2 contactor TKD 133ODL; RE3 relay TKE 54 PODG; RE4, RE5 relay TKE 52 PODG; RE6, RE7 contactor TKD 103 ODL; P06 - P029 circuit breaker; TR1 transformer B 570 430N; SV1 – SV3 distribution frame 75 K 8; A 100 – 1 plug 2RM42B30S2V1; A 100 – 2 plug 2RM39B45S2V1; V ground.
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FIG. 4
RS 6 (8) (Drwg. No. B 574 172N) DISTRIBUTION BOX WIRING DIAGRAM PS1 - PS3 printed wiring B 570 420 N; RE1, RE2 contactor TKD 133 ODL;RE3 relay TKE 54 PODG; RE4, RE5 relay TKE 52 PODG; RE6, RE7 contactor TKD 103 ODL;P06 - P029 circuit breaker; TR transformer B 570 430N; SV1 – SV3 distribution frame 75 K 8; ; A 100 – 1 plug 2RM42B30S2V1, A 100 – 2 plug 2RM39B45S2V1; V ground
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FIG. 5
THE FUSES (OR CIRCUIT BREAKERS) ARRANGEMENT ON THE RS 5 (8), RS 6 (8) DISTRIBUTION BOX NOTE:
The fuse (or circuit breaker) values and the text of the label differ according to the equipment of a particular aircraft version a label on the distribution box shows the system protected and the value of the fuse or circuit breaker.
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RS 4 (A 257) DISTRIBUTION BOX DESCRIPTION AND OPERATION 1. Purpose RS 4 distribution box provides for distribution of electrical energy from sources to the system of windshield electrical heating, propeller de-icing, instrument lighting, regulators and voltmeters. It performs namely:
connection of energy consumers via the CS1 and CS2 bus bars to sources of electric energy
switching over of the bus bar of Alternator#1 to the bus bar of Alternator#2 and vice versa upon failure of one of alternators
disconnection of short-circuited bus bar
protection of energy consumers connected to the three-phase bus bars
There are these types of the distribution boxes used on particular aircraft: RS 4 (Drwg. No. B570340N) distribution box - fuses are installed RS 4 (Drwg. No. B574140N) distribution box - KLIXON circuit breakers are installed
2. Technical data Nominal supply voltage
27 V
Nominal switched voltage
115 / 200 V / 400 Hz
Nominal switched output power
3.7 kVA
3. Operation Refer to the schematic on Figs. 1 and/or 2 for the operation of distribution box.
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FIG. 1
RS 4 (Drwg. No. B570340N) DISTRIBUTION BOX WIRING DIAGRAM ST1, ST2 contactor TKD 133 DOD; ST3, ST4 contactor TKD 103 DOD; PO1 to PO18 fuse CSN 354733F/1500; D1 to D4 diode KZL 81/40
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FIG. 2
RS 4 (Drwg. No. B574140N) DISTRIBUTION BOX WIRING DIAGRAM ST1, ST2 contactor TKD133ODL; ST3, ST4 contactor TKD103ODL; PO1 to PO18 circuit breakers KLIXON 7277-2-XX; D1 to D4 diode 1N4007
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FIG. 3
FUSES (OR CIRCUIT BREAKERS) ARRANGEMENT IN RS 4 DISTRIBUTION BOX NOTE:
The fuse (or circuit breakers) values and the text the label differ according to the equipment of a particular aircraft version. A label on the distribution box shows the system protected and the value of the fuse or circuit breaker.
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MAINTENANCE MANUAL RP 5 (8) (A 131) RELAY SWITCH (if installed) B 571 084 N RELAY SWITCH (if installed) DESCRIPTION AND OPERATION 1. Purpose RP 5 (8) (Drwg. No.B 570 410 N) relay switch, B 571 084 N relay switch is determined for automatic switching-on the stand-by inverter 115 V / 400 Hz in case of defect on main inverter 115 V / 400 Hz. NOTE:
Using of the relay switch RP 5 (8) or B 571 084 N is depend on installing of the inverter PC 250 or LUN 2460 in the aircraft.
2. Technical data Nominal switched and supply voltage: •
DC
27 V
•
AC
115 V / 400 Hz
Operating supply voltage: •
DC
24 to 29.4 V
•
AC
115 to 119 V
3. Operation Refer to the schematic on Fig. 1 and 2 for the operation of relay switches.
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FIG. 1
RELAY SWITCH RP 5 (8) WIRING DIAGRAM RE 1, RE 2 relay 15N 599 19.7; RE 3 relay B 573 245 N; RE 4 relay TKE 54 PODG; R1, R2 resistor TR 510, 2k7/3; C1, C2 capacitor TE 156-10M/50; D1-D8 diode KY 130/600; D9 diode KZL 81/40; D10 diode KY 132/1000; PO 1, PO 2 fuse CSN 354733F/1500
FIG. 2
RELAY SWITCH B571384N RE 1, RE 2 relay 15N 399 197; RE 3 relay B 573 245 N; RE 4 relay TKE 54 PODG; D1, D2 diode; D9 diode KZL 81/40; D10 diode KY 132/1000; PO 1, PO 2 fuse CSN 354733F/1500
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TKD 303 DOD, TKD 133 DOD CONTACTOR DESCRIPTION AND OPERATION 1. Purpose Contactors TKD 103 DOD a TKD 133 DOD are determined for remote switching of three phases of electric devices in aerospace technology.
2. Technical data Switched voltage •
AC
20 to 220 V
•
DC
5 to 30 V
Switched current
0.2 to 10 A
Switching nominal voltage
27 V
Retaining current TKD 103 DOD
0.33 A
TKD 133 DOD
0.42 A
3. Operation When voltage is supplied to clamps A - B, the contactor will connect its contact (switch over). If the voltage is disconnected the contactor returns back to the idle position by means of a spring.
TKD 103 DOD
FIG. 1
TKD 103 DOD, TKD 133 DOD CONTACTOR WIRING DIAGRAM
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TKD 133 DOD
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TKD 501 DOD CONTACTOR DESCRIPTION AND OPERATION 1. Purpose Contactor TKD 501 DOD is determined for remote switching of electric devices in aerospace technology.
2. Technical data Switched nominal voltage
27 V
Switched nominal current
50 A
Switching nominal voltage
27 V
Switching current
0.33 A
3. Operation When voltage is supplied to clamps A - B contactor connects the clips S1 - S2. After voltage disconnecting the contactor spring disconnects the clips S1 - S2.
FIG. 1
TKD 501 DOD CONTACTOR WIRING DIAGRAM
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TKE 52 PODG, TKE 54 PODG RELAY DESCRIPTION AND OPERATION 1. Purpose Hermetically sealed TKE 52 PODG and TKE 54 PODG relay serves to interconnecting of direct current circuits in electric powered systems of aerospace technology.
2. Technical data Switched nominal voltage
27 V
Switched nominal current
5A
Nominal switching voltage
27 V
Switching current TKE 52 PODG
0.17 A
TKE 54 PODG
0.21 A
3. Operation When voltage is supplied to the contacts A - B, a current passing through the relay coil creates the electromagnetic field, which will draw the relay anchor and thereby the relay contacts will switch over. When voltage is disconnected the spring will return the relay anchor and thereby contacts to the idle position.
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FIG. 1
TKE 52 PODG RELAY WIRING DIAGRAM
FIG. 2
TKE 54 PODG RELAY WIRING DIAGRAM
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15N 599 19.7 RELAY DESCRIPTION AND OPERATION 1. Purpose 15N 599 19.7 low-frequency relay is determined mostly to be used in printed wirings for low current circuits. It consists from two electromagnetically controlled switch-over bunches located in the metal hermetically sealed box with 8 tap points in glass melting.
2. Technical data Switched maximum voltage
125 V
Switched maximum current (power)
1 A (15 W)
Switching nominal voltage
27 V
Switching current
14 ± 2 mA
3. Operation When voltage is supplied to relay coil the contacts will be switched over. After disconnection of voltage relay returns by action of a spring to the idle position.
FIG. 1
15N 599 19.7 RELAY WIRING DIAGRAM
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B073576N OR B073576N /G RELAY DESCRIPTION AND OPERATION 1. Purpose B073576N and/or B073576N /G relay is determined for interconnecting the circuits in the aircraft electric systems. The B073576N consists from 15N 599 19.7 relay soldered to the printed wiring and cast in sealing compound. The B073576N /G consists from MIL-R-39016/6 relay soldered to the printed wiring and cast in sealing compound.
2. Technical data Voltage range: •
Nominal
28V DC
•
Emergency
18V DC
•
Operational (Normal)
22 ÷ 33.3V DC
•
Abnormal
20.5 ÷ 32.2V DC
Max. loading of contacts •
Ohmic loading
2A at 28V DC 0.3A at 115V AC / 400Hz
•
Inductive loading (200mH)
Consumption current (valid for switch ON of contacts K1 to K6)
0.75A at 28V DC 25 mA
3. Operation When voltage is supplied to relay coil the contacts will be switched over. After disconnection of voltage the relay returns by action of a spring to idle position.
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FIG. 1
B073576N /G RELAY
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B 073 245 N RELAY DESCRIPTION AND OPERATION 1. Purpose Relay B 073 245 N is determined for interconnecting the circuits in the aircraft electric systems. It consists from 15N 599 19.7 relay soldered to the printed wiring and cast in sealing compound.
2. Technical data Switched maximum voltage
125 V
Switched maximum current (power)
1 A (15 W)
Switching nominal voltage
27 V
Switching current
14 ± 2 mA
3. Operation When voltage is supplied to relay coil the contacts will be switched over. After disconnection of voltage the relay returns by action of a spring to the idle position.
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VF 0.4 - 45, VF 0.4 - 150 VOLTMETER DESCRIPTION AND OPERATION 1. Purpose Airborne ferrodynamic voltmeters VF 0.4 - 45 and VF 0.4 - 150 are determined for measuring the voltage in the alternate current networks of 36 V and 115 V.
2. Technical data VF 0.4 - 45
VF 0.4 - 150
Measuring range
0 - 45 V
0 - 150 V
Value of one scale division
1.0 V
5.0 V
Working part of scale
18 - 45 V
60 - 150 V
Nominal frequency Operating frequency range
400 Hz 350 - 900 Hz
Inaccuracy of voltmeters of the upper value of metering NOTE:
±2%
Voltmeter VF 0.4 - 150 is determined for measuring the voltage of alternators (inverters 115 V I, II - in dependence on installation of the change over switch on the right control panel). Lower frequency of alternators, which is under voltmeter frequency bound has not influence upon an accuracy of voltage measuring and it is limited on time of engine function during its idle run (ng = 60 - 65 %). When revolutions of gas turbine engine will increase to 67 %, then alternator frequency complies to low voltmeter frequency and since the standardized accuracy of voltage measuring is secured, and that is fully sufficient in aircrafts operation.
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VF 0.4 - 45, VF 0.4 - 150 VOLTMETER FAULT ISOLATION No. 1.
Trouble When connecting the voltmeter to network, the pointer does not move
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Possible causes
Correction
a) no voltage in network
a) switch on power
b) supply conductors interrupted
b) renew the electric circuit of voltmeter supply conductors
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VF 0.4 - 45, VF 0.4 - 150 VOLTMETER REMOVAL / INSTALLATION 1. Installation of VF 0.4 - 45, VF 0.4 - 150 voltmeters A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
C 2001/8140 Varnish
C. Tools
Spanners and screwdriver of corresponding size from tool set
D. Referenced information E.
-
Procedures (1) Tilt the right instrument board. (2) Install and fasten the voltmeter by 4 screws. (3) Remove the cover of the terminal block (1) (Fig. 401) by unscrewing 2 screws holding the cover. (4) Connect the network conductors to the voltmeter clamps and secure them by varnish. (5) Set up the cover (1) over clamps and fix it by 2 screws. CAUTION:
VOLTMETER EARTHING SCREW (2) MUST BE RELIABLY ELECTRICALLY CONNECTED TO THE AIRFRAME.
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FIG. 401
VF 0.4 - 45, VF 0.4 - 150 VOLTMETER (REAR VIEW) (1) Cover; (2) Screw
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VF 0.4 - 45, VF 0.4 - 150 VOLTMETER ADJUSTMENT / TEST 1. Check of VF 0.4 - 45, VF 0.4 - 150 voltmeters A.
Fixture, Test and Support Equipment
Source of alternating current with frequency adjustable from 400 Hz to 1000 Hz and output at least 100 W Frequency meter of class 1.0 Reference voltmeter of class 0.5 to 1500 Hz Reostat Switch
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures The wiring diagram for voltmeter testing is given in Fig. 501. The testing must be performed under normal conditions:
FIG. 501
•
working position of the scale - vertical
•
ambient air temperature + 20 ± 5°C
VOLTMETER TESTING DIAGRAM
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MAINTENANCE MANUAL U - source of alternating current with frequency adjustable within 380 to 420 Hz, with output power at least 100 W R - reostat enabling uninterrupted setting of voltage Hz - frequency meter of class 1.0 VX - tested voltmeter V - reference voltmeter of class 0.5 to 1500 Hz •
K - switch voltage frequency 380 - 420 Hz
•
practical sinus wave of voltage
•
with the exception of earth magnetic field, no other magnetic field must be present
•
relative humidity of ambient air 40 - 80 %
Test must be performed in all points of the working parts of the scale which are numbered, in the following sequence: (1) Connect the instrument according to the test wiring diagram. Switch voltage power on and continuously change its value from zero to the maximum, and back from the maximum to zero of the scale. At the same time ensure if the movement of the moving part of the voltmeter is indeed continuous, without hindrance. The pointer must move without difficulty, with no jumps. If you find that the pointer moves with jumps or hindrance, during a continuous change of voltage then discontinue testing and dispatch the instrument for repair. (2) Gradually set-up the voltmeter pointer to all points marked with numbers and covered by luminescent mass (on the working part of the scale) and record the voltage values obtained from the reference instrument. As basic inaccuracy it is necessary to take the highest difference (absolute difference) between the data read out from the reference and tested instruments, obtained from measurement results in continuous increase and decrease of the measured value, related to the upper limiting value measured by the instrument, and expressed in percents.
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SPC-5(C) STATIC INVERTER DESCRIPTION AND OPERATION 1. Purpose The SPC-5(C) static inverter is determined to convert 28 VDC to 26 VAC, 400 Hz sine wave power
2. Technical data Nominal supply voltage (VDC)
28 VDC
Input Current (ADC)
2.7 A
Nominal line output voltage
26 V
Nominal output frequency
400 Hz +/- 1%
Phase/Waveform
Single/ Sine Wave
Overload & Short Circuit Protection:
Withstands without damage or degradation load exceeding 150% of rated output to an output dead short.
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MAINTENANCE MANUAL DC CURRENT SOURCES DESCRIPTION AND OPERATION 1. General The sources of DC voltage in the aircraft are two startergenerators. As emergency source of DC current serve two alkaline NiCd or lead-acid accumulator batteries. The starter-generators can be used either as a generator of as a starter. The electric direct current system is divided to three following circuits:
left starter-generator circuit
right starter-generator circuit
battery circuit and external sources
2. List of components No.
Name
Qty
Location
1.
Starter-generator
LUN 2132.02-8
2
LH, RH engine
2.
Regulator
LUN 2167.03-8
2
Between 9 and 10 frame on the left, right
3.
Differential relay
DMR 400 DSP
2
Between 8 and 9 frame on the right
4.
Electromagnetic releasing switch DC GENERATOR LH DC GENERATOR RH
V 016 or V 016.01-8
1 1
Overhead panel
5.
Battery
20 NKBN-25 or SAFT P/N 26108 or VARTA / HAWKER 20FP25H1C(T-R) or NCSP-B-25150 or Concorde RG-CIS25
2
Between 1 and 2 frame on the left
6.
External power source plug
ShRAP 500
1
Between 1 and 2 frame on the left
7.
Fuse A 51
IP 250
1
Between 1 and 2 frame on the left
8.
Contactor
TKS 201 DOD
5 2
Between 1 and 2 frame on the right Between 8 and 9 frame
9.
Contactor
TKD 133 DOD
2
Between 10 and 11 frame on the left, right
10.
Contactor
TKS 401 DOD
1
Between 1 and 2 frame on the right
11.
Shunt
ShA-440 (8)
2 2
Between 1 and 2 frame On frame 11 and left, right
12.
Relay
B073576N or B073576N /G
4
Between 1 and 2 frame on the right
13.
Contactor
TKD 511 DOD
2 2
Between 8 and 9 frame on the left Between on the 8 and 9 frame on the right
14.
Switch BATTERY I BATTERY II
2 VG-15K-2S
1 1
Overhead panel Overhead panel
15.
Switch-over VA-METER
B082605N - P3(8)
1
Right control panel
16.
Voltammeter
LUN 2743.01-8
2
Instrument panel
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Type (Drwg No.)
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MAINTENANCE MANUAL
No.
Name
17.
Fuse BAT. I Fuse BAT. II
18.
Fuse GENERATOR BLOCKING
Qty
Location
4 CSN 354733F/1500 4 CSN 354733F/1500
1 1
Between 1 and 2 frame on the right Between 1 and 2 frame on the right
4 CSN 354733F/1500
2
Between 1 and 2 frame on the left
19.
Relay
TKE 52 PODG
1 1
Between 8 and 9 frame on the left on 7 frame the right
20.
Relay
TKE 54 PODG
2 2 2 1
Between 9 and 10 frame on the right Between 1 and 2 frame on the right Between 8 and 9 frame on the right Between 10 and 11 frame on the right
21.
Circuit breaker EMERGENCY BUS BAR I EMERGENCY BUS BAR II
AZRGK 50 AZRGK 50
1 1
Between 1 and 2 frame on the right Between 1 and 2 frame on the right
Circuit breaker BUS BAR S3B BUS BAR S2A BUS BAR S1B BUS BAR S2B BUS BAR S1A BUS BAR S3A
AZRGK 50 AZRGK 50 AZRGK 50 AZRGK 50 AZRGK 50 AZRGK 50
2 1 2 1 1 1
Between 7 and 8 frame Between 7 and 8 frame Between 7 and 8 frame Between 7 and 8 frame Between 7 and 8 frame Between 7 and 8 frame
0.4 CSN 354733F/1500 0.4 CSN 354733F/1500
1 1
Between 8 and 9 frame on the left Between 8 and 9 frame on the left
IP 150 IP 150
1 1
Between 1 and 2 frame on the right Between 1 and 2 frame on the right
2 CSN 354733F/1500 2 CSN 354733F/1500 2 CSN 354733F/1500
2 2 4
Between 1 and 2 frame on the right Between 1 and 2 frame on the right Between 8 and 9 frame on the right
Circuit breaker S1-S2 BAT. 1 BAT. 2 BAT. I BAT. II
AZR 70 AZR 70 AZR 70 AZR 70 AZR 70
1 1 1 1 1
Between 7 and 8 frame on the right Between 7 and 8 frame on the right Between 7 and 8 frame on the right Between 1 and 2 frame on the right Between 1 and 2 frame on the right
Circuit breaker REGULATOR ON-OFF
AZRGK 10
2
Between 10 and 11 frame on the left, right
Signal cell EXTERNAL POWER SUPPLY
-
1
Central warning display
29.
Signal cell BATTERY
-
1
Central warning display
30.
Signal cell DC GENERATOR
-
1
Central warning display
22.
23.
24.
25.
26.
27. 28.
Fuse EMERGENCY BUS BAR I EMERGENCY BUS BAR II
Fuse A 73 A 74 Fuse BATTERY I VA BATTERY II VA VOLTAMMETER
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No.
Name
Type (Drwg No.)
Qty
Location
31.
Contactor
TKD 501 DOD
1
Between 8 and 9 frame
32.
BAT. TEMP circuit breaker
AZRGK 2 (if installed)
1
Overhead panel
33.
Temperature indicator
BTI-600-2A 1 or DBTI 2002 (if installed)
1
Instrument panel
34.
Temperature probe
P600-14B (if installed)
2
Battery
35.
Push button TEST BTI
KNI (if installed)
1
Instrument panel
36.
Annunciator BAT. TEMP. I,II
LUN 2662.34 (if installed)
2
glareshield
37.
Temperature signal.
3089946225 (if installed)
2
battery
38.
Push button SIGN.
2KNR (if installed)
1
LH control panel
39.
Plug
07400
1 or 2 LH/RH control panel (if installed) 1 On frame 21 (if installed)
3. Operation NOTE: A.
Electric wiring diagram is stated in the list of aircraft Wiring Manual.
Operation of generators circuit When the left (right) engine is running, generator A 1 (A 2) is connected to the aircrafts network by switching on of the breaker GENERATOR LH (RH) A 7 (A 8). By switching on the breaker, voltage is supplied from the generator through circuit breaker A 63 (A 64) to the contactor coil of differential relay A 5 (A 6) which will connect the generator to the aircraft network in case when the voltage in the electrical circuit of the generator is about 0.3 to 0.7 V higher than voltage in the aircraft network (battery). Derived from the moveable contact of differential relay contactor is signalling of generator shut-off from the aircraft network using the relay A 21 (A 22) and signal cell GENERATOR LH (RH) on the warning display. After connecting a generator to aircraft electrical network, signal cell GENERATOR LH (RH) will extinguish. Generator voltage is maintained within the required tolerances by a semiconductor voltage regulator A 3 (A 4) under various speeds of the engine and under different loads in the aircraft electrical network. If voltage exceeds the value of 31 V (in case of defective voltage regulation), the generator will be automatically shut-off from the aircraft electrical network by a protective circuit located in the voltage regulator A 3 (A 4), which will activate the switch GENERATOR LH (RH) A 7 (A 8). This will cause a disconnection of differential relay A 5 (A 6) contactor. When voltage of the generator A 1 (A 2) will drop below the limit of aircraft electrical network voltage the current coil of the differential relay A 5 (A 6) will disconnect the generator from the aircraft electrical network with inverse current magnitude between 25 - 35 A. Magnitude of voltage and current supplied by the generator can be checked by the voltmeter A 29 (A 28) with the shunt A 41 (A 42). Measuring circuits of the voltammeter are protected by cut-off fuses A 45, A 47 (A 46, A 48).
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MAINTENANCE MANUAL Voltammeter A 28 is also used to check the voltage and current supplied from aircraft batteries. Selection of the measured node is performed by a switch-over VA METER A 27. When measuring voltage and current of the right side generator, the switch-over A 27 is in position GEN RH. The left and right generator circuits under normal operation conditions are independent of each other, and are separated by means of a contactor A 13 and circuit breaker A 12. When only one generator operates, the contactor A 13 interconnects both generator circuits. Contactor A 13 is controlled automatically, the control being derived from position of relay A 21 (A 22) contacts, which are controlled from the moveable contact of differential relay A 5 (A 6) contactor. The contactor is always supplied from battery of that generator circuit, from which the generator is cut-off by differential relay A 5 (A 6). During the time bus-bars are interconnected by contactor A 13, functioning are circuits for parallel cooperation of generators, which are located in the voltage regulator A 3 (A 4). The regulators for parallel cooperation (terminals 5 of both regulators) are connected through the relay A 62 controlled by the contactor A 13. NOTE:
Parallel cooperation of generators is functioning in case of second generator connection to network only.
B.
Operation of the batteries circuit Each generator circuit under normal functional conditions incorporates one battery A 9 (A 10). When both generator circuits are interconnected through the contactor A 13, both batteries can operate parallely, provided one of the generators is operating. The battery is connected to the aircraft network by switches BATTERY I (II), A 25 (A 26). By switching on the contactor A 15 (A 16) its coil circuit will be closed and it will connect battery A 9 (A 10) through fuses A 73 (A 74), shunts A 40 (A 20) and circuit breakers A 67 (A 68), A 43 (A 44) to the aircraft electrical network of generator A 1 (A 2). Batteries signaling circuit signals in case when the battery is not connected to the aircraft electrical network. Signaling is derived from the contactor A 15 (A 16) and from the controlling relay A 35 (A 36), which connects by its contacts the supply circuit of signal cell BATTERY on the central warning display. The signal cell is common to both batteries and the distinction as to which of the two batteries is cut-off must be made by ammeter A 28 (deviation of pointer during consumption of charging). Supply of signal cell is protected by cut-off fuse A 79. Voltage and charging of discharging current can be checked by the voltmeter A 28 of a switch-over VA METER A 27 is in position BAT I or BAT II. The checked parameters are recorded from the shunt A 40 (A 20). The measuring circuit is protected by cut-off fuses A 53, A 69 (A 54, A 70). Charging current of the battery is measured on the ammeter scale from "0" to the left and the discharging current from "0" to the right. In the regime of the engine starting-up from aircraft batteries, both batteries will be parallely interconnected by means of contactors A 77, A 78. These contactors are controlled by contacts of relay
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MAINTENANCE MANUAL A 65, A 66, which are activated during the engine start up, namely relay A 65 when the port engine is starting up, and relay A 66 when the starboard engine is being started up. Contactor control circuits A 77 are protected by cut-off fuse A 80, contactor A 78 and by cut-off fuse A 79. C. Operation of battery temperature measurement circuit (if installed) On the aircraft is installed a accumulator battery temperature measuring device. The device is put into operation by switching on the switches BATTERY I, II and circuit breaker BAT. TEMP. on the overhead panel. The temperature measurement circuit includes the circuit breaker AZRGK 2, BTI 600-2A temperature indicator push button KNR and P 600-48 temperature probe. D. Operation of battery overheating signaling system (if installed) –refer to the Fig. 5. The accumulator battery overheating signaling system is installed on the aircraft. The system is put into operation by switching on the switches BATTERY I, II and circuit breaker BAT TEMP on the overhead panel. In case of battery overheating a BATTERY OVERHEAT red warning light comes on. The warning lights are located on LH side of the glareshield of the instrument panel. If the red warning light comes on, switch off the BATTERY I (II) switch on the overhead panel. If the BATTERY I, II switches are in OFF position, you can continue in flight. After landing report the failure to the ground personal.
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FIG. 1
INSTRUMENTS LAYOUT OF DC CURRENT SOURCES SYSTEM (1) Starter - generator LUN 2132.02-8; (2),(3) Regulator LUN 2167.03-8; (4),(5) Differential relay DMR-400 DSP; (6),(7) Battery 20 NKBN - 25, or SAFT P/N 26108, or VARTA 20FP25H1C(T-R); (8) External power source plug ShRAP 500; (9),(10),(11) TKS 401 DOD contactor; (12),(13) TKD 133 DOD contactor; (14) TKS 401 DOD contactor; (15) ShA 440-8 shunt; (16),(17) TKE 54 PODG relay; (18),(19) TKD 511 DOD contactor; (20),(21) LUN 2743.01-8 voltammeter; (22) TKE 52 PODG relay; (23),(24) TKE 54 PODG relay; (25),(26) B 073 576 N relay; (27),(28),(29) ShA 440-8 shunt; (30),(31) TKD 511 DOD contactor; (32) TKE 52 PODG relay; (33),(34) TKE 54 PODG relay; (35),(36),(37),(38) TKS 201 DOD contactor; (39),(40) B 073 576 N relay; (41) TKE 54 PODG relay
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FIG. 2
INSTRUMENTS LAYOUT OF DC CURRENT SOURCES SYSTEM (Detail A, B from Fig. 1) (1) Starter - generator LUN 2132.02-8; (2),(3) Regulator LUN 2167.03-8; (4),(5) Differential relay DMR-400 DSP; (6),(7) Battery 20 NKBN - 25, or SAFT P/N 26108, or VARTA 20FP25H1C(T-R); (8) External power source plug ShRAP 500; (9),(10),(11) TKS 401 DOD contactor; (12),(13) TKD 133 DOD contactor; (14) TKS 401 DOD contactor; (15) ShA 440-8 shunt; (16),(17) TKE 54 PODG relay; (18),(19) TKD 511 DOD contactor; (20),(21) LUN 2743.01-8 voltammeter; (22) TKE 52 PODG relay; (23),(24) TKE 54 PODG relay; (25),(26) B 073 576 N relay; (27),(28),(29) ShA 440-8 shunt; (30),(31) TKD 511 DOD contactor; (32) TKE 52 PODG relay; (33),(34) TKE 54 PODG relay; (35),(36),(37),(38) TKS 201 DOD contactor; (39),(40) B 073 576 N relay; (41) TKE 54 PODG relay
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FIG. 3 INSTRUMENTS LAYOUT OF DC CURRENT SOURCES SYSTEM (Detail C from Fig. 1) (1) Starter - generator LUN 2132.02-8; (2),(3) Regulator LUN 2167.03-8; (4),(5) Differential relay DMR-400 DSP; (6),(7) Battery 20 NKBN - 25, or SAFT P/N 26108, or VARTA 20FP25H1C(T-R); (8) External power source plug ShRAP 500; (9),(10),(11) TKS 401 DOD contactor; (12),(13) TKD 133 DOD contactor; (14) TKS 401 DOD contactor; (15) ShA 440-8 shunt; (16),(17) TKE 54 PODG relay; (18),(19) TKD 511 DOD contactor; (20),(21) LUN 2743.01-8 voltammeter; (22) TKE 52 PODG relay; (23),(24) TKE 54 PODG relay; (25),(26) B 073 576 N relay; (27),(28),(29) ShA 440-8 shunt; (30),(31) TKD 511 DOD contactor; (32) TKE 52 PODG relay; (33),(34) TKE 54 PODG relay; (35),(36),(37),(38) TKS 201 DOD contactor; (39),(40) B 073 576 N relay; (41) TKE 54 PODG relay
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FIG. 4
DIAGRAM OF BATTERY TEMPERATURE MEASURING DEVICE (IF INSTALLED)
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FIG. 5
BLOCK DIAGRAM OF BATTERY OVERHEATING SIGNALING SYSTEM (IF INSTALLED)
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DC CURRENT SOURCES SERVICING 1. Inspection of switches in the pilot cockpit A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.00.A Routine
E.
Procedures (1) Check if the electric external power source and switches BATTERY I and II on the overhead panel are switched off. (2) Inspection of the switches and circuit breakers on the overhead panel. (3) All switches and circuit breakers on the overhead panel must be switched off. Switch off the switches and circuit breakers. NOTE:
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Position "SWITCHED OFF" is labeled on the overhead panel.
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LUN 2132.02-8 STARTER - GENERATOR DESCRIPTION AND OPERATION 1. Purpose Starter-generator serves to start the aircraft engine M 601E and in cooperation with LUN 2167.03-8 voltage regulator is determined to supply the airborne DC network.
2. Technical data Nominal voltage
28 V
Operational voltage
27 ÷ 28.5 V
Nominal current
200 A
Peak starting current during the starting up
approx. 700 A
Short - time overload •
for period of 5 minutes
250 A
•
for period of 5 secs in revs. higher than 7000 rpm
400 A
Overload •
at cooling air temperature of + 5°C
•
at ambient temperature up to + 30°C during the flight only, at revs. higher then 7000 rpm
250 A for period of 30 min
220 A permanently
3. Operation LUN 2132.02-8 starter-generator is a quadripolar generator of DC current with shunt excitation supplied through regulator from self terminals. Commutating and compensating winding is serially connected to anchor winding. Serial exciting winding is connected in function of starter only. LUN 2167.03-8 regulator •
enables engine start-up from aircraft and external ground power source
•
supplies nominal cooling power (self-and ram cooling)
•
supplies limited output for a limited period in operating, range of revolutions with self-cooling only
•
maintains constant value of operating voltage within operating, range of revolutions with variable loading
•
prohibits the possibility of dangerous voltage increase (overvoltage)
•
provides the possibility of parallel function of both sets
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FIG. 1
STARTER - GENERATOR WIRING DIAGRAM B - plus clamp E - minus clamp +
A - exciting winding C - start-up circuit D - compensating winding voltage tap (to regulator)
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LUN 2132.02-8 STARTER - GENERATOR SERVICING 1. Functional check of the LUN 2132.02-8 starter - generator A.
Fixture, Test and Support Equipment
Electric external ground power supply
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.01.A Periodical
E.
Procedures (1) Connect the external ground power supply. (2) Do not proceed in the vicinity of the propellers during the engine operation. (3) The LUN 2132.02-8 starter-generator functional check. The starter - generator must work as the starter as well as the dynamo. (4) Start-up the LH engine. Switch on the DC GENERATOR LH circuit breaker on the overhead panel for LH engine connection. Disconnect the external ground power supply. (5) Start-up the RH engine from the LH engine generator. After RH engine starting, stop the LH engine. Switch on the DC GENERATOR RH circuit breaker on the overhead panel for RH engine connection. (6) Start-up the LH engine from the RH engine generator. (7) Shut off both engines. (8) Clear away the external ground power supply.
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LUN 2167.03-8 REGULATOR DESCRIPTION AND OPERATION 1. Purpose LUN 2167.03-8 regulator is supplied from clamps of LUN 2132.02-8 starter-generator and excites it to hold output voltage in the whole loading range and at the revolutions change on the ground and during the flight. Regulator must also secure a parallel function of two starter-generators and by means of dangerous voltage increasing on the bus-bar in case of regulator failure. It limits the maximum generator current to 300 A.
2. Technical data Operating voltage
27 28.5 V
Excitation current
7A
3. Operation A.
Regulation Starter-generator starts to turn by engine at disconnected regulator. At the moment, when it takes over the function of dynamo, generator starts to work. Terminal C will disconnect from the bus-bar and generator output will be connected to clamp A of the excitation - see Fig. 2. Generator input is supplied from clamp B of a starter-generator via contact of the switch III. Excitation is realized through the break contact of relay B1 (see Fig. 1). When dynamo voltage increases approx. to 15 V relay B1 will attract and disconnect the contact of circuit and the excitation is already supplied from a regulator via output transistor T4. Through other contact of relay B1 the circuit of parallel cooperation is interconnected to the second regulator. Regulator operates on the pulse principle. The excitation winding of the LUN 2132.02-8 starter-generator is wired in the emitter circuit of the terminal switching transistor T4. The transistor switches at constant frequency - the value of excitation current changes relative to the value of pulse duty ratio. Square-wave voltage exciting the output amplifier is created by operational amplifier X2 as a result of comparison of saw-tooth voltage (T5, T6) with the anchor voltage of the starter-generator. During parallel functioning, both regulators are interconnected according to diagram in fig. 2. This circuit secures the uniform load division of two parallel connected starter - generators in various functional conditions. By connecting of the regulator terminals 4 and 5 into external circuit the voltage drop, proportional to voltage difference on auxiliary poles of starter-generators, i.e. proportional to current difference, is created on the resistor R5. This voltage is treated by differential amplifier with inertia X1 and through the filtering element R11, C5 is supplied to input of comparator X2.
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FIG. 1
LUN 2167.03-8 WIRING DIAGRAM
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MAINTENANCE MANUAL Disconnecting terminal 7 serves to disconnecting of this circuit when regulator is to be checked or repaired. In case of starter-generator load irregularity, the compensation is going on so that a circuit reduces the field current value if starter-generator is overloaded and increases field current value in case of its insufficient load. B.
Current limitation circuit The circuit obtains a signal from starter-generator current through terminal 4 and treats it in the differential amplifier X3 with PI coupling and non-sensitivity. Non-sensitivity is set up by potentiometer R 21. If starter-generator current will increase over the set-up level, the voltage on output X3 will increase too and after diode D4 opening it affects on the input of comparator X2 so that a current is limited.
C. Voltage protection At regulator failure, when voltage increases over allowed limit or if overvoltage appears in the aircraft network, the voltage protection disconnects a regulator supplying by means of a switch with electromagnetic releasing. Operator can ensure by hand re-switching, if the failure is lasting. Protection circuit is composed of a comparator X1, on which input the voltages from slow and fast protection dividers are added. Slow protection breaking voltage is derived from regulator supply voltage and can be set up by potentiometer R4. Fast protection breaking voltage is derived from starter-generator excitation voltage and can be set up by potentiometer R7. Comparator X2 latch voltage is set up by potentiometer R17. Dynamic properties of the protection are set up by RC - elements R9, R10 and C1, C2. After regulator switching on the capacitors are charged at operating voltage through diodes D5, D10 and thereby the protection preparation to intervention is speeded-up. Connection to external clamp 7 is controlled by a comparator output through diode D9, thyristor Ty 1.
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FIG. 2
DIAGRAM OF PARALLEL WIRING OF STARTER-GENERATORS WITH REGULATORS LUN 2167.03-8 I - Regulator; II - Starter-generator; III - Switch; IV - Starting contactors
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LUN 2167.03-8 REGULATOR SERVICING 1. LUN 2167.03-8 regulator functional check A.
Fixture, Test and Support Equipment
B 096 629 N Interconnecting unit B 5-8 (B 5-7) Source V 7-16 Voltmeter D 567 Voltmeter C 43-17 Voltammeter
B.
Materials
Not applicable
C. Tools
No. 710 - 2.3x105 Screwdriver 5.5x7 CSN 230611.6 Wrench
D. Referenced information
024.30.02.B Periodical
E.
Procedures (1) Prepare the work site in accordance with diagrams, stated in Fig. 301 - 304. (2) Verification of regulator function:
check the system of generator parallel operation
functional check of protection electrical circuits (of overvoltage protection)
functional check of current limitation circuits
(3) The overvoltage protection circuits must secure the following functional features: Input "slowly"
Input "fast"
Note
29.9 V
26.0 V
- At lower voltage value the overvoltage protection circuits must not disconnect within 60 secs
29.0 V
- At higher voltage value the overvoltage protection circuits must secure a disconnection within 10 secs
31.0 V
CAUTION:
TO CHECK A FUNCTION OF OVERVOLTAGE PROTECTION (ACCORDING TO PARA (6)), FIRST CHECK PARALLEL GENERATOR OPERATION (ACCORDING TO PARA (5)).
(4) Operational test of the voltage regulator. (a) Connect the voltage regulator in accordance with diagram in fig. 301. EFFECTIVITY ALL
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FIG. 301
DIAGRAM OF TESTING EQUIPMENT R - LUN 2167.03-8 regulator (tested instrument) P - B 096 629 N interconnecting unit Z1 - B 5-8 (B 5-7 supply) V1 - V7-16 voltmeter V2 - D 567 voltmeter
(b) Switch on the supply Z1 and increase voltage continuously from zero value (at the same time watch as it changes according to voltmeter V1 indications). At the same time check in what way the output voltage increases (on V2). This voltage must increase parallely with the input voltage increasing. As input voltage achieves a value of approximately 15 V (since 10/2007 is value 17.5 up to 21.5 V), the relay B1 located inside of regulator must switch (it is necessary to check by hearing) and through switched contacts of this relay output current then proceeds to the output transformer T4 (see Fig. 1). When the input voltage achieves a value of approximately 26 V, the output voltage must decrease in parallel with the input voltage increasing. When supply voltage is increased to value of 28.5 V, the zero-voltage appears on the output. Voltage value, at which the output voltage will start to drop, can be set up by means of an adjustable potentiometer (trimmer capacitor). The setting up can be carried out from the outside owing to good availability of the adjustable elements. (c) At the input voltage of 28.5 V, adjust the potentiometer R 33 to the position so that the output voltage would be approximately of 7 V. By setting up of the potentiometer in the reverse direction achieve a zero-voltage on the output (check according to voltmeter V2 indications). (d) Decrease the input voltage from the value of 28.5 V to the value of 26.0 0.5 V. Output value must change from 0 V to the maximum value approximately 24 V in this range. EFFECTIVITY ALL
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MAINTENANCE MANUAL (5) Functional check of circuits of generator parallel operation. (a) Connect the regulator in accordance with diagram stated in Fig. 302.
FIG. 302
DIAGRAM OF TESTING EQUIPMENT R - LUN 2167.03-8 voltage regulator (tested regulator) P - B 096 629 N interconnecting unit Z1 - B 5-8 (B 5-7) source Z2 - B 5-8 (B 5-7) source V1 - V 7-16 voltmeter V2 - D 567 voltmeter V3 - C 43-17 voltammeter
(b) Set up the voltage of 28.5 V on the source Z1. If voltage of the source Z2 equals to 0 V, the output voltage must be 0 V too. Increase fluently a voltage of source Z2 from the value of 0 V to the value of 2 V. Output voltage (in accordance with voltmeter V2 indications) must fluently increase too. (6) Functional check of overvoltage protection circuits. (a) Connect the regulator according Fig. 303.
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FIG. 303
DIAGRAM OF TEST EQUIPMENT R - LUN 2167.03-8 voltage regulator (tested regulator) P - B 096 629 N interconnecting unit Z1 - B 5-8 (B 5-7) source V1 - V 7-16 voltmeter V2 - V 7-16 voltmeter V3 - C 43-17 voltammeter C - 3 GN 016/1 solenoid breaker Z2 - B 5-8 (B 5-7) source
(b) Check of the input "slowly" Increase the input voltage (see voltmeter V1 indications) up to the value of 29.8 V. Check voltage in accordance with voltmeter V3 (switch C must be in switched on position). By means of the stop watch ensure, that overvoltage protection circuits (switch C) do not switch in 60 seconds. CAUTION:
CLAMPS 3 - 6 ARE INTERCONNECTED.
Increase the input voltage to the value of 31.1 V. Overvoltage protection circuits and the breaker C must switch on in 10 seconds. Observe when voltage on V3 decreases to zero value and make sure by hearing that a sound is produced by solenoid switching on of the breaker C. Set up (deregulate) the voltage on V1 at zero value. (c) Check of the input "fast"
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MAINTENANCE MANUAL CAUTION:
CLAMP 3 IN STATE "SWITCHED OFF".
Increase the input voltage into such a value to achieve the voltage of 25.9 V on the output (according to voltmeter V3 indications). At the same time in parallel check of voltage on voltmeter V3, make sure by means of the stop watch that overvoltage protection circuits and the breaker C do not switch on within 60 seconds. Increase the input voltage to achieve a voltage of 29.1 V (according to voltmeter V2 indications) on the output. Overvoltage protection circuits and the breaker must switch within 10 seconds at this value. Make sure that the voltage of V3 has decreased to zero value and the solenoid of the breaker C will produce a corresponding sound (check by hearing). Set up the input voltage to zero value. (7) Functional check of current limitation circuits (a) Connect the voltage regulator in accordance with diagram stated in fig. 304.
FIG. 304
DIAGRAM OF TEST EQUIPMENT R - LUN 2167.03-8 voltage regulator (tested regulator) P - B 096 629 N interconnecting unit Z1 - B 5-8 (B 5-7) source Z2 - B 5-8 (B 5-7) source V1 - D 567 voltmeter
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MAINTENANCE MANUAL V2 - V 7-16 voltmeter V3 - C 43-17 voltammeter V4 - C 43-17 voltammeter (b) Set up the input voltage according to voltmeter V1 to such a value so as to achieve the output voltage approximately equal to 50 % of the input voltage value (according to voltmeter V2 indications). Increase fluently the voltage of V3 from the zero value. As soon as the voltage on voltmeter V3 exceeds the value of 2.8 V and it will be in the range of 3.2 V to 3.4 V, the output voltage (on V2) will decrease to zero value. The voltage at terminal 8 of voltage regulator will increase at the same time from the value of approximately 2 V to the value of approximately 12 V. (8) If overvoltage protection circuits according to the paragraph (6) and current limitation circuits in accordance with instructions stated in paragraph (7) do not secure stated voltage values, it is necessary to set up these circuits. (a) Loosen 4 screws by a wrench 5.5x7 and take off the regulator cover. (b) Setting-up of the input "slowly" Set-up work must be performed in accordance with paragraph (6), subparagraph (b). Set-up the voltage value, at which overvoltage protection circuits must switch, by an adjustable potentiometer R4 in the range of 30.6 V to 30.7 V (see wiring diagram in Fig. 1). For this purpose use a No. 710 - 2.3x105 screwdriver. (c) Setting-up of the input "fast" Set up work is to be performed in accordance with instructions stated in paragraph (6) subparagraph (b). Set up the voltage at which overvoltage protection circuits must be activated, at the value of 29 V by a potentiometer R7. (d) Connect the universal voltmeter to the outlet 9 of the overvoltage protection circuit inside of the regulator against the frame (terminal 2). Before checking, set up the voltage at outlet 9 approximately to the value of 2V (see paragraph (4)) by means of the parallel operation circuit (from source Z2). Increase fluently the voltage between terminals 6 and 2 and source Z1. The voltage at terminal 9 of the circuit will rapidly increase in the voltage range of 29.6 0.2 V. If rapid voltage increasing is not achieved in this range it is necessary to perform setting up by a potentiometer R17. (e) Set up the regulator cover and fasten it. (9) Clear away the test equipment and measuring instruments.
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LUN 2167.03-8 REGULATOR REMOVAL / INSTALLATION 1. Removal and installation of the LUN 2167.03-8 regulator A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Emery cloths No. 400 C 1005/0080 Varnish
C. Tools
No. 697 - 6x120 Screwdriver 8x10 CSN 230611.7 Side spanner L 410.9141-05 Screwdriver
D. Referenced information
024.30.02.A Periodical
E.
Procedures (1) Lift off the ceiling of the aircraft cabin in the space of the frames 8 12 by loosening 5 quick locks by means of L 410.9141-05 screwdriver. (2) LUN 2167.03-8 regulator removal (a) Remove 2 sockets of the cabling at the regulator between the 9 and 10 frame. (b) Remove 2 regulators by loosening 8 screws by means of No. 697 - 6x120 screwdriver and by a spanner 8x10. (3) LUN 2167.03-8 regulator installation (a) After return of the regulators from the laboratory reinstall them by tightening 8 screws by means of No. 697 - 6x120 screwdriver and a wrench 8x10. Clean the framing points to the metallic lustre by an emery cloth No. 400 and paint them by the varnish C 1005/0080. (b) Connect 2 sockets of the cabling and secure them by a binding wire. (4) Cover again the ceiling of the aircraft cabin by screwing on 5 loosen of 5 quick locks by L 410.9141-05 screwdriver.
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DMR - 400 DSP DIFFERENTIAL RELAY DESCRIPTION AND OPERATION 1. Purpose DMR - 400 DSP relay is designed for: a)
Connection of generator to the aircraft electrical network when the generator voltage will be higher then the network voltage.
b)
Disconnection of generator from the electrical network at the stated value of reverse current.
c)
Securing of generator disconnection signalling from the network.
d)
The generator protection in case of reverse polarity of battery or the generator.
2. Technical data Nominal voltage
28.5 V
Nominal current of power circuit
400 A
Generator overvoltage above regulator voltage at which the relay will switch
0.3 to 0.7 V
Reverse breaking current
25 to 35 A
3. Operation A.
Differential relay function When generator voltage is lower than battery voltage, no current passes through shunt winding L2 (see Fig. 1) of the control relay since diode D2 is connected in the impermeable direction. In this way the diode D2 prevent an overload of winding of the differential control relay. Diode D1 creates bias which shifts the volt-ampere operating characteristics of diode D2 so as to achieve in the permeable direction on the diode an optimum voltage loss influencing the setting of switching voltage of the control relay. The voltage loss on diode D1 is caused by current passing from the plus terminal of the battery through diode D1 and resistor R1 to the minus terminal. When generator voltage will exceed the battery voltage by 0.3 to 0.7 V, diode D2 becomes conductive, current begins to pass through shunt winding L2 of the control relay so that the contacts of control differential relay will connect. The contactor winding circuit will be connected and contactor contacts will connect the generator to the battery. When generator voltage will drop and will be lower than battery voltage, reverse current will be supplied from battery to the generator, during passage through the serial turn S in the control relay the current will pre-magnetise the anchor. At the value of reverse current between 25 and 35 A the magnetic field of serial turn S will be sufficient to make the anchor charge its position and there by open up the contacts of the differential control relay and the contactor will disconnect the generator from the network.
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024.30.03 Page: 1 Nov 1/11
MAINTENANCE MANUAL In order to provide for a reliable disconnection of contacts of the control relay, resistor R2 is placed between diode D2 and the minus terminal of relay DMR - 400 DSP.
FIG. 1
DMR - 400 DSP DIFFERENTIAL RELAY WIRING DIAGRAM
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MAINTENANCE MANUAL Diode D3 prevents connection of the generator when the generator or the battery is wrongly polarized. B.
Control relay function The magnetic system of the relay consists of one permanent magnet with poles divided to two parts. The upper poles - parts of the south pole, and the lower poles, parts of the north pole. The anchor is a moveable part of the magnetic circuit and according to its position between the poles is attracted to one or the other pair of magnet poles. When the relay contacts are disconnected the anchor is attracted to the left upper and right lower magnet poles, with relay contacts connected, the anchor is attracted to the left lower and right upper poles. The relay anchor freely passes through the inside of the coil and serial turn, and as a result of interference effect the magnetic field of the permanent magnets and magnetic field generated by a current passing through the differential and serial windings in the anchor the relay will take one of the extreme positions. The anchor cannot remain in a neutral position. The relay connection will happen at generator voltage be higher than voltage in the aircraft network by 0.3 to 0.7 V. The relay is maintained in a contact position by permanent magnets of the relay. When generator supplied current will pass through the serial turn (generator is loaded), the current passing through the serial turn coil generate magnetic field which will magnetize the relay anchor, at the same time the position of the anchor remains unchanged and the force holding the anchor to closer poles will grow. When current starts to pass through the serial turn in the opposite direction than described above (generator voltage is lower than board battery voltage), then with intensity of reverse current 25 to 35 A the anchor will be re-magnetized and the control relay contacts will be disconnected. After an automatic generator cut-off current will again pass through the differential winding, but now from the network to the generator. The current passing in this direction will not change the position of the anchor, but quite to the contrary, it will facilitate opening of the relay contacts.
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DMR - 400 DSP DIFFERENTIAL RELAY SERVICING 1. Inspection of the contacts of the DMR-400 DSP differential relay A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
CSN 660860 Alcohol 1 % Deerskin
C. Tools
L 410.9141-05 Screwdriver No. 697 - 4.5x100 Screwdriver (the shortened)
D. Referenced information
024.30.03.A Periodical
E.
Procedures (1) By means of L 410.9141-05 screwdriver remove the ceiling upholstery between the frame 8 and 9 (4 quick locks) in the space of the passengers cabin. (2) Remove the contacts cover from the differential relay, two screws by means of No. 697 - 4.5x150 screwdriver. (3) Ensure about the cleanliness and state of the contacts. The following defects are not permitted: blackened or burnt up contacts Works to be performed if technical requirements are not met: clean the blackened contacts with alcohol and with deerskin. In case of burnt up contacts replace them by new ones. (4) Cover the relay contacts by 2 screws and No. 697 - 4.5x100 screwdriver. Cover the ceiling space of the frames 8 and 9 back again with upholstering of 4 quick-locks by means of L 410.9141-05 screwdriver.
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20 NKBN - 25 or SAFT P/N 26108 ACCUMULATOR BATTERY DESCRIPTION AND OPERATION 1. Purpose 20 NKBN - 25 or SAFT P/N 26108 NiCd battery is designed for:
supply of the aircraft network electrical devices in case of starter-generators failure
independent starting
power supply of particular loads on the ground while absence of other power sources
2. Technical data The Technical Description and Maintenance Manual of battery 20 NKBN - 25 or SAFT P/N 26108 are contained in a separate volume. CAUTION:
FOR CORRECT OPERATION AND DURABILITY OF THE STORAGE BATTERY IT IS NECESSARY NOT TO EXCEED THE MAXIMUM PERMISSIBLE MAINS VOLTAGE. (IF THE BATTERY IS HEAVILY OVERCHARGED, VAPOUR GENERATION AND ELECTROLYTE RUNNING - OFF OCCURS). THE MAINS VOLTAGE DEPENDS ON AMBIENT TEMPERATURE. AT A TEMPERATURE OF 20°C THE VOLTAGE IS TO BE 28.5 V. WHEN THE TEMPERATURE IS HIGHER (40°C), THE MAINS VOLTAGE MUST BE ADJUSTED TO:
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27.5 V TO 28V FOR THE SAFT P/N 26108 BATTERY
28.5 V FOR THE 20 NKBN 25 BATTERY
024.30.04 Page: 1 May 30/14
MAINTENANCE MANUAL 2.1 Determination of SAFT P/N 26108 battery condition Cells condition Using a middle point allows the comparison of 2 series of 10 cells. This method is usually considered as sufficient to identify the possible short-circuit at the end of discharge. The differential value depends on conditions and operating phages considered. The difference of maximum voltage between 2 series of 10 cells is 0.6 V in following conditions:
battery temperature between 0 and + 40°C
discharge current: 10 to 20 A
battery being at least half charged
Battery condition The insulation measurement between positive and grounding of the battery is sometimes used to check the battery condition. It is possible to evaluate the battery behavior a specially during overcharge by recording the battery temperature. Generally speaking, a battery should not be charged at temperature above 57°C. The upper limit is generally + 71°C in overcharge. Using the battery above this limit remains exceptional. State of charge of the battery SAFT position is as follows:
It is possible to determine that the battery is at least half charged by voltage measurement in determined conditions.
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20 NKBN - 25 or SAFT P/N 26108 ACCUMULATOR BATTERY SERVICING 1. Check of the voltage of accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.04.B Routine
E.
Procedures NOTE:
Following procedure is valid for all types of the batteries (20 NKBN-25 or SAFT P/N 26108 or VARTA / HAWKER 20FP25H1C(T-R) or Concorde RG-CIS25 etc.)
(1) Switch on the circuit breakers and switches on the overhead panel: INVERTERS 115V AC I (if installed), INVERTERS 36 V AC I, II, ADF I, II, GYRO COMPASS I, II (if installed), PFD I, II (if installed), DCP I, II (if installed), DCU (if installed), CHP (if installed), AHRS I (if installed), ADC I, II (if installed), NAV/GPS I (if installed), WING TIP TANK LH, RH, FUEL PUMP LH, RH, COCKPIT, STBY CIRCUIT, PASSENGER CABIN 2/3, SEARCHLIGHTS - LANDING I, II, ANTICOLL. BEACON, RADIO ALTIMETER, SSR I, II, POSITION LIGHTS on the overhead panel and the switches WING TIP TANK FUEL TRANSFER on the RH instrument panel. (2) Turn on simultaneously both switches BATTERY I, II for the time of 3 - 5 sec. (3) Read the voltage value of both VA - meters (set up gradually the VA - meter change-over switch to positions BAT I V - A, BAT II V - A). The voltage must be 25 V (-1) V. If will detected low battery voltage, charge the battery according to the respective AMM section e.g. 024.30.04 or 024.30.05 or 024.30.10. Switch off all the circuit breakers from the point (1). (4) Check the battery temperature measuring system (if installed) as follows: (a) Switch on the circuit breakers BATTERY I, II, BAT. TEMP. on the overhead panel. (b) Depress the TEST BTI pushbutton. The temperature indicated on the BTI 600-2A indicators must reach 38°C, and the yellow and red lights on the temperature indicators must illuminate. (c) After the TEST BTI pushbutton is released, the indicated temperature will go back to its original value and the lights on the indicator will turn off. (d) Switch off the circuit breakers BATTERY I, II, BAT. TEMP. on the overhead panel.
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MAINTENANCE MANUAL (5) Check the battery overheating signalling system (if installed) (a) Switch on the circuit breakers BATERY I, II and BAT. TEMP on the overhead panel. (b) Push the SIGN pushbutton on the LH control panel. Red signal lights must illuminate. (c) After the SIGN pushbutton is released the lights turn off. (d) Switch off the BAT. TEMP. and BATTERY I, II circuit breakers on the overhead panel.
2. Inspection of the accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Distilled water according to IEC 993 Baysilone spray Non metal brush Soft cloth
C. Tools
Necessary tools from tool kit
D. Referenced information
024.30.04.C Periodical
E.
Procedures NOTE:
Check of 20 NKBN-25 or SAFT P/N 26108 accumulator battery is carried out according to instructions in Maintenance Manual of a battery 20 NKBN - 25 or SAFT P/N 26108.
3. Inspection of the accumulator battery bay between the No. 1-2 frames A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
No. 400 Emery paper CSN 656542 Petrol
C. Tools
No. 697 - 6x120 Screwdriver
D. Referenced information
024.30.04.D Periodical
E.
Procedures (1) Remove the cover of the accumulator battery bay. (2) Take out the accumulator batteries. (3) Inspect of the batteries bay. Inspection of the accumulator batteries bay - any uncleanness and the marks of electrolyte running away are not allowed. Remove any dirt according to work procedure 024.30.04.F.
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MAINTENANCE MANUAL (3) Inspect the battery pins. Burning up accumulator battery pins is not allowed. Clean the burnings with the emery paper No. 400 and wash them by petrol. Set up the accumulator batteries to their position. (4) Inspect the attaching rails. (6) Cover again the accumulator batteries bay.
4. Charging of the accumulator batteries A.
Fixture, Test and Support Equipment
Charge / discharge unit (e.g. RF 80-K (CE)) Thermometer
B.
Materials
Distilled water according to IEC 993; Baysilon lubricant
C. Tools
Necessary tools from tool kit
D. Referenced information
024.30.04.E Periodical
E.
Procedures NOTE:
Charging of the battery 20 NKBN - 25 or SAFT P/N 26108 is to be performed according to Maintenance Manual of a battery 20 NKBN - 25 or SAFT P/N 26108.
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5. Preservative of the accumulator battery bay A.
Fixture, Test and Support Equipment
A metallic pail for water A vessel for the conservation agent
B.
Materials
REZISTIN ML - Lubricant K 17 GOST 10877.76 B-70 or NEFRAS or CSN 656542 Petrol UNIVERSAL Saponate agent Sodium carbonate-soda MOLINO Hairless textile, kind 393/130 CSN 874730
C. Tools
Necessary tools from tool kit
D. Referenced information
024.30.04.F Periodical
E.
Procedures (1) Prepare the detergent solution, the neutralization solution, the conservation agent REZISTIN ML and cleaning means (rags, brush). (a) Preparation of the detergent solution:
10 % detergent
90 % water
(b) Preparation of the neutralization solution:
0.1 kg sodium carbonate
1 liter of water
(c) Preparation of the conservation solution: REZISTIN ML, thinned as needed by lacquer petrol. (2) Work to be performed if TR (Technical Requirements) are not met: Replace the damaged pins, clean impurities on pins with petrol and burning up with emery paper No. 400 and petrol. The following defects are not permitted: damaging, uncleanness and burning up of the pins, leakage of electrolyte, non conserved places, electric devices and the cabling stained by REZISTIN ML, the run-down conservation agent in the corners of the batteries spaces, uncleanness sticking on the layer of the conservation agent, corrosion spots. Wipe the battery bay thoroughly with a rag wetted in water solution of the detergent agent. Remove corrosion spots. (3) Neutralize the battery bay by solution of sodium carbonate. (4) Wipe this space by a rag wetted in clean water. After washing dry it by a clean dry rag. EFFECTIVITY ALL
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MAINTENANCE MANUAL CAUTION:
DURING THE CLEANING WORKS MAKE SURE THAT THE CLEANING SOLUTIONS DO NOT COME INTO CONTACT WITH THE EQUIPMENT AND AGGREGATES WITHIN THE BATTERY BAY.
(5) The conservation agent REZISTIN ML should be thoroughly mixed before use. (6) Wipe out the whole battery bay by REZISTIN ML using hairless textile. After being coated, the conservation agent has to make a thin consisting layer on the whole surface. The coating should get dry at the temperature of at least 15°C for 24 to 48 hours. CAUTION:
THE ELECTRIC DEVICES AND THE CABLING MUST NOT COME INTO CONTACT WITH THE CONSERVATION AGENT REZISTIN ML.
(7) Clean away the vessels and tools used for the conservation.
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20 NKBN - 25 or SAFT P/N 26108 ACCUMULATOR BATTERY REMOVAL / INSTALLATION 1. Removal and installation of the accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Cloth
C. Tools
Z 37.9110-10 Screwdriver
D. Referenced information
024.30.04.A Routine, Periodical
E.
Procedures (1) Remove the cover of batteries bay by loosening of 18 screws of the quick locks by means of Z 37.9110-10 screwdriver. (2) Removal of the batteries (a) Loose 2+2 safety pins on each battery disconnect the plugs of the batteries temperature measuring system or batteries overheating signalling system (if installed) and remove the batteries from the aircraft. (b) Hand over the batteries to the workshop. (3) Installation of the batteries (a) Bring the batteries to the aircraft after checking in workshop. (b) Set up the batteries into a battery bay and secure them by 2+2 pins and install the plugs of the batteries temperature measuring system or batteries overheating signalling system (if installed). (c) Check the proper connection of the batteries by means of the cockpit voltmeter. (4) Cover the batteries bay by tightening 18 screws of the quick-locks by means of Z 37.9110-10 screwdriver.
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VARTA / HAWKER 20 FP 25 H1C (T-R) ACCUMULATOR BATTERY DESCRIPTION AND OPERATION 1. Purpose VARTA / HAWKER 20 FP 25 H1C (T-R) Ni/Cd airborne batteries is designed for: •
supply of the aircraft network electrical devices in case of starter-generators failure
•
independent starting
•
power supply of particular loads on the ground while absence of other power sources
2. Technical data Number of cells in battery
20
Rated capacity
25 Ah
Rated Voltage
24V
Admitted current of start up load
1550 A
Admitted current of prolonged load
500 A
The current of rated charge (0,2 . I1)
5A
The current of quick charge (I1)
25A
Final charging voltage
1.56 V/cell
Electrolyte – caustic potash solution No. 9 (KOH), density 1.28 + 0.02 kg/l NOTE: The type VARTA 20 FP 25 H1CT-R is with temperature probe NOTE:
It is permissible during further operation of the battery the decrease in electrolyte density until the level 1.22 kg/l.
CAUTION:
THERE IS NO NEED TO CHANGE THE ELECTROLYTE DURING THE LIFE OF THE BATTERY.
Operating temperature range
-40 ÷ +70°C
Operating temperature range during charge-discharge process
-18 ÷ +50°C
Maximum operating altitude
25 000 m
Maximum operating acceleration
15 g in every direction
For more information - Refer to the Nickel - Cadmium Batteries Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
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FIG. 1
20 FP 25 H1C (T-R) VARTA BATTERIES INSTALLATION
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VARTA / HAWKER 20 FP 25 H1C (T-R) ACCUMULATOR BATTERY SERVICING 1. Monthly checks on aircraft of the VARTA / HAWKER accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Necessary tools from tool kit
D. Referenced information
024.30.05.A Periodical
E.
Procedures NOTE:
The battery can be inspected visually fitted in the aircraft or alternatively removed and inspected on the airfield.
CAUTION:
DO NOT DISCONNECT A BATTERY WHILST UNDER LOAD.
(1) Remove the lid from the battery case. Check the locks for defects, if the lid cannot be removed. (2) Check whether the interior battery is contaminated with electrolyte. (3) Check the battery case and lid as well as connectors, pole nuts, temperature sensor assembly for any mechanical and thermal damages, as well as any signs of dents, cracks, splits, overheating, short circuits, melting, burn down, dark spots and tarnish. (4) Inspect the main connector for any damage caused by arcing, faulty connection, corrosion, loose parts, cracks in the connector casing. Any damage found, send battery to workshop. (5) Inspect harnesses, temperature switches, thermistors and thermocouples for loose wiring, cracks, dents, connector pins in place. Any damage found, send battery to workshop and proceed according to the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (6) Record in the battery log book whether the battery has passed or failed. (7) Refit the lid on the battery case after the check.
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2. Quarterly maintenance of the VARTA / HAWKER accumulator batteries A.
Fixture, Test and Support Equipment
Source of the oil free compressed air (with pressure below 3 bar); Megaohmmeter (e.g. EXTECH 380366 or MG302 or equivalent); Multimeter (e.g. EXTECH MP530A or MG302 or equivalent; Charge / discharge unit (e.g. RF 80-K (CE))
B.
Materials
Not applicable
C. Tools
Plastic brush; Insulated torque wrench 0.5-20.0 Nm (5-200 kpcm); Tool box with special HAWKER tools Size No: 43 (HAWKER P/N 929 1480 780); Necessary tools from tool kit
D. Referenced information
024.30.05.B Periodical
E.
Procedures (1) Remove the lid and check that the gasket is fully adhered to the lid. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (2) Inspect battery container and lid for any damages, signs of dents, cracks, splits, overheating, short circuits, melting, dark spots and tarnish. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (3) Inspect the main connector for signs of damage caused by arcing, faulty connection, corrosion, loose parts and cracks in the connector casing. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. CAUTION:
MINERAL SALTS FROM SPILLED ELECTROLYTE ARE CAUSTIC. WHEN CLEANING BATTERIES AND CELLS WEAR GOGGLES AND GLOVES; IN ADDITION WEAR DUST MASK AND EAR PROTECTION WHEN APPLYING COMPRESSED AIR FOR CLEANING; THE COMPRESSED AIR SHALL HAVE A PRESSURE BELOW 3 bar.
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MAINTENANCE MANUAL (4) Tighten any loose vent plugs and clean the top of the cells with a plastic brush, and remove any remaining deposits with an oil free compressed air. (5) Tighten the upper nuts with 5Nm (50 kpcm) torque. (6) Inspect visually harnesses with temperature switches, thermistors, thermocouples, and for loose wiring, cracks, dents, connector pins in place and any damages. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (7) Measure the insulation resistance with a Mega ohmmeter at 250 V DC between the + pin of the battery connector and the battery case. Requirement value: R ≥ 0.5MΩ. If value R ≤ 0.5MΩ, continue at Work procedure 024.30.05.C - Annual Maintenance step (12). (8) Measure and record cell voltages. (9)
Mark cells with voltages lower than 1.2V (as possible defective cells).
(10) Undo the vents and keep them aside on the cells mouth. CAUTION:
DO NOT TOP UP THE CELLS WITH WATER AT THIS STAGE.
(11) Connect the battery to the charge / discharge unit. CAUTION:
DO NOT USE MERCURY THERMOMETER.
(12) Check the battery temperature; Requirement: below 35°C. If battery temperature is higher than 35°C, soak the battery to ambient room temperature (13) Discharge the 24 V batteries at I1 to 20 V. (pay particular attention to previously marked cell(s) in step 8/9). NOTE:
RATED CURRENT (I1) - The rated discharge current of the battery returns not less than its rated C1 capacity in 1 hour.
Requirement: The voltage of each cell after 48 minutes must be equal / greater than 1.0V. NOTE:
If the discharge at the I1 rate is not feasible, select a different rate and criteria from the table below.
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Discharge current rate
Time (min) cell voltage reading
Voltage requirement for cells (V)
0.2 * I1
240
≥ 1.0
0.4 * I1
120
≥ 1.0
0.6 * I1
80
≥ 1.0
0.8 * I1
60
≥ 1.0
I1
48
≥ 1.0
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MAINTENANCE MANUAL Record the cell voltages at the corresponding time indicated in column 2 in the battery log book. If the requirement is not met, then continue with Task “Reconditioning” in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (14) Soak the battery to room temperature for up to 8 hours before recharging. (15) Recharge the battery using either (15-a), or (15-b) or (15-c) step •
Adjust the electrolyte level at a current of 0.2*I1 15 minutes to 10 minutes prior to end of the charge methods, (15-a), (15-b), and (15-c).
•
Afterwards measure the voltage on each cell prior to the end of charge at 0.2* I1.
Requirement: cell voltage shall be ≥ 1.56 V •
Record cells end of charge voltages in the logbook.
CAUTION: •
DO NOT CHARGE THE BATTERY WITH CURRENTS HIGHER THAN I1
•
IF YOU CANNOT FULLY SUPERVISE, DO NOT USE METHOD DESCRIBED IN (15-c).
Identify cells for replacement. Refer to Task in the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 or later.
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MAINTENANCE MANUAL (a) IUI-charge = IUI charge – method (Fig. 301) (Combination of constant voltage and constant current charge with two current limitations) •
Charge the battery at I1 until voltage has increased to 1.55V times number of cells and charge for 2 hours at 0.2* I1
•
After about 1 hour charge, check that battery has reached the voltage level to switch the charge current to 0.2* I1.
FIG. 301
TYPICAL IUI-CHARGE FOR 24V AIRCRAFT BATTERY
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(b) I charge method (Fig. 302) •
FIG. 302
TYPICAL CONSTANT CURRENT CHARGE FOR A 24V AIRCRAFT BATTERY
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Charge the fully discharged battery for seven hours at 0.2* I1.
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MAINTENANCE MANUAL (c) II charge method (Fig. 303) •
Charge the fully discharged battery with parameters selected from the table below and afterwards charge for two hours at 0.2* I1
•
Check battery current switching to 0.2* I1 at the stage 1(max) time presented in the table below.
FIG. 303
current
Stage 1 time (max)
0.4 * I1
180
0.6 * I1
120
0.8 * I1
90
TYPICAL II-CHARGE FOR A 24V AIRCRAFT BATTERY (16) Allow the battery to stand for one hour to support the escapes of charging gases from cells. (17) Tighten the vents between 1 and 24 hours after charging and fit the lid onto the case. (18) Release the battery to service (operation) , or if required in accordance with Task "Commissioning" mentioned in EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
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3. Annual maintenance of the VARTA / HAWKER accumulator batteries A.
Fixture, Test and Support Equipment
Source of the oil free compressed air (with pressure below 3 bar); Megaohmmeter (e.g. EXTECH 380366 or MG302 or equivalent); Multimeter (e.g. EXTECH MP530A or MG302 or equivalent; Charge / discharge unit (e.g. RF 80-K (CE))
B.
Materials
Not applicable
C. Tools
Plastic brush; Insulated torque wrench 0.5-20.0 Nm (5-200 kpcm); Tool box with special HAWKER tools Size No: 43 (HAWKER P/N 929 1480 780); Necessary tools from tool kit
D. Referenced information
024.30.05.C Periodical
E.
Procedures (1) Remove the lid and check that the gasket is fully adhered to the lid. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (2) Inspect battery container and lid for any damages, signs of dents, cracks, splits, overheating, short circuits, melting, dark spots and tarnish. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (3) Inspect the main connector for signs of damage caused by arcing, faulty connection, corrosion, loose parts and cracks in the connector casing. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. CAUTION:
MINERAL SALTS FROM SPILLED ELECTROLYTE ARE CAUSTIC. WHEN CLEANING BATTERIES AND CELLS WEAR GOGGLES AND GLOVES; IN ADDITION WEAR DUST MASK AND EAR PROTECTION WHEN APPLYING COMPRESSED AIR FOR CLEANING; THE COMPRESSED AIR SHALL HAVE A PRESSURE BELOW 3 bar.
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MAINTENANCE MANUAL (4) Tighten any loose vent plugs and clean the top of the cells with a plastic brush, and remove any remaining deposits with an oil free compressed air. (5) Tighten the upper nuts with 5Nm (50 kpcm) torque. (6) Inspect visually harnesses with temperature switches, thermistors, thermocouples, and for loose wiring, cracks, dents, connector pins in place and any damages. Any damage found, record defect and replace in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (7) Measure and record cell voltages. (8)
Mark cells with voltages lower than 1.2V (as possible defective cells).
(9) Undo the vents and keep them aside on the cells mouth. CAUTION:
DO NOT TOP UP THE CELLS WITH WATER AT THIS STAGE.
(10) Connect the battery to the charge / discharge unit. CAUTION:
DO NOT USE MERCURY THERMOMETER.
(11) Check the battery temperature; Requirement: below 35°C. If battery temperature is higher than 35°C, soak the battery to ambient room temperature, which can take up to 8 hours. (12) Discharge the 24 V batteries at I1 to 20 V. (pay particular attention to previously marked cell(s) in step 8). NOTE:
RATED CURRENT (I1) - The rated discharge current of the battery returns not less than its rated C1 capacity in 1 hour.
Requirement: The voltage of each cell after 48 minutes must be equal / greater than 1.0V. NOTE:
If the discharge at the I1 rate is not feasible, select a different rate and criteria from the table below.
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Discharge current rate
Time (min) cell voltage reading
Voltage requirement for cells (V)
0.2 * I1
240
≥ 1.0
0.4 * I1
120
≥ 1.0
0.6 * I1
80
≥ 1.0
0.8 * I1
60
≥ 1.0
I1
48
≥ 1.0
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MAINTENANCE MANUAL Record the cell voltages at the corresponding time indicated in column 2 in the battery log book. If the requirement is not met, then continue with Task “Reconditioning” in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (13) Continue discharge at 0.1* I1 to an average of 0.5 volt per cell. (14) Tighten all vents. (15) Disassembly. CAUTION:
ATTENTION: DO NOT LOOSE THE LOWER NUTS OF THE CELL TERMINALS.
(a) Undo and remove the upper pole nuts (b) Remove washers, and intercell links (c) Remove the thermostat assembly from cells, if any (d) Identify cell positioning within the case (e) Remove all the cells from the case starting with the middle cell of each row using the appropriate insulated cell puller. (f)
Remove insulating material from the case, also noting their positions
(g) Undo the thermostat connectors and remove the harness in one-piece from the battery case (h) Remove the main connector, only if defective. (16) Carry out battery cleaning in accordance with following steps (16-a) to (16-d). NOTE:
If the insulation resistance value of the battery is smaller than 0.5 MΩ, Battery cleaning shall be carried out. Do not use any other solvent than soapy water for cleaning disassembled battery components.
(a) Remove any contamination of connectors and harnesses with a damp cloth, soaked in a soapy water solution. (b) Clean all remaining disassembled battery components, e.g. battery case, liners, vent plugs in a solution with soapy water. Afterwards rinse with fresh water. NOTE:
it is recommended that drying with the pressurized air-supply should be below 3 bar.
(c) Allow all components to dry naturally, or supported by oil-free pressurized air. (d) Coat all disassembled and cleaned metallic components with silicone spray. EFFECTIVITY ALL
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MAINTENANCE MANUAL (17) Inspection and check. (a) Check the disassembled upper pole nuts, washers, and intercell links for signs of damage and corrosion. Replace as necessary in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
FIG. 304
DIAGRAM OF CELLS CONNECTION OF 20FP25H1CT-R BATTERY (b) Check the cells for thermal damage and discolouration. Replace as necessary in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (c) Check the cable assembly with thermostats / thermistors (if any) for signs of damage (d) Test the thermostat and thermistor functions as detailed under Task "Functional Test on thermostats" mentioned in the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (e) Replace the assembly as necessary in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. (f)
Replace as necessary in accordance with the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
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MAINTENANCE MANUAL (18) Reassembly the battery CAUTION:
INCORRECT ASSEMBLY HARMS THE AIRWORTHINESS OF THE BATTERY AND WILL RESULT IN ADDITIONAL REPAIR WORK. USE ALWAYS THE BATTERY COMPONENTS IN ACCORDANCE WITH THE CORRESPONDING IPL (ILLUSTRATED PARTS LIST).
•
Fit the main connector into the battery case (if replaced)
•
Fit the thermostat harness assembly connector into the battery case
•
Place the liners, the cells and dummy cells, packing pieces and heater mats (if any) into the original positions of the battery case according to the IPL (Illustrated Parts List)
•
Tighten the lower pole nuts with an calibrated torque wrench with the torque 4Nm (40 kpcm).
•
Place intercell links on cells terminals
•
If shown on the IPL, place the intercell links fixed to the thermostat assembly on the terminals of the corresponding cells
•
Place spring washers on the intercell links and screw upper nuts on the pole threads
•
Tighten the upper pole nuts using an calibrated torque wrench with the torque 5Nm (50 kpcm).
(19) Refit the lid and test the insulation resistance as described in step (19-a) to (19-b). CAUTION:
READ THE SAFETY INSTRUCTIONS FOR THE HIGH VOLTAGE – INSULATION RESISTANCE TESTER.
(a) Measure the insulation resistance with a MΩ-meter at 250 V DC between the + pin of the battery connector and the battery case. If the insulation resistance is below 0.5 MΩ subject the battery to battery cleaning Task in step (16). (b) Record the values in the battery log book. (20) Remove the lid. (21) Connect the battery to the charge/discharge unit. (22) Remove the vents. (23) Test the vent’s response pressure as detailed in Task "Testing vents response pressure after cleaning" mentioned in the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
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MAINTENANCE MANUAL (24) Charge the battery for 8 hours at 0.2* I1 as shown in fig. 302 – commissioning charge. Adjust the electrolyte level 15 minutes before the end of charge. (25) Stand the battery for 1 hour. (26) Discharge the 24V battery at I1 to 20V Requirement: The voltage of each cell after 48 minutes must be equal / greater than 1 Volt. NOTE:
If the discharge at the I1 rate is not feasible, select a different rate and criteria from the table below. Record the cell voltages at the corresponding time indicated in column 2 in the log book.
Discharge current rate
Time (min) cell voltage reading
Voltage requirement for cells (V)
0.2 * I1
240
≥ 1.0
0.4 * I1
120
≥ 1.0
0.6 * I1
80
≥ 1.0
0.8 * I1
60
≥ 1.0
I1
48
≥ 1.0
(27) Soak the battery to room temperature for up to 8 hours before recharging. (28) Recharge the battery using either (28-a), or (28-b) or (28-c) step •
Adjust the electrolyte level at a current of 0.2*I1 15 minutes to 10 minutes prior to end of the charge methods, (28-a), (28-b), and (28-c).
•
Afterwards measure the voltage on each cell prior to the end of charge at 0.2* I1.
Requirement: cell voltage shall be ≥ 1.56 V •
Record cells end of charge voltages in the logbook.
CAUTION: •
DO NOT CHARGE THE BATTERY WITH CURRENTS HIGHER THAN I1
•
IF YOU CANNOT FULLY SUPERVISE, DO NOT USE METHOD DESCRIBED IN (28-c).
(a) IUI-charge = IUI charge – method (Refer to the Fig. 301) •
Charge the battery at I1 until voltage has increased to 1.55V times number of cells and charge for 2 hours at 0.2* I1
•
After about 1 hour charge, check that battery has reached the voltage level to switch the charge current to 0.2* I1.
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(b) I charge method (Refer to the Fig. 302) •
Charge the fully discharged battery for seven hours at 0.2* I1.
(c) II charge method (Refer to the Fig. 303) •
Charge the fully discharged battery with parameters selected from the table below and afterwards charge for two hours at 0.2* I1
•
Check battery current switching to 0.2* I1 at the stage 1(max) time presented in the table below. current
Stage 1 time (max)
0.4 * I1
180
0.6 * I1
120
0.8 * I1
90
(29) Measure the electrolyte density on cells: CAUTION:
WEAR APPROPRIATE PPE (PERSONAL PROTECTIVE EQUIPMENT).
WARNING:
AVOID SPILLING OF ELECTROLYTE INTO THE BATTERY DURING THE MEASUREMENTS. DO NOT CHANGE CELLS ELECTROLYTE.
NOTE:
Any measurement of electrolyte density directly after an adjustment of cells electrolyte level with water may result in values below the requirement. Always measure the electrolyte density after the charge following the electrolyte adjustment on fully charged cells.
15 minutes after the recharge, measure the temperature with a thermometer and the density of the electrolyte with a hydrometer or an electronic density meter on 3 random selected cells out of a 20 cells battery. Requirement: 1.30 kg/L ≥ Density: ≥ 1.26 kg/L. If density values are below the required value, measure the density of all cells and replace according to the EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later. If the density are above 1.3 kg/L. Check whether electrolyte was adjusted correctly before. Check whether electrolyte temperature is considerably below 20°C. Check whether battery was charged. (30) Refit the vents on the cells between 1 hour and not later than 24 hours after charge. (31) Refit the lid on the battery case.
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MAINTENANCE MANUAL (32) Measure the insulation resistance as described in step (19-a) to (19-b). Requirement: Insulation resistance ≥10 MΩ. If less than 10 MΩ, remove the lid and allow the battery to stand for 24 hours in a dry ventilated environment. (33) Release the battery to service (operation) , or if required in accordance with Task "Commissioning" mentioned in EnerSys / HAWKER Operating and Maintenance Manual, SAP number: 4635536 Date of issue: 01/01/2013, Index of Revision: 01 - or later.
4. Testing the temperature sensor (if installed) A.
Fixture, Test and Support Equipment
Heatable fixture Multimeter (Ohmmeter) (e.g. EXTECH MG302 or equivalent)
B.
Materials
Not applicable
C. Tools
Insulated torque wrench 0.5-20.0 Nm (5-200 kpcm)
D. Referenced information
024.30.05.D Periodical
E.
Procedures WARNING:
DO NOT DISCONNECT CONNECTORS FROM THE TEMPERATURE SENSOR!
(1) Remove the temperature sensor with connector from the battery – remove all parts which fasten the temperature sensor to cell of battery container with torque wrench. (2) Attached the connector with the temperature sensor to a heatable fixture. (3) Connect a ohmmeter between the relevant terminals of the temperature sensor. (4) Increase slowly (1°C/min.) the temperature of heatable fixture to the upper switching temperature 70°C. Temperature sensor must be closing contact at temperature 70°C ± 3°C. (5) Lower the temperature of heatable fixture to the lower switching temperature. (6) If case of absence of temperature sensor switching (see point (3) and (4)) replace it with the new one. (7) Install back the temperature sensor in battery.
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MAINTENANCE MANUAL CAUTION:
IT IS IMPORTANT THAT ALL MEASUREMENTS CARRIED OUT ON THE BATTERY ARE RECORDED IN THE BATTERY LOG BOOK, INCLUDING ANY REFERENCES TO REPAIRS/REPLACEMENT PARTS OF BATTERY OR AMOUNT OF REFILLING DISTILLED WATER. (REFER TO THE NEXT PAGE)
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FIG. 305
BATTERY PROCESS CARD
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VARTA / HAWKER 20 FP 25 H1C (T-R) ACCUMULATOR BATTERY REMOVAL / INSTALLATION 1. Removal and installation of the accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Cloth
C. Tools
Z 37.9110-10 Screwdriver
D. Referenced information
-
E.
Procedures (1) Remove the cover of batteries bay by loosening of 18 screws of the quick locks by means of Z 37.9110-10 screwdriver. (2) Removal of the batteries (a) Loose 2+2 safety pins on each battery disconnect the plugs of the batteries temperature measuring system or batteries overheating signalling system (if installed) and remove the batteries from the aircraft. (b) Hand over the batteries to the workshop. (3) Installation of the batteries (a) Bring the batteries to the aircraft after checking in workshop. (b) Set up the batteries into a battery bay and secure them by 2+2 pins and install the plugs of the batteries temperature measuring system or batteries overheating signalling system (if installed). (c) Check the proper connection of the batteries by means of the cockpit voltmeter. (4) Cover the batteries bay by tightening 18 screws of the quick-locks by means of Z 37.9110-10 screwdriver.
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TKS 201 DOD, TKS 401 DOD CONTACTOR DESCRIPTION AND OPERATION 1. Purpose Except dimensions, contactors of the type TKS 201 DOD and TKS 401 DOD have the same instructions. They are designed for power circuit switching in aerospace technology.
2. Technical data TKS 201 DOD
TKS 401 DOD
Switched nominal voltage
27 V
27 V
Switched nominal current
200 A
400 A
Switching nominal voltage
27 V
27 V
Retaining current
0.4 A
0.4 A
Switching current
5A
5A
3. Operation The contactor solenoid consists of two windings. Switching winding SV and retaining winding PV (see Fig. 1). When voltage is connected do clamps A, B the switching current is passing through the low-ohm coil SV. Consequently the magnetic field, needed to pull the anchor and to connect the contacts K, is generated. When contactor anchor is attached the contact BK will disconnect high-ohmic coil PV will be connected into the circuit and lower retaining current passes through coils. After disconnection of voltage from clamps A, B the contactor spring returns the anchor to idle position and at the same time the contacts K will be disconnected.
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FIG. 1
TKS 201 DOD, TKS 401 DOD CONTACTORS WIRING DIAGRAM
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TKD 511 DOD CONTACTOR DESCRIPTION AND OPERATION 1. Purpose TKD 511 DOD contactor is designed for remote switching of instrument board devices from one bus-bar to the other.
2. Technical data Nominal switched voltage
27 V
Nominal switched current
50 A
Nominal switching voltage
27 V
Retaining current
0.35 A
3. Operation The contactor solenoid consists of two windings. Switching winding SV and retaining winding PV (see Fig. 1). When voltage is connected to claps A, B the switching current is passing through the low-ohmic coil SV. Consequently the magnetic field needed to pull the anchor and to switch over the contact is generated. Clamps 1, 2 will connect and clamps 3, 4 will disconnects. When contactor anchor is attached to contact BK will disconnect high-ohmic coil PV will be connected into the circuit and lower retaining current passes through coils. After disconnecting of voltage from clamps A, B the contactor spring returns the anchor to idle position.
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FIG. 1
TKD 511 DOD CONTACTOR WIRING DIAGRAM
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LUN 2743.XX-8 VOLTAMMETER DESCRIPTION AND OPERATION 1. Purpose LUN 2743.XX-8 magneto electric voltammeter together with ShA 440 (8) shunt is designed to measurement of DC voltage within range 0 - 40 V and to measurement of DC current within the range of 100-0-300 A. Table of the variant LUN 2743.XX-8 voltammeter: Type of voltammeter
Color Marking
LUN 2743.01-8
-
LUN 2743.03-8
Green arc from 25 to 30 V range
LUN 2743.04-8
Green arc from 23.5 to 30 V range
2. Technical data Measuring range of the voltammeter •
voltammeter
0 ÷ 40 V
•
ammeter
100 ÷ 0 ÷ 300 A
Inaccuracy of the voltmeter and ammeter DC voltage and current measuring under normal conditions is ± 2 %.
FIG. 1
LUN 2743.XX-8 VOLTAMMETER
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LUN 2743.XX-8 VOLTAMMETER SERVICING 1. Check of the LUN 2743.XX-8 voltammeter A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600); Multimeter (e.g. EXTECH MG-302); Shunt (e.g. TRIBASE Electric type 80A-100mV)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.08.B Periodical
E.
Procedures (1) Verification of the voltage measurement of the (A28) LUN 2743.XX-8 voltammeter (a) Remove the cover between frames No. 1 to 2 on LH side of the fuselage. (b) Remove the cover from fuse case of the IP-250 (A51) fuse. NOTE:
The A51 etc. are el. symbols - refer to the Wiring Manual of airplane.
(c) Switch OFF the A12 circuit breaker located between frames No. 7 to 8. (d) Connect the ground power unit to the airplane. (e) Switch ON the A30 circuit breaker at the ground power unit (GPU) socket and BATTERY I (A25) switch on the overhead panel. (Switch OFF the A39 circuit breaker at the GPU socket and BATTERY II (A26) on the overhead panel). (f)
Measure with use multimeter the voltage on the A51 fuse and record the its value.
(g) Set the A27 rotary switch to BATTERY I VA position located on the RH control panel and read the value of voltage on the (A28) LUN 2743.XX-8 voltammeter. (h) Compare the values, measured in the steps (1-f) and (1-g) and evaluate the accuracy of voltage measurement that is indicated on the (A28) LUN 2743.XX-8 voltammeter. Not permitted the deviation higher that +/- 4%. (2) Verification of the el. current measurement of the (A28) LUN 2743.XX-8 voltammeter (a) Remove the IP-250 (A51) fuse from fuse case.
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MAINTENANCE MANUAL (b) Connect the multimeter with shunt (e.g. TRIBASE Electric type 80A-100mV) that enable the measurement of the el. current up to the 80A on the clamps of the A51 fuse case. (c) Switch OFF the A12 circuit breaker located between frames No. 7 to 8. (d) Switch ON the A30 circuit breaker at the ground power unit (GPU) socket and BATTERY I (A25) switch on the overhead panel. (Switch OFF the A39 circuit breaker at the GPU socket and BATTERY II (A26) on the overhead panel). (e) Switch ON the Electro, Navigation, and lighting systems on the overhead panel. (f)
Set the A27 rotary switch to BATTERY I VA position located on the RH control panel and read the value of current on the (A28) LUN 2743.XX-8 voltammeter.
(g) Read the el. current value supplied from ground power unit on the multimeter connected as described in step (2-b). (h) Compare the values, measured in the steps (1-f) and (1-g) and evaluate the accuracy of el. current measurement that is indicated on the (A28) LUN 2743.XX-8 voltammeter. Not permitted the deviation higher that +/- 8%. (3) Verification of the measurement of the (A29) LUN 2743.XX-8 voltammeter (a) Carry out the relocation of the plugs between the A28 and A29 voltammeter and perform the check of the A29 voltammeter accuracy according to the steps (1) and (2). (b) Disconnect the ground power unit from airplane.
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LUN 2743.XX-8 VOLTAMMETER REMOVAL / INSTALLATION 1. Removal and installation of the LUN 2743.01-8 voltammeter A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
∅ 0.6 mm CSN 11343.0 426410.91 Binding wire
C. Tools
CSN 230034.2 Lateral pliers
D. Referenced information
024.30.08.A Periodical
E.
Procedures (1) During removal and installation all switches and circuit breakers on the cockpit overhead panel must be switched off. (2) Removal and installation of LUN 2743.01-8 voltammeter. (a) In the cockpit dismount a fixing screw of the right panel on the central instrument panel and tilt the right panel of the instrument panel towards yourself. (b) By means of the lateral pliers No. 3031, remove the binding wire of two P - S connection of voltammeters, disconnect the P - S connections by hand. (c) By a screwdriver loosen 4 + 4 screws fixing voltammeters to the right panel of the instrument panel and take off the voltammeter. (d) Hand the voltammeters (2 pcs) over to the laboratory for checking. CAUTION:
PROTECT THE VOLTAMMETER AGAINST WEATHER EFFECTS, HUMIDITY, IMPACTS, MECHANICAL DAMAGE AND IMPURITIES.
(3) Installation of LUN 2743.01-8 voltammeter to the aircraft after its checking in the laboratory. (a) In accordance with the airframe book and corresponding certificate check if production number of LUN 2743.01-8 voltammeter agrees. (b) Set-up the instrument on the right panel of the instrument panel and tighten 4+4 screws by a screwdriver. (c) Connect the P - S connections of voltammeter according to the diagram and coloured markings of voltammeter, screw on and secure them by a binding wire. (d) Put the right panel of instrument panel into initial position, screw on the fixing screw by hand. (4) Check the voltammeter function.
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MAINTENANCE MANUAL (a) Switch on the switches BATTERY I, II, INVERTER I 36 V and INVERTERS II 36 V at the overhead panel. (b) Switch-over the change-over switch VA METER on the right control panel to position BATTERY VA. (5) Switch off all switches and circuit breakers.
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ShA - 440 (8) SHUNT DESCRIPTION AND OPERATION 1. Purpose ShA - 440 (8) shunt in connection with voltammeter serves to current measurement in the aircraft. The measured current passes through the shunt on which the voltage, drop proportionate to the current and shunt resistance is created. The voltage is then fed to measuring of the voltammeter.
2. Technical data Nominal current
300 A
Voltage drop
75 mV
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ShA - 440 (8) SHUNT SERVICING 1. Inspection of the ShA - 440(8) shunt A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Z 37.9110-10 Screwdriver No. 697 - 6x120 Screwdriver L 410.8141-05 Screwdriver
D. Referenced information
024.30.09.A Periodical
E.
Procedures (1) Dismount two covers between the 1 and 2 frame on the RH by unscrewing by means of Z 37.9110-10 screwdriver and by unscrewing screws by means No. 697 - 6x120 screwdriver. (2) Remove the ceiling upholstery in the space between the 7 and 11 frame on the left by loosening universal screws by means of L 410.9141-05 screwdriver. (3) Perform the inspection of shunt. First of all check whether there are not any deformations, which could cause damage of welds. The following defects are not permitted: mechanical damage of shunt - in this case exchange the shunt. (4) Cover the space between the 1 and 2 frame on the left by setting up two covers and by screwing in universal quick locks by Z 37.9110-10 screwdriver and screws by means of No. 697 - 6x120 screwdriver. (5) Cover the ceiling by the upholstery between the 7 and 11 frame and screw in the screws by a L 410.9141-05 screwdriver.
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RG–CIS25 VALVE REGULATED LEAD – ACID AIRPLANE BATTERY (IF INSTALLED) DESCRIPTION AND OPERATION 1. General The airplane can be equipped with a Concorde RG–CIS25 valve regulated lead – acid airplane batteries. NOTE:
The replacement of the VARTA / HAWKER 20 FP 25 H1CT-R batteries for the Concorde RG-CIS25 lead-acid batteries is described in the Information Bulletin No. L410UVP-E/399b.
A lead – acid battery in which there is no free electrolyte and the internal pressure is regulated by a pressure relief valve. This battery requires no maintenance of the liquid level and recombines the gases formed on charge within the battery to reform water. The battery may be used in any attitude without danger of leakage or spilling of electrolyte. Cell construction: Concorde airplane batteries are valve – regulated, recombinant gas, absorbed electrolyte, lead acid batteries. The cells are sealed with a pressure relief valve that prevents gases within the battery from escaping. The positive and negative plates are sandwiched between layers of glass mat consisting of glass micro fibers of varying length and diameter. This blend features superior wicking characteristics and promotes maximum retention of the electrolyte. Electrolyte is absorbed and held in place by the capillary action between the fluid and the absorptive glass mat fibers. The void space provides the channels by which oxygen travels from the positive to the negative plates during charging. When the oxygen gas reaches the negative plate, it reacts with lead to form lead oxide and water. This reaction at the negative plate suppresses the generation of hydrogen that otherwise would come off the negative plate. In this manner, virtually all of the gas is recombined inside the cell, eliminating the need to add water, resulting in “maintenance free” operation. Grids and plates: Each cell of a storage battery has positive and negative plates arranged alternately, insulated from each other by separators. Each plate consists of a framework, called the grid, and a lead paste compound called active material. The grid is cast a lead alloy. Ay outside frame adds strength to the plate for good vibration and shock durability. The small also act as conductors for the current. The lead paste compound (active material) is applied to the grid in much the same manner as plaster is applied to a lath wall. A different paste formula is used for the positive and negative plates.
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MAINTENANCE MANUAL Plate groups: Plate groups are made by joining a number of similar plates to a common terminal post by means of a plate strap. The capacity of battery is determined by the number and size of plates in a group. Each plate is made with a lug at the top which is fused to the strap. A positive group consists of a number of positive plates connected to a plate strap and a negative group consists of a number of negative plates connected in the same manner. The two groups meshed together with separators between the positive and negative plates constitute a cell element. Separators: The main separator material is made of glass microfibers and is commonly called absorptive glass mat (AGM). This material is extremely porous so it retains a high volume of electrolyte and provides a minimum of resistance to the ions passing through it. The AGM is wrapped around the positive plates to insulate them from the negative plates. An extra layer of micro porous polyethylene surrounds the AGM layer to impart extra puncture resistance and improve battery durability. Cell containers After the cell elements are assembled, they are placed in a container made of plastic. The plastic used is selected for its high resistance to sulfuric acid, low gas permeability and high impact strength. Cell covers: The assembled cell or monoblock has a cover made of plastic material similar to that of the cell container. The cell or monoblock cover has holes through which the terminal posts extend and it also includes the pressure relief valves. The cover is permanently sealed to the cell or monoblock container after the plate groups are installed. Electrolyte: The assembled cell or monoblock contains an electrolyte consisting of a mixture of sulfuric acid and water. The electrolyte is absorbed within the pores of the plates and AGM separator. The battery is nonspillable even when turned upside down. Theory of operation: A chemical reaction takes place when a battery is being charged or discharged. When valve regulated batteries are on charge, oxygen combines chemically with the lead at the negative plates in the presence of sulfuric acid to form lead sulfate and water. This oxygen recombination suppresses the generation of hydrogen at the negative plates. Overall, there is minimal water loss during charging. A very small quantity of water may be lost a result of self discharge reactions. However, such loss is so small that no provision need be made for water replenishment. The battery cells have a pressure relief safety valve that may vent if the battery is overcharged.
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MAINTENANCE MANUAL Definitions: -
Rated C1 capacity - The nominal capacity, expressed in Ampere-hours (Ah), obtained from a fully charged battery when discharged at the one hour rate to specified end point voltage at a temperature of 21 - 25ºC (70 - 77º). C1 rate – The rate in amperes, equal to the battery’s rated C1 capacity. For example, the C1 rate
-
of a battery rated at 25 Ah is 25 amperes. -
End point voltage (EPV) - The voltage at which the discharge current is terminated when measuring battery capacity. Unless otherwise stated, the EPV is equal to 20.0 volts. Open circuit voltage (OCV) – The voltage of the battery at rest (no charging or discharging
-
current present). A stable OCV requires a rest of at least four hours.
2. Purpose RG–CIS25 Valve regulated lead – acid Airplane Battery is designed for:
supply of the airplane network electrical devices in case of starter-generators failure
independent starting
power supply of particular loads on the ground while absence of other power sources
3. Technical data Voltage:
24 V
Rated capacity:
26 Ah
Mass:
29.9 kg max
Capacity at -18ºC:
19.2 Ah
Capacity at -30ºC:
16.2 Ah
Capacity at +50ºC:
28.8 Ah
Operating temperature range:
-40ºC ÷ +70ºC
Maximum operating altitude:
60000 feet
NOTE:
The RG–CIS25 valve regulated lead – acid airplane batteries are designed for use in countries with dominating of the higher environment temperatures. The RG–CIS25 valve regulated lead – acid airplane batteries are not equipped with the batteries temperature measuring system. Wiring of the batteries temperature measuring system is disconnected and secured. Verify the marking of the BAT. TEMP. I, II, signal cells on glare shield and BAT TEMP circuit breaker on the overhead panel with INOPERATIVE labels.
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FIG. 1
THE RG–CIS25 VALVE REGULATED LEAD – ACID AIRPLANE BATTERIES INSTALLATION
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RG–CIS25 VALVE REGULATED LEAD – ACID AIRPLANE BATTERY (IF INSTALLED) SERVICING 1. Check of the voltage of RG-CIS25 accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.10.B Routine
E.
Procedures Perform the check of the voltage RG-CIS25 accumulator batteries according to Work procedure 024.30.04.B mentioned in AMM section 024.30.04. If will detected low battery voltage, charge the battery according to the Work procedure 024.30.10.D
2. Inspection of the RG-CIS25 accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
No. 697 - 6x120 Screwdriver
D. Referenced information
024.30.10.C Periodical
E.
Procedures (1) Remove the battery according to the WP 024.30.10.A mentioned in section REMOVAL / INSTALLATION. (2) External checking of the battery (a) Check the outside surfaces of the battery and electrical connectors for deterioration or corrosion that may affect the battery’s operation. (b) Check the battery for loose or missing fasteners. (c) Check the identification and informational labels to ensure they are legible and securely attached.
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MAINTENANCE MANUAL (d) If the above checks reveal items that need attention, repair or replace battery as appropriate. (3) Inspection of the accumulator battery bay between the No. 1-2 frames (a) Inspect the accumulator batteries bay - any uncleanness and the marks of electrolyte running away are not allowed. (b) Inspect the attaching rails. (4) Install the battery according to the WP 024.30.10.A mentioned in section REMOVAL / INSTALLATION.
3. Charging of the RG-CIS25 accumulator batteries A.
Fixture, Test and Support Equipment
Electronic load, capable of constant current at C1 ADC and 20 - 28 VDC with EPV termination at 20 VDC for capacity testing, commercially available Constant voltage power supply, capable of 28.0 – 28.5 VDC and at least 0.2C1 ADC output for constant potential charging, commercially available Constant current power supply, capable of C1/ 10 ADC and at least 34 VDC output for constant current charging, commercially available Digital multimeter, capable of 18 – 34 VDC with accuracy of 1% or better for measuring OCV, commercially available Thermometer
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.30.10.D Periodical
E.
Procedures WARNING:
THIS PROCEDURE ONLY BE DONE IN A WELL VENTILATED AREA BECAUSE A SIGNIFICANT AMOUNT OF HYDROGEN GAS MAY BE RELEASED FROM THE BATTERY. IF THE BATTERY IS INSTALLED IN AN AIRPLANE DO NOT PERFORM ANY SERVICING PROCEDURES.
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MAINTENANCE MANUAL Verify the capacity of accumulator batteries for continued airworthiness: (1) Operating less than 1000 hours per year: (a) Initial check at 12 months after initial installation (± 1 month) – perform the step (3) and the work procedure 024.30.10.C. (b) As long as the capacity is above 90%, subsequent capacity checks every 6 months in service (± 1 month) – perform the step (3) and the work procedure 024.30.10.C. (c) If the capacity is between 85% and 90%, subsequent capacity checks every 3 months in service (± 1 month) – perform the step (3) and the work procedure 024.30.10.C. (d) If the capacity is less than 85%, replace the battery. (2) Operating 1000 hours per year or more: (a) Initial check at 1000 hours after initial installation (± 100 hours) – perform the step (3) and the work procedure 024.30.10.C. (b) As long as the capacity is above 90%, subsequent capacity checks every 500 hours in service (± 100 hours) – perform the step (3) and the work procedure 024.30.10.C. (c) If the capacity is between 85% and 90%, subsequent capacity checks every 250 hours in service (± 100 hours) – perform the step (3) and the work procedure 024.30.10.C. (d) If the capacity is less than 85%, replace the battery. (3) Capacity test procedure (a) If the battery is cold, warm it up to at least 20ºC (68ºF) before testing (b) Charge the battery at constant potential per paragraph (2) (c) Connect the battery to the discharge equipment and discharge at the C1 rate on the label (i.e. 24 Amps for a 24 Ah battery). (d) Discharge the battery to an end point voltage (EPV) of 20 volts. (e) Record the time to the EPV. The battery passes the capacity test if the time to the EPV is 51 minutes or greater (85% of rated capacity or greater). (f)
The battery is at least 90% of rated capacity if the time to the EPV is 54 minutes or greater. For other discharge times, the percent capacity can be calculated using this formula: Percent capacity = Discharge minutes x 1.667.
(g) If the battery passes the capacity test, charge at constant potential per paragraph (4) and return battery to full state of charge. The battery is acceptable for installation. (h) If the battery fails the capacity test, perform the conditioning procedure given in paragraph (5). After the battery has been conditioned repeat the capacity test. (i)
If the battery passes the second capacity test, charge at constant potential per paragraph (4) and return battery to full state of charge. The battery is acceptable for installation.
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MAINTENANCE MANUAL (j)
If the battery fails the second capacity test, repeat the conditioning charge per paragraph (5) and repeat the capacity test.
(k) If the battery passes the third capacity test, charge at constant potential per paragraph (4) and return battery to full state of charge. The battery is acceptable for installation. (l)
If the battery fails the third capacity test, the battery should be replaced.
(m) If the battery gets very hot (greater than 55ºC/ 130ºF) during constant potential charging, the battery should be replaced. (4) Constant potential charge procedure NOTE:
CONSTANT POTENTIAL CHARGING IS THE PREFERRED METHOD OF CHARGING THE BATTERY. IF THE BATTERY FAILS THE CAPACITY TEST, THE CONDITIONING CHARGE PROCEDURE SHOULD BE USED
(a) Connect the battery terminals to the constant charging equipment. (b) Apply a constant potential of 28.25 ±0.25 volts with a current capability of at least 0.2 C1 amperes. NOTE:
THE OUTPUT CURRENT OF THE CHARGING EQUIPMENT SHOULD BE SET AS HIGH AS POSSIBLE. RG® SERIES BATTERIES CAN ACCEPT CHARGING RATES UP TO 8C1.
(c) Continue charging until charge current remains constant (within 10%) for 3 consecutive hourly reading. (5) Conditioning charge procedure CAUTION:
THIS PROCEDURE WILL CAUSE THE BATTERY VOLTAGE TO GO AS HIGH AS 34 VOLTS WHICH COULD DAMAGE ELECTRONIC CIRCUITS CONNECTED TO A BATTERY BUS. DO NOT PERFORM A CONDITIONING CHARGE WHILE THE BATTERY IS INSTALLED IN AN AIRPLANE.
CAUTION:
A CONDITIONING CHARGE IS ONLY NECESSARY IF THE BATTERY FAILS THE CAPACITY TEST. THIS PROCEDURE MAY SHORTEN THE BATTERY’S LIFE IF PERFORMED ON A REPETITIVE BASIS.
(a) Discharge the battery at the C1 rate to an EPV of 20 volts. If the battery is already discharged to 20 volt EPV, skip this step.
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MAINTENANCE MANUAL (b) Connect the battery to the constant current charging equipment. When conducting the conditioning charge procedure, the charging equipment must be capable of maintaining a constant current throughout the entire charge period. The battery voltage may get as 36 volts for 24 volt batteries (18 volts for 12 volt batteries), so the charging equipment must be capable of outputting this voltage to maintain constant current. (c) The preferred conditioning charge method is to charge at a constant current of C1/10 (i.e., 4.2. Amps for a battery with a C1 rating of 42 Ampere-hours) until the battery voltage reaches 31 volts (15.5 volts for 12 volt batteries), then continue charging at the same constant current rate an additional 4 hours. The charge profile should be continuous when using this method, i.e., no pauses should be included. However, if there is an interruption (e.g. due to a local power outage), continue from where the profile left off and run to completion. (d) An alternative conditioning charge method is to charge at a constant current rate of C1/10 (i.e., 4.2. Amps for a battery with a C1 rating of 42 Ampere-hours) for a total of 16 hours. The charge profile does not need to be continuous when using this method, i.e., pauses may be included. For example, an 8 hour charge on the first day and an 8 hour charge on the second day is allowable. NOTE:
The method outlined in Step (5-c) above should be used when the battery has been deeply discharged (Open circuit voltage below 20 volts).
CAUTION:
IF BATTERY BECOMES HOT (ABOVE 55ºC/ 130ºF) DURING CONSTANT CURRENT CHARGING, STOP THE CURRENT ALLOW BATTERY TO COOL TO ROOM TEMPERATURE BEFORE CONTINUING THE CHARGE.
(e) After charging, allow the battery to cool down for at least 8 hours or until the battery is within 10ºC/ 18ºF of the ambient temperature, then proceed with the capacity test.
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RG–CIS25 VALVE REGULATED LEAD – ACID AIRPLANE BATTERY (IF INSTALLED) REMOVAL / INSTALLATION 1. Removal and installation of the RG-CIS25 accumulator batteries A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Flat Screwdriver (e.g. Z 37.9110-10)
D. Referenced information
024.30.10.A Periodical
E.
Procedures (1) Remove the cover of batteries bay by loosening of 18 screws of the quick locks by means of flat screwdriver (e.g. Z 37.9110-10). (2) Removal of the batteries (a) Loose 2+2 safety pins on each battery and remove the batteries from the airplane. (b) Hand over the batteries to the workshop for a capacity test. (3) Installation of the batteries (a) Bring the batteries to the airplane after checking in workshop. (b) Set up the batteries into a battery bay and secure them by 2+2 pins. (c) Check the proper connection of the batteries by means of the cockpit voltmeter. (4) Cover the batteries bay by tightening 18 screws of the quick-locks by means of flat screwdriver (e.g. Z 37.9110-10). (5) Verify that the BAT. TEMP. I, II, signal cells on glare shield and BAT TEMP circuit breaker on the overhead panel are marked with the INOPERATIVE labels.
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EXTERNAL POWER DESCRIPTION AND OPERATION 1. General The aircraft can be connected to an external direct current source of voltage 28 V, which serves to starting of drive units to supply and checking of the individual electric circuits when the aircraft is on the ground. The external source is connected to the aircraft through the external source connecting plug located under a lid under the battery bay on the left hand side of the aircraft nose.
2. Technical data A.
For devices checking Voltage: 27 V ÷ 29 V Other requirements are identical to standard GOST 19705-81.
B.
For engine starting Maximum short-time overload: 700 ÷ 800 A The voltage must not fall under 14 V at any phase of starting. (When the button "ENGINE START UP" is pressed the voltage drop to 14 V is admissible max. 2. sec.) NOTE:
External source voltage is measured in position of V - A meter change-over switch NS I or NS II.
3. Operation The external source is connected to the aircraft network through the external power plug A 11. After the plug is inserted the relay A 33, A 34 will change-over switch and will disconnect from the aircraft network: •
battery A 9, A 10 by contactors A 15 and A 16
•
generators A 2 (2 pcs) by means of differential relay A 5, A 6 contactors
After switches BATTERY I, BATTERY II on the overhead panel have been put in the "ON" position, contactor A 19 will connect the external source to aircraft network. Connecting of external source is signaled by signal cell "EXTERNAL POWER SUPPLY" in the warning display in the cockpit. Control circuits of the automatic switching are secured by cut-off fuses A 30, A 39. The power circuit of the external source is secured by a cut-off fuse A 51. NOTE:
Electric wiring diagram is stated in the list of aircraft L 410 UVP-E, E9, E20 Wiring Manual.
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EXTERNAL POWER SERVICING 1. Ground power unit connecting A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.40.00.A Routine, Periodical.
E.
Procedures (1) Open the cover of the ground power unit socket. (2) Prepare the cable of the ground power unit and check its plug whether it is not burnt or damaged. (3) Bolt the connector of the ground power unit into the aircraft external power plug.
2. Ground power unit disconnection A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
024.40.00.B Routine, Periodical
E.
Procedures (1) Disconnect the cable of the ground power unit (after starting up the engine). (2) Close the cover of the plug of the ground power unit on aircraft. (3) Take away the cable of the aircraft ground power unit.
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ShRAP 500 EXTERNAL POWER SOURCE SOCKET DESCRIPTION AND OPERATION 1. Purpose ShRAP 500 external power source socket serves to interconnection of the aircraft with external power source.
2. Technical data Nominal current
500 A
Nominal voltage
30 V
Number of power contacts
2
Number of auxiliary contacts
1
Force necessary for disconnection
200 ÷ 300 N
3. Operation The plug-and-socket connection consists of two parts: of a plug designed to be mounted on the aircraft and of a socket serving like a cable head of the external electric power source. The design used for the plug-and-socket assembly secures the plug-and-socket contact in only one given position of the pins to the sockets. This position will be secured before the contact of pins and sockets. The plug-and-socket connection has not a secured pointed (connected) state.
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ShRAP 500 EXTERNAL POWER SOURCE SOCKET SERVICING 1. Check of the ShRAP 500 external power source socket A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Emery paper No.400 Petrol CSN 656541
C. Tools
Not applicable
D. Referenced information
024.40.01.A Periodical
E.
Procedures (1) Check the state of external power source socket (1 - 2 frame on the left). The following defects are not permitted: Corrosion, burning-up of the pins, uncleanness inside the socket. Clean corrosion and burning up by emery paper No. 400, wash the inner part of the socket by technical petrol CSN 656541. In case of socket bad state, it is necessary to exchange it.
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ELECTRICAL LOAD DISTRIBUTION DESCRIPTION AND OPERATION 1. General NOTE:
Electric wiring diagram is stated in the list of aircraft L 410 UVP-E, E9, E20 Wiring manual.
The direct current aircraft network is designed as being of a one conductor type. The positive pole is distributed by insulated conductors, while the aircraft frame represents the negative pole. From the generator electric power is supplied through a differential relay to the individual bus-bars of the left (right) generator circuit. The circuit of the left generator A 1 is securing the supply to the following bus bars: S 1 A secured by circuit breaker A 59 S 1 B secured by circuit breaker A 57 S 2 A secured by circuit breaker A 56 N S 1 secured by circuit breakers A 43, A 67 and A 37 In the event of a supply voltage loss the bus-bars are automatically switched over: S 1 A to battery A 10 (NS 2) circuit contactor A 24 through circuit breaker A 38 and through circuit breakers A 68, A 44 to the circuit of generator A 2. S 1 B to generator A 2 circuit through contactor A 49 and breaker A 52. The circuit of the right generator A 2 is securing the supply to the following bus bars: S 2 B secured by circuit breaker A 58 S 3 B secured circuit breaker A 61 S 3 A secured by circuit breaker A 60 N S 2 secured by circuit breakers A 44, A 68 and A 38 In the event of a supply voltage loss the bus bars-are automatically switched-over as follows: S 2 B a part of electric devices (supplied through contactor A 23) to the battery A 9 (NS 1) circuit by contactor A 23 through circuit breaker A 37 and through circuit breaker A 67, A 43 to the generator A 1 circuit, and a part of devices supplied via contactor A 32 and circuit breaker A 38 to the battery A 10 circuit. S 3 B to the generator A 1 circuit through contactor A 50 and circuit breaker A 55. Directly supplied from the battery A 9 bus-bar are:
crash recorder circuit secured by circuit breaker K 16
circuit of the left engine fireproof system secured by circuit breaker M 201
position lighting circuit secured by circuit breaker C 34
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MAINTENANCE MANUAL NOTE: During the supplying from external power source is via fuse C 34 supplied IELU LH, RH through circuit breakers M 189 and M 190 board intercommunication device through circuit breaker FA 13 and transceiver VHF I through circuit breaker FN 1. Supplied directly from the battery bus bar A 10 are:
circuit of the right engine fire system secured by circuit breaker M 202
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ELECTRICAL LOAD DISTRIBUTION SERVICING 1. Check of the operation of the automatic switching of bus bars A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600)
B.
Materials
Not applicable
C. Tools
L410.9141-05 Screwdriver
D. Referenced information
024.50.00.A Periodical
E.
Procedures (1) Connect the ground power unit. (2) By means of L 410.9141-05 screwdriver, release and tilt the ceiling upholstery panels between frames No. 7 and 12. (3) The check should be carried out at running engines. Start the both engine according to the Airplane Flight Manual, chapter 4. (4) After starting the engines disconnect the ground power unit. (5) During engines running stay in the pilots’ cockpit. (6) During the run of engines switch off the switches BATTERY I and II on the overhead panel. Switch off the circuit breaker A 12 in space between the frames No. 7 and 8. Switch on the switch/circuit breaker DC GENERATOR LH on the overhead panel. Switch on the circuit breakers SEARCHLIGHTS I, AIRFRAME DE-ICING, COCKPIT 1/3, 2/3 and verify the function of the switched on electric devices. Switch off the switch/circuit breaker DC GENERATOR LH and switch on switch/circuit breaker DC GENERATOR RH. All devices mentioned above must be functioning. Switch off the circuit breakers SEARCHLIGHTS I, AIRFRAME DE-ICING, COKPIT 1/3, 2/3. (7) Switch on the switches BATTERY I, II on the overhead panel. Switch on the circuit breaker A 12 between the frames No. 7 and 8. Switch off the switch/circuit breaker DC GENERATOR RH, BATTERY I and switch on the circuit breaker VHF II (or COM II, NAV/GPS II) and verify the function of the transceiver. NOTE:
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Keep the stated order of switching on and switching-off.
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MAINTENANCE MANUAL (8) Switch on the switch/circuit breaker DC GENERATOR LH and the BATTERY I switch. Switch off the switch/circuit breaker DC GENERATOR RH and the BATTERY II switch. Switch on the circuit breaker BLOWER and verify its function. NOTE:
Keep the stated order of switching on and switching-off.
(9) Switch on the switch BATTERY II and switch/circuit breaker DC GENERATOR RH on the overhead panel. In space between the frames No. 7 and 8 switch off the circuit breaker A 12 and than A 44. Switch off the BATTERY II switch and switch on the circuit breaker VHF I (or COM I, NAV/GPS I) on the overhead panel. Check if transceiver is operative. Switch on the BATTERY II switch and switch off switch/circuit breaker DC GENERATOR RH. Check if transceiver is operative. (10) Stop the both engines according to the Airplane Flight Manual, chapter 4. (11) Switch off all used circuit breakers on the overhead panel. (12) Check if between frames No. 7 and 8 the circuit breaker A 12 and A 44 are switched on. By means of L 410.9141-05 screwdriver close and secure the ceiling upholstered panels between frames No. 7 and 12.
2. Measurement of the voltage values at the connection of A 71 and A 72 contactors A.
Fixture, Test and Support Equipment
Ground power unit (e.g. GPU-600), Мultimeter (measuring direct voltage and a.c. voltage, DC direct current and AC alterting current and electric resistance, accuracy class ± 2,5%, measuring range 10mV to 600V, 10µA to 10A, 2Ω to 5MΩ, input resistance 100kΩ/V) - (e.g. EXTECH MG302 or equivalent)
B.
Materials
Not applicable
C. Tools
L 410.9141.05 Screwdriver
D. Referenced information
024.50.00.B Periodical
E.
Procedures (1) Connect the ground power unit. (2) By means of L 410.9141-05 screwdriver release and tilt the ceiling upholstered panels between frames No. 7 and 12. (3) The check should be carried out at running engines. Start the both engine according to the Airplane Flight Manual, chapter 4.
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MAINTENANCE MANUAL (4) After start-up of engines disconnect the ground power unit. (5) During engines running stay in the pilots’ cockpit. (6) Make sure that the switch for BATTERY I, II and DC GENERATOR, LH, RH are switched-on. (7) Measure the voltage on the bridging of A 71-1, A 72-1 contactors using the multimeter (the bringing is between the No. 1 connectors of the both contactors). The contactors are installed in the power section in the ceiling part between the frames No. 8 and 9 at the right hand side. The voltage measured on this bridging must be zero. (8) Stop the both engines according to the Airplane Flight Manual, chapter 4. (9) Switch off all the switches on the overhead panel. (10) Close and fix the ceiling panels between the frames No. 7 and 12.
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CIRCUIT BREAKING ELEMENTS-FUSES, CIRCUIT BREAKERS DESCRIPTION AND OPERATION 1. General Inertia fuses, instrument fuse tubes and automatic circuit breakers are used to secure the individual electric circuits in the aircraft. Inertia fuses of type IP and instrument fuse tubes of type CSN 354733 F/1500 serve to disconnect the secured electric circuit from the aircraft network. In case of overload or short circuit in this circuit - the fuse will burn. The fuse has to be exchanged. CAUTION: Two types of instrument fuses are used in the aircraft xx.x CSN 354733F/1500 or F/xx.xA 1500A EN60127-2. Where xx.x is normal value of the fuse in ampere. Both types of fuses are equivalent and interchangeable with same nominal value. Circuit breakers of types AZR, AZRGK serve the same purpose as fuses, the only difference being that the respective circuit becomes disconnected, and after repair of the overload or short circuit cause the circuit breaker may same time be used as unipolar switches. Circuit breakers of types KLIXON serve the same purpose as fuses, the only difference being that the respective circuit becomes disconnected, and after repair of the overload or short circuit cause the circuit breaker may same time be used as unipolar switches.
2. Technical data A.
Instrument fuse tubes CSN 354733 F/1500 Nominal current:
0.4, 0.63, 1, 1.6, 2, 2.5, 3.15, 4, 6.3 A
Nominal voltage:
250 V
Instrument fuse body is mounted in instrument fuse holder. B.
Inertia fuses IP 150, IP 250 Nominal voltage
up to 30 V
Nominal current of fuse
IP 150
150 A
IP 250
250 A
The fuse body is mounted in XL 29.820-65 fuse holder. C. Circuit breaker AZRGK, AZR AZRGK
AZR
Nominal current
2, 5, 10, 20, 40, 50 A
70 A
Nominal voltage
27 V
27 V
D. Circuit breaker KLIXON Nominal current:
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½ A, ¾ A, 1 A, 1½ A, 2 A, 2½ A, 3 A, 4 A, 5 A, 7½ A, 10 A
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MAINTENANCE MANUAL 3. Operation Circuit breaker represents an electromagnetic device whose sensitive element in case of generation of current overloads will effect the mechanism of contact disconnection. The sensitive element is made of bimetallic thin sheet. In addition in circuit breakers AZRGK for current values of 20, 40, 50 Amps an electric relay is built in.
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V 016 OR V 016.01-8 ELECTROMAGNETIC RELEASING SWITCH DESCRIPTION AND OPERATION 1. Purpose The electromagnetic releasing switch is designed to disconnect the circuit in the case of failure.
2. Technical data Operating voltage up to
30 V
Minimal voltage
10 A
3. Description The circuit breaker consists of the basic unit with thermal releasing mechanism supported by electromagnetic disconnection.
4. Operation When supplying a voltage to the electromagnet winding the main circuit will be momentarily disconnect.
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V 016 OR V 016.01-8 ELECTROMAGNETIC RELEASING SWITCH SERVICING 1. Functional check of the V 016 or V 016.01-8 electromagnetic releasing switch A.
Fixture, Test and Support Equipment
YE - 2T stabilized DC source (or equivalent) (Technical paramaters: supply voltage 230 V +- 10%, 150 Hz +- 2%; DC voltage complliance 0-40V ; demand electric current max. 3.4 A; supply max. 750 VA; output current max. 10 A; output DC voltage max. 40 V; output supply max. 400 W)
B.
Materials
S 1005 Varnish
C. Tools
No. 697 6x120 Screwdriver
D. Referenced information
024.50.02.A Periodical
E.
Procedures (1) Tilt the overhead panel according to the Work procedure specified in section 031.13.00. (2) BATTERY I, II switches on the overhead panel must be switched off. (3) Using the No. 697 6x120 screwdriver disconnect from the switch A 255 (AC GENERATOR RH), A 256 (AC GENERATOR LH), A7 (DC GENERATOR LH), A8 (DC GENERATOR RH) the following conductors: 461 A (from A 255), 460 A (from A 256), 137 A (from A7) and 138 A (from A8). (4) Switch on the switch. Gradually supply momentarily the 18 V voltage from the Power source onto the connectors of the electromagnetic releasing switch. The switch must be switched off. NOTE:
4 (pcs) of 4.5 V in series connected flat batteries may be used in place of the Power source.
(5) Using the No. 697 6x120 screwdriver connect the previously disconnected conductor and secure it with the S 1005 varnish. (6) Close and secure the overhead panel according to the Work procedure in section 031.13.00.
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CONDUCTORS DESCRIPTION AND OPERATION 1. General The distribution of electric energy is performed by conductors of the type RA, RAF having a cross-section from 0.35 mm sq. to 50 mm sq. The RAF conductors are screened and are used in electric circuits with possible occurrence of high frequency oscillations. The RA conductors are used in the parts of on aircraft with on increased temperature. The conductors are string bound to bundles which are attached to the aircraft structures by collars, clips, locks or buttoned strips. Conductor bundles held in attaching points by metal clips or collars are lined with leatherette. In the engine vicinity conductor bundles are wound by FIRE FLEX tape having the function of mechanical protection. Conductor bundles of individual structural units are interconnected by plug-and-socket connections or bus bars. Soldered connections are made with the use of Sn 50 Pb solder, as flux a spiritgum mixture was used. The soldered connection is cleaned by spirit and lacquered by red varnish C 1005. Every screwed electric joint is covered by a drop of C 2001/8140 paint. All sockets of electrical devices and of plug-and-socket connections are secured in position by binding wire 0.5 CSN 42 6410.9 are sealed.
2. Marking of instruments and conductors All used electric circuits are divided to the following sections according to their function: •
section A - sources of electrical energy
•
section B - engine start up
•
section C - lighting
•
section D - heating, deicing, air conditioning
•
section E - control and signalling of mechanism on aircraft airframe
•
section F – radio equipment
•
section K – recording devices
•
section L - navigational instruments
•
section LA – auto flight (if installed)
•
section LC – signal converter (E) GPWS (if installed)
•
section M - engine check and extinguishing
•
section F subdivides to:
•
section FA - transceiver and intercom
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MAINTENANCE MANUAL •
section FB - radiocompass
•
section FC - radioaltimeter
•
section FD – radio marker
•
section FE – transponder
•
section FG – gyrocompass
•
section FI – weather radar
•
section FN - radionavigation set
•
section FT – anti-collision system (if installed)
Every electric element used in the electric system of the aircraft is denoted by a symbol which is composed of a letter of the appropriate section and a serial number within the particular section (e.g. A 86). The bus bars, plug-and-socket connections and earthing connections are denoted by a symbol composed of letter "V" and a serial number (e.g. V 60). The used symbols of electric elements and conductor numbers are listed in the Wiring diagrams of individual section.
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BRIDGING AND EARTHING DESCRIPTION AND OPERATION 1. Purpose The normal function of radio-communications and other equipment is impaired by interference generated in various electrical devices such as electric motors, generators, relays, contactors, etc., and by interference caused as a result of accumulation of static electricity charges. In order to reduce the danger of defects are performed on the aircraft: •
conductive connections of individual parts of the aircraft between them and with the aircraft airframe;
•
built-in static electricity discharges (see section 023.60.00).
Methods of conductive connection performing: •
conductive connection by direct contacting
•
conductive connection by bridging. The method of bridging is chosen whenever the interconnected parts are in mutual movement or whenever for design reasons it proves impossible to use direct contacting
To maintenance it is necessary to take into consideration that on the most parts the surface finish has been made: •
by cadmium plating of steel parts
•
by eloxal coating at light metal alloys
Metal coatings surface protections are electrically conductive. In fixed joints (screws, rivets) of these parts sufficient electrical connection is obtained. Surface treated by eloxal coating, phosphatizing, varnishing, pickling, etc. are electrical non-conductive. The contact surfaces serving a conductive connection must have their contact areas thoroughly cleaned to metal gloss and degreased. After a connection was made the contact must be protected by varnish S 1005.
2. Technical data Permissible values of contact resistances between conductively interconnected parts are stated in the following table: Ser. No.
Measured place
Contact resistance (µΩ)
1.
Front cover-fuselage LH
B 018 566 N
600
2.
Front cover-fuselage RH
B 018 566 N
600
3.
Nose landing gear fairing RH-fuselage
7-200 ONL 6664.01
2000
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Type of bridging
Note
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Measured place
Contact resistance (µΩ)
4.
Nose landing gear fairing LH-fuselage
7-200 ONL 6664.01
2000
5.
Nose landing gear-rear fairing-fuselage
7-150 ONL 6664.01
2000
5a.
Nose landing gear-rear fairing-fuselage
7-150 ONL 6664.01
2000
5b.
Pull rod-countershaft
3-100 ONL 6664.01
2000
5c.
Pull rod-countershaft
3-100 ONL 6664.01
2000
5d.
Countershaft-fuselage
3-150 ONL 664.011
2000
5e.
Nose landing gear lock – end frame
bolted joint
600
5f.
Pull rod – countershaft
3-100 ONL 6664.01
2000
7-100 ONL 6664.01
2000
7-100 ONL 6664.01
2000
6.
7.
Cover RH of main landing gear – landing gear nacelle Cover RH of main landing gear – landing gear nacelle
8.
Cover – fittings LH+RH
3-100 ONL 6664.01
2000
9.
Fittings – pull rod LH+RH
3-150 ONL 6664.01
2000
10.
Pull rod – countershaft LH+RH
3-150 ONL 6664.01
2000
11.
Countershaft – pull rod LH+RH
3-150 ONL 6664.01
2000
12.
Countershaft – undercarriage LH+RH
3-150 ONL 6664.01
2000
13.
Landing gear main axis – fuselage LH+RH
7-150 ONL 6664.01
2000
14.
Rear cover LH fuselage
bolted joint
600
bolted joint
600
7-200 ONL 6664.01
2000
7-200 ONL 6664.01
2000
15. 16.
17.
Rear cover RH – fuselage Front luggage accommodation cover – fuselage LH Front luggage accommodation cover – fuselage RH
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Type of bridging
Note
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Measured place
Type of bridging
Contact resistance (µΩ)
18.
Fuselage – wing
XL 410.1201-07
600
19.
Wing suspensions – fuselage LH
bolted joint
2000
20.
Wing suspensions – fuselage RH
bolted joint
2000
21.
Edge rib. No. 31 – discharger LH, RH
bolted joint
600
22.
Aileron suspension – external wing LH, RH
3-200 ONL 6664.01
2000
23.
Aileron suspension – central – wing LH, RH
3-200 ONL 6664.01
2000
24.
Aileron suspension – internal – wing LH, RH
3-200 ONL 6664.01
2000
25.
-
-
-
26.
-
-
-
27.
Wing – external slot LH, RH
3-100 ONL 6664.01
2000
28.
External slot – flap LH, RH
3-100 ONL 6664.01
2000
29.
Wing – external slot LH, RH
3-100 ONL 6664.01
2000
30.
External slot – flaps LH, RH
3-100 ONL 6664.01
2000
31.
Wing - external slot LH, RH
3-100 ONL 6664.01
2000
32.
External slot – flap LH, RH
3-100 ONL 6664.01
2000
33.
Wing – internal slot LH, RH
3-100 ONL 6664.01
2000
34.
Internal slot – flap
3-100 ONL 6664.01
2000
35.
Fuselage – slot LH, RH
3-100 ONL 6664.01
2000
36.
Slot – flap LH, RH
3-100 ONL 6664.01
2000
37.
Rudder – discharger I, II
bolted joint
600
38.
Rear fuselage cover – discharger
bolted joint
600
EFFECTIVITY ALL
Note
If terminal fuel tanks will not be used.
024.60.00 Page: 3 Nov 1/11
MAINTENANCE MANUAL Ser. No. 39. 40. 41.
Measured place Rolling tab – wing LH, RH Between 1 and 2 bulkhead on the left (under battery) 6 bulkhead on the right side
Contact resistance (µΩ)
3-100 ONL 6664.01
600
Minus V 73 (riveted joint)
300
minus terminal V 211
300
42.
-
-
-
43.
-
-
-
44.
-
-
-
45.
-
-
-
1.5-100 ONL 6664.01
2000
B 030 774 L
600
B 030 774 P
600
-
-
46. 47.
48.
Aileron – balance tab of aileron Antenna cover VKV II – vertical stabilizer (if installed) Antenna cover VKV II – vertical stabilizer (if installed)
49.
-
50.
Dorsal fin – suspension
3-150 ONL 6664.01
2000
51.
Dorsal fin – suspension
3-150 ONL 6664.01
2000
52.
Rudder – dorsal fin
3-150 ONL 6664.01
2000
53.
Suspension - rudder
3-150 ONL 6664.01
2000
54.
Suspension – rudder
3-150 ONL 6664.01
2000
55.
Rudder - fuselage
3-150 ONL 6664.01
2000
56.
Elevator - suspension
3-100 ONL 6664.01
2000
57.
Elevator - suspension
3-100 ONL 6664.01
2000
58.
Elevator - suspension
3-100 ONL 6664.01
2000
EFFECTIVITY ALL
Type of bridging
Note
024.60.00 Page: 4 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
59.
Elevator - suspension
3-100 ONL 6664.01
2000
60.
Elevator - suspension
3-100 ONL 6664.01
2000
61.
Elevator - suspension
3-100 ONL 6664.01
2000
62.
Elevator – stabil.
3-100 ONL 6664.01
2000
63.
Elevator – stabil.
3-100 ONL 6664.01
2000
64.
Elevator - control
3-100 ONL 6664.01
2000
65.
Elevator - control
3-100 ONL 6664.01
2000
66.
Elevator - control
3-100 ONL 6664.01
2000
67.
Elevator - control
3-100 ONL 6664.01
2000
68.
Elevator - control
3-100 ONL 6664.01
2000
69.
Elevator - control
3-100 ONL 6664.01
2000
70.
Dorsal fin – fuselage
7-150 ONL 6664.01
600
71.
Tail plane – fuselage
7-150 ONL 6664.01
600
72.
-
-
-
73.
-
-
-
74.
Countershaft – airframe
see note
1500
75.
Countershaft arm – pull rod
3-200 ONL 6664.01
1500
76.
Pull rod – lever
3-200 ONL 6664.01
1500
77.
Lever – pull rod
3-200 ONL 6664.01
1500
EFFECTIVITY ALL
Note
It is meant between front joint of the console and of the countershaft washer or through the elevator.
024.60.00 Page: 5 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
78.
Pull rod - lever
79.
Lever - airframe
3-150 ONL 6664.01
1500
80.
Lever – pull rod
3-100 ONL 6664.01
1500
81.
Pull rod – lever
3-200 ONL 6664.01
1500
82.
Lever – pull rod
3-100 ONL 6664.01
1500
83.
Lever – pull rod
3-100 ONL 6664.01
1500
84.
Pull rod – lever
3-200 ONL 6664.01
1500
85.
Lever – airframe
3-150 ONL 6664.01
1500
86.
Lever – pull rod
3-100 ONL 6664.01
1500
87.
Pull rod – double arm lever
3-150 ONL 6664.01
1500
88.
Double arm lever – pull rod
3-100 ONL 6664.01
1500
89.
Pull rod – double arm lever
3-150 ONL 6664.01
1500
90.
Double arm lever – pull rod
3-150 ONL 6664.01
1500
91.
Pull rod – control block lever
3-100 ONL 6664.01
1500
92.
Control block – airframe
3-150 ONL 6664.01
1500
93.
-
-
-
94.
Elevator balance tab LH, RH – pull rod LH, RH
3-200 ONL 6664.01
1500
95.
Elevator balance tab control
3-200 ONL 6664.01
1500
96.
Cables mutually
3-200 ONL 6664.01
1500
97.
-
-
-
98.
-
-
-
EFFECTIVITY ALL
Type of bridging 3-200 ONL 6664.01
Contact resistance (µΩ)
Note
1500
Rear part of fuselage
vertical channel
control block
024.60.00 Page: 6 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
99.
-
-
-
100.
-
-
-
101.
Wing LH, RH – pull rod LH, RH
3-150 ONL 6664.01
1500
102.
Pull rod – double arm lever
3-150 ONL 6664.01
1500
103.
Double arm lever – airframe
3-100 ONL 6664.01
1500
104.
Double arm lever – pull rod
3-200 ONL 6664.01
1500
105.
Pull rod – countershaft LH-RH
106.
Countershaft – mainframe
3-150 ONL 6664.01 3-150 ONL 6664.01
107.
Countershaft – pull rod
3-200 ONL 6664.01
1500
108.
Pull rod RH countershaft
3-150 ONL 6664.01
1500
109.
Pull rod LH – countershaft
3-150 ONL 6664.01
1500
110.
Front pull rod countershaft
3-200 ONL 6664.01
1500
111.
Countershaft mainframe
3-150 ONL 6664.01
1500
112.
Pull rod - lever
3-200 ONL 6664.01
1500
113.
Pull rod - lever
3-100 ONL 6664.01
1500
114.
Lever – airframe
3-150 ONL 6664.01
1500
115.
Pull rod – double arm lever
3-150 ONL 6664.01
1500
116.
Double arm lever – vertical pull rod
3-150 ONL 6664.01
1500
117.
Vertical pull rod – double arm lever
3-150 ONL 6664.01
1500
118.
Double arm lever – pull rod
3-150 ONL 6664.01
1500
119.
Pull rod – double arm lever
3-150 ONL 6664.01
1500
EFFECTIVITY ALL
Note
1500 1500
024.60.00 Page: 7 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
120.
Double arm lever – control block lever
3-100 ONL 6664.01
1500
121.
Lever – interconnection pull rod
3-150 ONL 6664.01
1500
122.
Interconnection pull rod – lever
3-150 ONL 6664.01
1500
123.
Control block - airframe
3-150 ONL 6664.01
124.
-
-
-
125.
-
-
-
126.
-
-
-
127.
Electromechanical strut – airframe
128.
Pull rod – aileron
129.
-
130.
see note
1500
3-150 ONL 6664.01
1500
-
-
Segment – airframe
various
1500
131.
Rudder cable – airframe LH+RH
various
1500
132.
Turnbuckle of ruder cables – mutually
various
1500
133.
Segment – airframe
various
1500
134.
Segment – pull rod LH – RH
various
1500
135.
Three-armed lever LH+RH airframe
various
1500
various
1500
various
1500
various
1500
various
1500
136. 137. 138. 139.
Pull rod LH+RH – three –armed lever Three-armed lever LH+RH – pull rod LH+RH Pull rod LH+RH – pedal RH Pull rod LH+RH – pedal RH
EFFECTIVITY ALL
Note
Connection with the frame is performed through minus pin – ZZ connections
024.60.00 Page: 8 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
140.
Breaking cylinder LH, RH – pedal LH, RH
various
1500
141.
-
-
-
142.
-
-
-
143.
-
-
-
144.
-
-
-
145.
-
-
-
146.
Rudder – tab
3-150 ONL 6664.01
1500
147.
Tab – pull rod
3-150 ONL 6664.01
1500
148.
Pull rod – motor arm
3-150 ONL 6664.01
1500
149.
Electromechanical strut – console
see note (up to the st 21 series)
1500
Note
Connection with the frame is performed through minus pin – ZZ connection
3-200 ONL 6669.01 (from nd the 22 series) 3-100 ONL 6664.01
1500
see note
1500
-
-
-
153.
-
-
-
154.
-
-
-
155.
Pull rod from oper. Cylinder of flap – three – armed
3-200 ONL 6664.01
1500
156.
Three – armed lever – 1 – airframe
3-150 ONL 6664.01
1500
157.
Three – armed lever I. – pull rod
3-200 ONL 6664.01
1500
150.
Console-airframe
151.
Electromechanical strut – rudder
152.
EFFECTIVITY ALL
024.60.00 Page: 9 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
158.
Pull rod – flap lever
3-200 ONL 6664.01
1500
159.
Three – armed lever I. – pull rod
3-200 ONL 6664.01
1500
160.
Pull rod – three – armed lever II.
3-150 ONL 6664.01
1500
161.
Three-armed lever II. – pull rod
3-150 ONL 6664.01
1500
162.
Pull rod – flap rod
3-200 ONL 6664.01
1500
163.
-
-
-
164.
-
-
-
165.
-
-
-
166.
Interceptor LH, RH wing
3-150 ONL 6664.01
1500
167.
Lever – console
3-150 ONL 6664.01
1500
168.
Console – airframe
3-150 ONL 6664.01
1500
169.
Lever – pull rod LH, RH
1,5x200 ONL 6664.01
1500
170.
Pull rod – lever
1.5x200 ONL 6664.01
1500
171.
Lever – pull rod
3-150 ONL 6664.01
1500
172.
Lever – airframe
3-150 ONL 6664.01
1500
173.
Pull rod – lever
3-150 ONL 6664.01
1500
174.
Lever – pull rod
3-150 ONL 6664.01
1500
175.
Lever – airframe
3-150 ONL 6664.01
1500
176.
Pull rod – bent lever
3-150 ONL 6664.01
1500
177.
Bent lever – airframe
3-150 ONL 6664.01
1500
178.
Bent lever - interceptor
3-150 ONL 6664.01
1500
EFFECTIVITY ALL
Note
024.60.00 Page: 10 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
179.
-
-
-
180.
-
-
-
181.
-
-
-
182.
Double arm lever – pull rod
3-150 ONL 6664.01
1500
183.
Pull rod – console
3-150 ONL 6664.01
1500
184.
Pull rod – rolling tab lever
3-150 ONL 6664.01
1500
185.
-
-
-
186.
Engine bed – fireproof bulkhead LH+RH
7-250 ONL 6664.01
600
187.
Engine bed – upper strut (2x)
7-150 ONL 6664.01
600
188.
Engine bed – lower strut (2x)
7-150 ONL 6664.01
600
189.
Lower strut – II. fireproof bulkhead (2x)
190.
Lower strut – III. fireproof bulkhead (2x)
7-150 ONL 6664.01 7-150 ONL 6664.01
192. 193.
Engine nacelle – fireproof bulkhead LH RH Engine –circular engine bed
ALL
600
600
3-150 ONL 6664.01
2000
-
600
L410.6400-66
2000
L410M.6400-27
2000
194.
Pulley countershaft airframe
195.
Console – fire wall
196.
Lever – pull rod
1.5-150 ONL 6664.01
2000
197.
Pull rod – pull rod
1.5-150 ONL 6664.01
2000
198.
Console – lever
1.5-150 ONL 6664.01
2000
199.
Lever – engine control pull rods
1.5-100 ONL 6664.01
2000
EFFECTIVITY
Note
2+2
024.60.00 Page: 11 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
199a.
Airframe – cables
1.5-150 ONL 6664.01
2000
200.
Terminal tank – wing
B 560 641 N
2000
201.
Terminal fuel tank – discharger
B 560 627 N
600
202.
Terminal fuel tank – airframe
B 560 667 N
600
203.
Additional fuel tank (cap) - airframe
B 560 554 N
600
204.
Additional fuel tank (cap) - airframe
3-150 ONL 6664.01
600
205.
Additional fuel tank interconnection – inside
3-200 ONL 6664.01
600
205a.
Fuel pump – airframe
3-150 ONL 6664.01
600
206.
Venting pipe – airframe
3-150 ONL 6664.01
600
207.
External fuel tank cap – airframe
bolted joint
600
208.
External fuel tank cap – airframe
bolted joint
600
209.
Fuel tank interconnection external – central
3-200 ONL 6664.01
600
210.
Central fuel tank cap (filler cap) – airframe
B 560 554 N
600
211.
Central fuel tank cap (transmitter) airframe
bolted joint
600
212.
Header fuel tank cap (filler cap) – airframe
B 560 554 N
600
213.
Repump pipe – airframe
3-150 ONL 6664.01
600
214.
Repump pipe – airframe
215.
Repump pipe – airframe
3-150 ONL 6664.01 3-150 ONL 6664.01
216.
Sprocket with lever – pull rod
3-100 ONL 6664.01
1500
217.
Pull rod – double arm lever
3-100 ONL 6664.01
1500
EFFECTIVITY ALL
Note
In case of terminal fuel tank assembly only.
600 600 metal to metal framing
024.60.00 Page: 12 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
218.
Double arm lever – pull rod
1.5-150 ONL 6664.01
1500
219.
Pull rod – lever
3-100 ONL 6664.01
1500
220.
Lever – pull rod
3-100 ONL 6664.01
1500
221.
Pull rod – segment
3-150 ONL 6664.01
1500
222.
Spring rod – threearmed lever
3-150 ONL 6664.01
1500
223.
-
-
-
224.
-
-
-
225.
Fuel tank – undercarriage nacelle
1.5-100 ONL 6664.01
2000
226.
Pump – airframe
1.5-100 ONL 664.03
2000
227.
T part – airframe
1.5-100 ONL 6664.03
2000
228.
-
-
-
229.
-
-
-
230.
Main hydraulic tank – airframe
bolted joint
600
231.
Emergency hydraulic tank – airframe
8-100 ONL 6664.01
600
232.
Instrument panel (right) – fuselage
3-100 ONL 6664.01
2000
233.
Instrument panel (central) – fuselage
3-100 ONL 6664.01
2000
234.
Instrument panel (left) – fuselage
3-100 ONL 6664.01
2000
235.
Instrument panel – airframe
cable 2 CSN 02 4320.43
1500
236.
Front panel – fuselage LH, RH
1.5-150 ONL 6664.01
2000
237.
Heating distribution – fuselage LH, RH
238.
Transponder’s control box
1.5-100 ONL 6664.01 1.5-100 ONL 6664.03 1.5-100 ONL
EFFECTIVITY ALL
Note
600 1500
024.60.00 Page: 13 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
Note
6669.03
239.
5 frame – control deicing box
240.
bolted joint
1500
Overhead panel – fuselage
1.5-100 ONL 6664.01
600
241.
Control panel (left and right) – airframe
1.5-100 ONL 6664.02
2000
242.
De-icing instruments frame – airframe
bolted joint
600
243.
Frame – double valve
bolted joint
600
244.
Frame – valve
bolted joint
600
245.
Frame – air pressure reducing valve
bolted joint
600
246.
Frame – pressure transmitter
bolted joint
2000
247.
Deicing pipes – airframe LH, RH
1.5-100 ONL 6664.03
2000
248.
Accumulator – bulkhead (9, 17)
minus pole
600
249.
Communicating aerial VHF I – fuselage
bolted joint
600
bolted joint
600
bolted joint
600
bolted joint
600
bolted joint
600
bolted joint
600
250. 251.
252.
253.
254.
Communicating aerial VHF II – fuselage Rear antennas SRO 2L – fuselage (2 board) (if installed) Rear antennas SRO 2P – fuselage (3 board) (if installed) Front antennas SRO 2L – fuselage (2 band) (if installed) Front antennas SRO 2 P – fuselage (3 board) (if installed)
255.
Aerial GS – fuselage
bolted joint
600
256.
Aerial MKR – fuselage
bolted joint
600
257.
Aerial ADF – fuselage
bolted joint
600
EFFECTIVITY ALL
024.60.00 Page: 14 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
258.
Antenna frame ARK –II – fuselage (if installed)
bolted joint
600
259.
Heading aerial ILS – fin LH+RH
bolted joint
600
260.
Aerials KRA 405 – fuselage LH+RH
bolted joint
600
261.
Aerial KT 79 – fuselage
bolted joint
600
262.
-
-
-
263.
Receiver-transmitter (if installed)
bolted joint
2000
264.
Receiver ADF I
bolted joint
2000
Unit – frame Frame - airframe
265.
Receiver ADF II
bolted joint
2000
Unit – frame Frame - airframe
266.
Generator LH – fuselage
bolted joint
300
267.
Generator RH – fuselage
bolted joint
300
268.
Battery – airframe
bolted joint
300
269.
Contactor B12 – airframe
bolted joint
600
Right side
270.
Contactor B11 – airframe
bolted joint
600
Left side
271.
Recorder K3 – fuselage
bolted joint
600
272.
Interrupter D 102 – fuselage
bolted joint
600
Right side
273.
Interrupter D 101 – fuselage
bolted joint
600
Left side
274.
-
-
-
275.
Regulator A 3(A 4) – airframe
bolted joint
600
276.
Time relay B 17 (B 18) – airframe
bolted joint
600
277.
Contactor A 13 – airframe
bolted joint
600
278.
-
-
-
EFFECTIVITY ALL
Note
024.60.00 Page: 15 Nov 1/11
MAINTENANCE MANUAL Ser. No. 279. 280.
Measured place IELU M 181 – M 182/+ derivative element airframe Inverters LUN 2460 – airframe
281.
Inverter LUN 2456.02-8 – airframe
282.
Inverters LUN 2450 – airframe
283.
284.
FB 39 – non-directional antenna coupling element – ground (if installed) FB 9 – non-directional antenna coupling element – ground (if installed)
Contact resistance (µΩ)
Bolted joint
600
bolted joint
600
1.5-100 ONL 6664.01
2000
bolted joint
600
bolted joint
600
bolted joint
600
285.
-
-
-
286.
-
-
-
287.
-
-
-
288.
Entry door – fuselage
7-150 ONL 6664.01
2000
289.
Cargo door – fuselage
7-150 ONL 6664.01
2000
290.
Front door – fuselage
7-150 ONL 6664.01
2000
291.
1 bulkhead – 27 bulkhead
292.
Flash beacon - upper frame - lower frame
293.
Between most distant wing places (bulkhead 31 LH, 31 RH)
294.
Beam – airframe
295.
Aircraft earthing - earth
296.
Regulator A 253, A 254 – beam
EFFECTIVITY ALL
Type of bridging
Note
5000 bolted joint bolted joint
600 600
5000 3-100 ONL 6664.01 Landing gear conductive connection with earth bolted joint
600
max.7M
Measure with megaohmmeter 500V
600
024.60.00 Page: 16 Nov 1/11
MAINTENANCE MANUAL Ser. No.
Measured place
Type of bridging
Contact resistance (µΩ)
297.
Distribution box A 257 – beam
bolted joint
600
298.
Interrupter D 101, D 102 – fuselage
bolted joint
600
299.
Separation box K 4 – fuselage
bolted joint
600
300.
Input block of recorder K 1 – fuselage
Bridging delivered with instrument
2000
301.
Alternator A 252 (LH+RH) – fuselage
bolted joint
900
302.
Light source C 48 – fuselage
bolted joint
600
Note
NOTE: Instead of bridging according to ONL 6664.01, ONL 6664.02 and ONL 6664.03 it is possible to use the bridging according to ONL 6669.01, ONL 6669.02 and ONL 6669.03 (the section and length of the bridging is not modified).
EFFECTIVITY ALL
024.60.00 Page: 17 Nov 1/11
FIG.1
EFFECTIVITY
ALL
024.60.00
Page: 18 Nov 1/11
Legend to Fig. – see on the previous pages (1÷17) RESISTANCES
MEASURED PLACE LOCATION DIAGRAM OF CONTACT RESISTANCES
MAINTENANCE MANUAL
FIG.2
EFFECTIVITY
ALL
Legend to Fig. – see on the previous pages (1÷17) RESISTANCES
MEASURED PLACE LOCATION DIAGRAM OF CONTACT RESISTANCES
MAINTENANCE MANUAL
024.60.00
Page: 19 Nov 1/11
FIG.3
EFFECTIVITY
ALL
Legend to Fig. – see on the previous pages (1÷17) RESISTANCES
MEASURED PLACE LOCATION DIAGRAM OF CONTACT RESISTANCES
MAINTENANCE MANUAL
024.60.00
Page: 20 Nov 1/11
FIG.4
EFFECTIVITY
ALL
Legend to Fig. – see on the previous pages (1÷17) RESISTANCES
MEASURED PLACE LOCATION DIAGRAM OF CONTACT RESISTANCES
MAINTENANCE MANUAL
024.60.00
Page: 21 Nov 1/11
MAINTENANCE MANUAL
INTENTIONALLY LEFT BLANK
EFFECTIVITY ALL
024.60.00 Page: 22 Nov 1/11
CHAPTER
EQUIPMENT / FURNISHINGS
MAINTENANCE MANUAL
CHAPTER 25 EQUIPMENT / FURNISHINGS LIST OF EFFECTIVE PAGES Chapter Section Subject
Page
Date
Title page
-
-
List of Effective Pages
1
Mar 30/16
2
Page
Date
025.10.00
1
Nov 1/11
Description and Operation
2
Nov 1/11
Mar 30/16
3
Nov 1/11
3
Mar 30/16
4
May 30/14
4
Mar 30/16
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CHAPTER 25 EQUIPMENT / FURNISHING RECORD OF REVISIONS Rev. No.
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025-RECORD OF TEM. REVISIONS Page: 2 Nov 1/11
MAINTENANCE MANUAL CHAPTER 25 EQUIPMENT / FURNISHINGS CONTENTS Subject
Chapter, Section, Subject
Page
Effectivity
GENERAL 025.00.00 Description and Operation General Maintenance Practices General Servicing Inspection of furnishing and of emergency and rescue equipment Check of the emergency equipment Inspection of protective covers and safety belts of pilots’ passengers’ seats and foldable serving plates Check of the reliability of fixing of crew and passenger seats to the floor of the aircraft Inspection of passenger and flight compartment upholstery Cleaning of passenger and flight compartment Inspection of the safety belts of crew and passenger seats
1 1 1 201 201 301 301
ALL
FLIGHT COMPARTMENT Description and Operation General Navigator’s table Spare fuse box DV 3 FAN Flight compartment upholstery Flight documentation case Map spring clips EFB –iPad holders Servicing Inspection of the navigator’s table and its tilting mechanism Inspection of the spare fuse box (if installed) Removal / Installation Removal and installation of the navigator’s table (if installed)
1 1 1 2 2 5 5 5 6 8 301 301
025.10.00
DV-3 FAN 025.10.01 Description and Operation Purpose Technical data Servicing Check of DV - 3 fan brush height and inspection of its collector-brush assembly Removal / Installation DV - 3 fan removal and installation
EFFECTIVITY: ALL
301 302 303 303 304 307 ALL
301 401 401 1 1 1 1 301 301
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401 401
025-CONTENTS Page: 1 Mar 30/16
MAINTENANCE MANUAL Subject
Chapter, Section, Subject
Page
Effectivity
PILOTS’ SEATS 025.11.00 Description and Operation General Fault Isolation Removal / installation Removal and installation of pilots’ seats and elbow rests
1 1 1 101 401 401
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SAFETY BELTS AMSAFE P/N 504388 SERIES Description and Operation Purpose Operation Fault Isolation Task - Testing on Aircraft Procedure for Fault Isolation Cleaning / Painting Cleaning the safety belts
025.11.01
1 1 1 1 101 101 103 701 701
ALL
CURTAINS Description and Operation General Removal / Installation Removal and installation of curtains
025.12.00
1 1 1 401 401
ALL
1 1 1 1
ALL
PASSENGER COMPARTMENT 025.20.00 Description and Operation General Passenger transport version – 19 seats (basic version) Passenger transport version – 17 seats Passenger transport version – 11 seats Passenger executive version – 8 seats Flying ambulance Parachute jumping Cargo version Servicing Wounded person loading (if flying ambulance is installed) Removal / Installation Removal and installation equipment for wounded persons (if flying ambulance is installed) Removal and installation of the parachute seats (three-seated benches) (if parachute jumping is installed) Removal and installation of the anchor cables (if parachute jumping is installed) Removal and installation of the tables of passenger executive (VIP) version (if installed) Removal and installation of the salon seats of passenger executive (VIP) version (if installed)
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404 405 408
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PASSENGER’S SEATS Description and Operation General Removal / Installation Removal and installation of single and double passenger seat sets
025.21.00
1 1 1 401 401
ALL
SAFETY BELTS AMSAFE P/N 2019 SERIES Description and Operation Purpose Operation Fault Isolation Task - Testing on Aircraft Procedure for Fault Isolation Cleaning / Painting Cleaning the safety belts
025.21.01
1 1 1 1 101 101 102 701 701
ALL
1
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PARTITION BETWEEN FLIGHT AND PASSENGER 025.22.00 COMPARTMENT (if installed) Description and Operation General Servicing Inspection of the doors of the partition between flight and passenger compartment (if installed)
1 1 301 301
PASSENGER AND FLIGHT COMPARTMENT UPHOLSTERY Description and Operation General
025.23.00
1 1 1
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ADDITIONAL EQUIPMENT Description and Operation Head wear shelf (rack) (if installed) Newspaper and magazine holder (if installed) Foldable serving plate (if installed) LAVATORIES Description and Operation General Servicing Inspection of the equipment of the toilet section
025.24.00
1 1 1 1 1 1 1 1 301 301
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CARGO COMPARTMENTS Description and Operation General
025.50.00
1 1 1
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CARGO COMPARTMENTS IN PASSENGER VERSION Description and Operation General Servicing Inspection of the front and rear baggage compartment structure
025.51.00
1 1 1 301 301
ALL
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ALL ALL
025-CONTENTS Page: 3 Mar 30/16
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CARGO COMPARTMENTS IN CARGO VERSION Description and Operation Cargo version Servicing Inspection of the polyamide net Inspection of the fastening belts Inspection of cargo version equipment Removal / Installation Cargo version equipment installation Cargo version equipment removal Installation and removal of the seat for the person accompanying cargo
025.52.00
1 1 1 301 301 301 301 401 401 402 404
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EMERGENCY EQUIPMENT Description and Operation General List of components First-aid kit installation in the passenger compartment First-aid kit installation in the flight compartment Emergency axe Crew call signalling (see fig. 2) Life rafts, emergency packages and life jackets Emergency locator transmitter (ELT) Servicing Inspection of emergency equipment Check of the operation of push-buttons for calling the crew Removal / Installation Removal and installation of life jackets, life rafts and emergency packages
025.60.00
1 1 1 2 2
ALL
ASZH-63P LIFE JACKET (if installed) Description and Operation General
025.60.01
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SP-12 LIFE RAFT (if installed) Description and Operation General
025.60.02
1 1 1
ALL
NAZ-7 EMERGENCY PACKAGE (if installed) Description and Operation General
025.60.03
1 1 1
ALL
ELT-10 EMERGENCY LOCATOR TRANSMITTER (if installed) Description and Operation Purpose Technical data Operation Servicing Check of the battery pack / Battery pack replacement in the ELT-10 Emergency Locator Transmitter Check of the operation of ELT-10 Emergency Locator Transmitter
025.60.04
1 1 1 1 2 301 301
ALL
EFFECTIVITY: ALL
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3 3 4 5 5 301 301 303 401 401
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401 401
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POINTER 3000 (POINTER 200, POINTER 3000-10) EMERGENCY LOCATOR TRANSMITTER (if installed) Description and Operation Purpose Technical data Operation Servicing Check of the battery pack / Battery pack replacement in the POINTER 3000 Emergency Locator Transmitter Check of the operation of POINTER 3000 Emergency Locator Transmitter Removal / Installation POINTER 3000 disassembly and re-assembly
025.60.05
1
ALL
ARTEX C 406 - 2 EMERGENCY LOCATOR TRANSMITTER (if installed) Description and Operation General List of components Operation Servicing Check of the battery pack / Battery pack replacement in the ELT C 406-2 Emergency Locator Transmitter Check of the operation of C 406-2 Emergency Locator Transmitter
025.60.06
Removal / Installation ELT-10 disassembly and re-assembly
1 1 1 2 301 301
303 401 401
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ALL
1 1 1 1 301 301
302
AMERI-KING AK-451 EMERGENCY LOCATOR 025.60.07 TRANSMITTER (if installed) Description and Operation General List of components Operation Servicing Check of the battery pack / Battery pack replacement in the ELT AK-451 Emergency Locator Transmitter Check of the operation of AK-451 Emergency Locator Transmitter ARM-406 AS1 PORTABLE EMERGENCY LOCATOR TRANSMITTER (if installed) Description and Operation
1
025.60.08
1
ALL
1 1 1 1 301 301 302 1
ALL
1
025-CONTENTS Page: 5 Mar 30/16
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KANNAD 406 AP PORTABLE EMERGENCY LOCATOR TRANSMITTER (if installed) Description and Operation General List of components Operation Controls Working mode information Battery pack Servicing Check of the battery pack / Battery pack replacement in the KANNAD 406 AP Emergency Locator Transmitter Check of the operation of KANNAD 406 AP Emergency Locator Transmitter
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1 1 1 2 3 4 5 301 301
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025-CONTENTS Page: 6 Dec 10/14
MAINTENANCE MANUAL
GENERAL DESCRIPTION AND OPERATION 1. General In the aircraft fuselage appropriately furnished compartments are provided for the crew, passengers and cargo (baggage), as well as for a toilet. Internal equipment includes also emergency and rescue equipment: •
first-aid kits, an axe, a crew call signalling, life jackets (if installed), life rafts (if installed), emergency packages (if installed) and Emergency Locator Transmitter or emergency transceiver (if installed).
Fasteners and storing space are provided for location of life jackets, life rafts and emergency packages.
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GENERAL MAINTENANCE PRACTICES 1. General A.
B.
The components removed from the aircraft for laboratory test must be inspected for: •
visible mechanical damage of the body
•
corrosion of plug-and-socket connectors, terminals, pushbuttons
•
deformation of plug-and-socket connector pins
•
deposits of dirt
•
evidence of fluid leaks
When removing a unit (a component) from the aircraft (for laboratory test or replacement), its place of installation, connector or pipe mating parts must be inspected for: •
mechanical damage (cracks) of the place of installation
•
wear of the attachment holes
•
corrosion and deformation of plug-and-socket connector pins
•
dents
•
ruptures
•
deformation of pipe connecting parts
•
damage of connector and pipe union nut threads
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MAINTENANCE MANUAL GENERAL SERVICING 1. Inspection of furnishings and of emergency and rescue equipment A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.A Routine, Periodical
E.
Procedures (1) Inspection of seat covers. The covers must be clean, non-torn and non-ripped. (2) Check for completeness of fastening belts. The number of safty belts must correspond to the number of seats. (3) Check for life jacket completeness. The number of life jackets must correspond to the number of seats. (4) Inspect and check passenger seat covers, safety belts and life jackets for completeness and for compliance with the requirements of para. 1, 2 and 3.
2. Check of the emergency equipment A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.B Routine
E.
Procedures (1) Check the life jackets in the passenger compartment (if installed). Check that each seat in the passenger compartment is provided with a life jacket. At the same time check proper condition of the life jacket cover. The life jackets are placed in the pockets below the seats. Supplement missing life jackets; replace damaged jackets by new ones. (2) Check that each seat in the flight compartment is provided with a life jacket. At the same time check proper condition of the life jacket cover. The life jackets are placed in the pockets of the back rest cover (on the rear side). Supplement missing life jackets, replace damaged jackets by new ones.
EFFECTIVITY ALL
025.00.00 Page: 301 May 30/14
MAINTENANCE MANUAL (3) Check the first-aid kits for correct condition and fixing. The first-aid kits are placed in the flight compartment and in passenger compartment. (4) Check the axe for correct condition and fixing. The axe is placed in the flight compartment behind the pilot’s seat on the wall of the partition between the flight and passenger compartments. Replace the damaged axe fastening straps by new ones.
3. Inspection of protective covers and safety belts of pilots, passengers seats and foldable serving plates A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.C Periodical
E.
Procedures (1) Check the condition of the seat covers and safety belts in the flight compartment. Check the function and condition of the safety belt locks. (2) Check the condition of the seat covers in the passenger compartment. Check condition of the safety belts as well as the condition and functioning of the safety belt locks. Check conditions and function of the foldable serving plates located in the passenger seats at the partition between the flight and passenger compartment as well as the foldable serving plates located at the fuselage sides at the first row of passenger seats. (3) Defects not allowed: damaged covers of passengers’ and pilots’ seats, damaged safety belts or their parts, damaged hinges and damaged safety equipment for foldable serving plates, deformed or otherwise damaged foldable serving plates (if installed).
EFFECTIVITY ALL
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4. Check of the reliability of fixing of crew and passenger seats to the floor of the aircraft A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.D Periodical
E.
Procedures (1) In the flight compartment, check the condition and functioning of the adjusting mechanism of the pilots’ seats. Check the condition of the pins by means of which the seats are attached to the floor. Replace damaged parts by new ones. (2) In the passenger compartment, inspect the brackets of the seats and check their condition in the area of attachment to the floor. Replace damaged parts by new ones. (3) Defects not allowed: damaged or deformed adjusting mechanism of the pilots’ seats, loosened elements and parts fixing the seats to the corresponding floor elements in the flight or passenger compartment.
5. Inspection of passenger and flight compartment upholstery A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.E Periodical
E.
Procedures (1) The soiled spots on the lining should be cleaned with detergent dissolved in warm water. WARNING:
WHEN CLEANING UPHOLSTERY, DO NOT USE EITHER PETROL OR ORGANIC SOLVENTS.
(2) Check the flight and passenger compartment upholstery for damage. Glue on unstuck margins of the upholstery using the 6286 (K88) rubber adhesive. Replace damaged parts of upholstery by new ones. (3) Defects not allowed: soiled, torn or otherwise damaged upholstery inside the fuselage.
EFFECTIVITY ALL
025.00.00 Page: 303 May 30/14
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6. Cleaning of passenger and flight compartment A.
Fixture, Test and Support Equipment
Vacuum cleaner with an extension cord (of max. 800 W power demand) Carpet brush
B.
Materials
Solution acc. to para (2) Wiping cloth Detergent (solution) Mixture acc. to para (2) Sponge Tetrachlorine or trichloroethylene
C. Tools
Not applicable
D. Referenced information
025.00.00.F Periodical
E.
Procedures (1) Prepare an 800 W vacuum cleaner with a suitable extension cord. (2) Prepare the following solution for carpet cleaning: 1 table spoon of detergent 1 liter of water 1 table spoon of 8 % vinegar For cleaning of spots of unknown origin use the solution consisting of a mixture of most commonly used cleaning agents, prepared as follows: 100 g of petrol 25 g of alcohol 10 g of ether 5 g of ammonia NOTE:
Shake the solution before use thoroughly.
(3) When using inflammable substances (alcohol, petrol, acetone) or substances with harmful evaporations (tetrachlorine, trichlorine, ammonia etc.) do not work with open fire, do not smoke and provide effective ventilation of the space (open door, open direct vision panels). (4) Cleaning of passenger and flight compartments (seats, upholstery, carpets, side-table). Defects not allowed: mud, dust, damaged fixing elements of removable upholstering panels, occurrence of static electricity. (5) Clean the carpets as follows: EFFECTIVITY ALL
025.00.00 Page: 304 Nov 1/11
MAINTENANCE MANUAL (a) Remove all dust from the whole surface of the floor covering using normal mechanical means (vacuum cleaner or carpet brush). (b) Apply wet method to clean more soiled areas using one of the above-mentioned solutions (see paragraph (2) of this Work procedure). (c) Remove the different spots by means of one of the methods given in the following table. Kind of soiling
Method of removal
Spirits (beer, wine, distilled liquors)
Remove excessive moisture, wash with lukewarm water or with detergent solution, remove possible remaining spots with citric acid solution or with pure lemon squash, wash with lukewarm water again.
Asphalt
Soften the spot with turpentine oil and wipe with tetrachlorine, petrol or with a spot cleaning agent. At the end wash the spot with lukewarm detergent solution.
Mud
Remove dry pieces mechanically, wipe the rest by a thinned detergent solution. At the end brush the place slightly.
Oil varnish, incl. drying oil
Soften the spot with turpentine oil, suck it up and wipe out with tetrachlorine or with a spot cleaning agent
Synthetic varnish, lacquers
Soften the spot with turpentine oil, nitrocellulose thinner or with acetone, suck it up with a dry rag and wipe out with tetrachlorine or spot cleaning agent
Ball pen
Wipe slightly off with a clean rag or sponge wetted in alcohol until the spot disappears. Permanently change the rag (sponge)! At the end wipe the spot with a thinned detergent solution.
Chocolate
Remove the deposits of chocolate matter mechanically. Then wipe the spot with thinned detergent solution and at the end with a spot cleaning agent or tetrachlorine. After drying brush the spot off.
Blood
Wash the spot immediately with cold water (with possible addition of ammonia). Old, dried spots must be softened at first and then wiped with cold water. After drying brush them off. It is also possible to use a bio detergent. Apply the detergent to the spot, let it act and then wipe the spot with cold water. NOTE: When cleaning, use cold water only!
Nail-varnish
Clean the spot with acetone
Grease (oil)
Clean the spot with grease solvents (tetrachlorine or trichlorethylene, petrol or spot cleaning agent) until it disappears completely. Then wipe it with a thinned detergent solution.
Urine
Clean it with a thinned vinegar solution, then with a thinned detergent solution and at the end with water.
Fruit, fruit juices
First wipe the spot with cold water, then with a cold solution of ammonia or with a solution of lemon acid (lemon squash) and at the end with cold water.
(d) When cleaning the spots, adhere to the following principles: •
Clean the spots as soon as possible after their occurrence. Obsolete spots are removable only with difficulties. Repeat the recommended cleaning procedure several times.
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Hard and semi-hard dirt is to be removed by scraping off at first (by blunt knife side, by a spoon etc.). Suck up excessive moisture with a dry cloth (sponge, filtering paper) at first.
•
The applied cleaning agent should be left to react for a certain time (a few minutes).
•
If several cleaning agents are used, then prior to using the next agent the preceding one must be thoroughly washed off and wiped with water or with a detergent solution.
Suck up excessive moisture and only then use the next cleaning agent. Do not rub the spots when cleaning, wipe them only slightly away, proceeding always from the margins of the spot towards its center in order not to enlarge the spot unnecessarily. (6) Check the attachment of all removable upholstery panels. Check the upholstery for cleanliness. Repair or replace defective fixing elements of the removable upholstery panels. Clean the removable upholstery panels and other parts of cabin lining with recommended agents (e.g. KORDOVAN or a solution of 95 % of water and 5 % of the PROGRESS liquid). It is not permitted to clean the removable upholstery panels and other parts of cabin lining with technical petrol or other organic solvents. (7) Clean the fabric seat upholstery with shampoo or with one of the above-mentioned spot cleaning agents - see paragraph (2). (8) Dispatch the removable seat covers for dry-cleaning. (9) If static electricity occurs on the seat covers or the carpet, either use a freshening agent when rinsing the covers after the wash, or spray the covers and the carpet with an antistatic agent. (10) Wipe both sides of the side-table with a clean wet cloth. (11) To clean seat covered with finished leather use appropriate type of cleaning wipes (if not available use a cloth soaked in a mild soap/water solution) and wring it out until damp. Do not use detergent solution. Apply the wipe (or the soaked cloth) to the surface of the leather in a light circular motion, turning the wipe (or the soaked cloth) regularly. Avoid aggressive with a damp cloth rinsed in clean warm water. Allow to dry and then light polish using a clean, dry soft cloth. Do not over clean leather really does not take much of looking after. Do not use wax/spray polished – wax polishes and furniture spray often contain silicone which will, in time, produce an unpleasant sticky feel to the leather. (11) Remove the vacuum cleaner with the extension cord.
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7. Inspection of the safety belts of crew and passenger seats A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.00.00.G Periodical
E.
Procedures The following procedure is written for a AmSafe Safety belts (see section 025.11.01 and 025.21.01). (1) Task: Use visual checks to find damaged or worn parts and parts that show signs of near failure. If you find and correct possible conditions of failure, you can prevent failures in the aircraft and make the equipment more reliable. (2) General (a) Make sure that the restraint system is clean and does not contain: dirt, oil or grease, or other unwanted particles of substances. (b) Make sure all parts are satisfactorily attached. (3) Webbing NOTE:
Slight wear of the webbing is permitted. However, excessive web wear that has progressed to cut or worn edges must be replaced, as described below.
(a) Examine webbing for cut or worn edges, damaged stitching, broken fabric threads, tears, excessive chafe marks, excessive wear or excessive fusing. (b) Replace webbing if any of the following are observed: A limited amount of “frayed” webbing will retain sufficient strength necessary to meet the required strength. Frayed webbing is defined as broken filaments from either the warp (longitudinal) yarns or the filler (transverse) yarns. The number of broken filaments should not be sufficient to obscure the identity of any yarn when viewed from a distance of about 8 inches. Any web that is cut or torn on the edge should be replaced. The amount of fray should be limited to an amount that is less than 10% of the width of the webbing and not to exceed 8 inches in length. Webbing with more than 15 broken yarns in locations other than the edge. Webbing that is frayed or distorted sufficiently to cause improper operation of any portion
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MAINTENANCE MANUAL of the restraint system. A total of 15 stitches can be torn in a stitch pattern before the webbing needs replacement. (c) Examine labels for legibility. (4) Fittings NOTE:
1. Burrs, nicks, and scratch is material that is raised above the normal surface. This material must be removed to make sure that the parts will fit together correctly.
NOTE: 2. Dents must not damage the finish or functional operation of any parts. (a) Examine fittings for: burrs, nicks or scratches, cracks, dents or corrosion. (5) Rotary Buckle and connector (a) Examine rotary buckle and connectors for burrs, nicks or scratches, dents or corrosion. (6) Reel Assembly (a) Examine reel assembly for burrs, nicks or scratches, cracks, dents or corrosion. (b) Make sure movable parts operate correctly. (7) Control Cable NOTE:
Damage to threaded parts must not be more than 50% of one thread.
(a) Examine control cable for damage to threaded parts, broken cable strands. (b) Make sure both ends of cable are attached. (c) Make sure cable moves freely in the conduit. (8) Handle Assembly NOTE:
Damage to threaded parts must not be more than 50% of one thread.
(a) Examine handle assembly for burrs, nicks or scratches, cracks dents or corrosion.
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FLIGHT COMPARTMENT DESCRIPTION AND OPERATION 1. General The flight compartment is located in this fuselage nose section between the frames No. 4 and 7. It is separated from the passenger compartment by a fixed partition with folding wings. The flight compartment is equipped with pilot’s seats, head rests, a navigator’s table, map spring bracket a spare fuse box, a flight documentation case and a portable lamp. The passenger compartment is separated from the flight compartment by a curtain. Greater part of the flight compartment is provided with upholstery and acoustic isolation for noise reduction. Located on the right-hand side of the flight compartment is an emergency exit door.
FIG. 1
FLIGHT COMPARTMENT FURNISHINGS (1) Pilot’s seats; (2) Navigator’s table; (3) Spare fuse box; (4) Portable lamp; (5) Flight documentation case
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MAINTENANCE MANUAL 2. Navigator’s table The navigator’s table which tilts into a recess in the right-hand side cockpit upholstery is intended for the co-pilot.
FIG. 2
NAVIGATOR’S TABLE (1) Table; (2) Spring clip; (3) Bearer; (4),(5) Pins; (6) Spring; (7) Pin; (8) Left-hand suspension; (9) Right-hand suspension
3. Spare fuse box (if installed) The spare fuse box is located in a pocket on the right-hand side of cockpit. The fuses stored in the box are intended for the replacement of burnt fuses:
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MAINTENANCE MANUAL •
in the distribution box located on the right-hand control panel in the cockpit
•
in the fuse panels located on the right-hand side of the cockpit between the frames No. 5 and 6
•
in the bus bar located between the frames No. 8 and 9 in the right-hand ceiling power supply section
•
in the space between the frames No. 1 and 2 of the fuselage nose section
The spare fuse box contains the following fuses: No.
Name
Qty
1.
Fuse
0.4 A CSN 354733F/1500
10
2.
Fuse
0.63 A CSN 354733F/1500
13
3.
Fuse
1 A CSN 354733F/1500
10
4.
Fuse
1.6 A CSN 354733F/1500
5
5.
Fuse
2 A CSN 354733F/1500
1
6.
Fuse
2.5 A CSN 354733F/1500
3
7.
Fuse
3.15 A CSN 354733F/1500
6
8.
Fuse
4 A CSN 354733F/1500
5
9.
Fuse
5 A CSN 354733F/1500
3
10.
Fuse
6.3 A CSN 354733F/1500
3
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Type
Note
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FIG. 3 NOTE:
SPARE FUSE BOX Values of the fuses may vary may be different according to the equipment used
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4. DV 3 FAN The DV 3 fan is attached with two screws to the windshield central column. The fan is put into operation by switching the FAN (AZRGK-5) circuit breaker situated on the clock panel.
FIG. 4
DV 3 FAN WIRING DIAGRAMME
5. Flight compartment upholstery The description and illustrations of the flight compartment upholstery are given in section 025.20.00 PASSENGER COMPARTMENT.
6. Flight documentation case The flight documentation case is placed in the middle of the vertical control channel in the plane of the frame No. 7. The case contains: •
Check lists of normal and emergency procedures
•
Weight and centre of gravity record
•
Flight plan
•
Charts and plans of aerodromes
NOTE:
The aircraft flight manual is placed in a special bag on the upper shelf of the rear baggage compartment.
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7. Map spring clips The map spring clips (holders) are fixed at the centre part of the control wheel of the first and/or second pilot. A.
The MADELEC P/N 205-05-Mxxx (Order No. 92510933) LED lighted chart holders can be installed on the steering wheels. These chart holders have LED lighting with use the 12 LED diodes. Intensity of the lighting can be regulated with use the potentiometer with OFF position.. For more information see the Data sheet on the website: www.madelec.fr http://www.madelec.fr/pdf/TDS%20205%2005.pdf
FIG. 5
MADELEC P/N 205-05-Mxxx MAP HOLDER
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The P/N F0080922 (Order No. 92513237) Map holders can be installed on the steering wheels. The P/N F0080922 map holder is small folding table for fixing of the flight plans or maps. Mechanically fixing of the maps or plans provide the metal spring. Map holder has the folding possibility with the two shifting levers for support of the sheet A5-A4 size. LED Lighting with regulation is part of map holder.
FIG. 6
P/N F0080922 MAP HOLDER
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8. EFB -iPad holders The flight compartment of the airplane can be equipped with the EFB -iPad holders (RAM-B-189-TAB3-ALA1-KRU – Ord. No. 95254390) and USB sockets installation – Refer to the figs. 7 and 8.
Description for the figs. 7 and 8: (2) RAM-HOL-TAB-LGU RAM Tab-Tite Universal Clamping Cradle for 9” or 10” Screen Tablets (Ord. No. 95254396) – 2 pcs; (3) RAM-B-238U RAM diamond ball base with 1” ball (95254394) – 2 pcs; (4) RAM-B-201U RAM double socket arm (94 mm) for 1” ball bases (95254392) – 2 pcs; (5) RAM-B-230U RAM double 1” ball adapter (95254393) – 2 pcs; (6) RAM-B-201U-C RAM long (152 mm) double socket arm for 1” ball bases (95254391) – 2 pcs; (7) RAM-B-202U RAM 2.5" Round Base with the AMPs Hole Pattern & 1" Ball (95254395) – 2 pcs; (8) B588165N Backplate – 2 pcs; (9) ECF504-5M USB Type A Female Panel Mount Coupler (91671490) – 4 pcs; (10) M5x25-A2 FABORY 51030 Screw (30000140) – 6 pcs.; (11) M3x12 ISO 7380 (30000127) – 8 pcs; (12) M3 CD DIN 980 Type V (33721053) – 8 pcs; (13) 3.2 CD DIN 125-1 Type A Washer (35655632) – 8 pcs
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FIG. 7
EFB -IPAD HOLDERS AND USB SOCKETS INSTALLATION (Description for fig. is mentioned on previously page)
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FIG. 8
EFB -IPAD HOLDERS AND USB SOCKETS INSTALLATION (CONT.) (Description for fig. is mentioned on previously page)
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FLIGHT COMPARTMENT SERVICING 1. Inspection of the navigator’s table and its tilting mechanism A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.10.00.A Periodical
E.
Procedures (1) Tilt the navigator’s table into its operation position. (2) Inspection of the navigator’s table and its tilting mechanism, incl. inspection of the spring clip condition (situated on the left-hand side of the working surface of the table). (3) Check the tilting of the navigator’s table in both limit positions. (4) Check correct functioning of the spring clip on the left-hand side of the table. (5) Defect not allowed: damaged paint coating, deformed or unstuck margin strips, deformed cover sheets, defects of mechanical character, failure of tilting mechanism and its catch, defective or fatigued clip spring. (6) Tilt the navigator’s table back into the initial position.
2. Inspection of the spare fuse box (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.10.00.B Periodical
E.
Procedures (1) Check the condition of the spare fuse box Defects not allowed: defective box, inclusion of spare fuses other than prescribed or of defective ones.
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MAINTENANCE MANUAL (2) Check completeness and the condition of the spare fuses in the box. Make up for missing fuses. The box shall contain the following spare fuses: Fuse
0.4 A
CSN 354733F/1500
10 pcs
Fuse
0.63 A
CSN 354733F/1500
13 pcs
Fuse
1A
CSN 354733F/1500
10 pcs
Fuse
1.6 A
CSN 354733F/1500
5 pcs
Fuse
2A
CSN 354733F/1500
1 pc
Fuse
2.5 A
CSN 354733F/1500
3 pcs
Fuse
3.15 A
CSN 354733F/1500
6 pcs
Fuse
4A
CSN 354733F/1500
5 pcs
Fuse
5
CSN 354733F/1500
3 pcs
Fuse
6.3
CSN 354733F/1500
3 pcs
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FLIGHT COMPARTMENT REMOVAL / INSTALLATION 1. Removal and installation of the navigator’s table (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Necessary tools from the tool kit
D. Referenced information
-
E.
Procedures (1) Removal of the navigator’s table (following procedure is write for RH navigator’s table): Remove the ledge located under navigator’s table refer to the step 1a and 1b in fig. 401. (2) Unlock the spring from the backstop refer to the step 2 in fig. 401. (3) Push out the navigator’s table refer to the steps 3a up to 3e in fig. 401. (a) Push out the navigator’s table to forward direction and push down – refer to the step 3b. (b) Push out the navigator’s table backward until the pins are out of cutout of the hinge – refer to the step 3c. (c) Turn the navigator’s table so, that pins again not clicked into cutout of the hinge – refer to the step 3d. (d) Push up the navigator’s table direction over the hinge – refer to the step 3d. (4) Pull out the navigator’s table to forward direction and pull to RH direction for remove the navigator’s table from LH suspension. (5) Perform the installation of the navigator’s table in reverse working process.
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FIG. 401
REMOVAL OF THE RH NAVIGATOR’S TABLE (LH NAVIGATOR’S TABLE IS MIRROR IMAGE)
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DV - 3 FAN DESCRIPTION AND OPERATION 1. Purpose The fan with an electric motor is intended for air circulation in the flight compartment. The fan propeller is fitted with rubber blades.
2. Technical data Voltage
28 V
Input power
1A
Rotation speed
2400 - 3300 r.p.m.
Operation mode
continuous
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DV - 3 FAN SERVICING 1. Check of DV - 3 fan brush height and inspection of its collector-brush assembly A.
Fixture, Test and Support Equipment
Power source 27 V, 40 A
B.
Materials
C 2029/9110 Varnish P/N 995208 (Order No. 95223925) Carbon brush - Dimension of new carbon brush 6x3.5x12.5mm
C. Tools
ISOLA No. 706, 4.5x0.8 Screwdriver
D. Referenced information
025.10.01.B Periodical
E.
Procedures (1) Unscrew two attachment screws of the rear fan cover. Remove the cover. Defects not allowed: Evidence of collector burning, brush wear (brush height must be at least 8 mm). Replace the brushes for new ones if their height is insufficient. Clean burnt or soiled collector with fine emery paper. Remove dust with a vacuum cleaner. Remove other impurities of the fan cover or propeller with a napkin wetted in technical petrol. (2) Check the fan for serviceability. Fan propeller must rotate in correct direction and no high collector sparkling shall be visible. (3) Reinstall the rear cover. Screw in the screws and lock them with varnish. (4) Disconnect the fan from power source and insert it into the protective cover.
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DV - 3 FAN REMOVAL / INSTALLATION 1. DV - 3 fan removal and installation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
No. 400 Emery cloth A 4
C. Tools
No. 697 6x120 Screwdriver
D. Referenced information
025.10.01.A Periodical
E.
Procedures (1) Fan removal Remove the DV - 3 fan from the middle windshield column in the flight compartment. Unscrew two screws using a screwdriver No. 697 (6x120) and then, having disconnected the single-pin plug-and-socket connector, remove the fan. (2) Fan installation Install the fan on the middle windshield column and secure it with 2 original screws using a screwdriver No. 697 (6x120) and then connect the single-pin plug-and-socket connector. Clean the electrical bonding surfaces with emery cloth No. 400.
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PILOTS’ SEATS DESCRIPTION AND OPERATION 1. General The seats of both pilots are fitted with seat adjusting mechanism and are attached to the floor. The seat adjusting mechanism is placed between the upper part of the front strut and the bottom part of the rear seat strut. The adjusting mechanism enables the seat to be shifted upwards-downwards (60 mm travel) and forwards-backwards (130 mm travel). Longitudinal and vertical seat positions are mutually dependent. The seat proper consists of a metallic skeleton and foamy filler material which are coated with fabric. Fixed on the rear backrest sides are the pockets for life jackets. Each seat is provided with 2 shoulder and 2 thigh straps fitted with a ring lock and fixed to the seat skeleton. The straps are inserted into the lock in the position marked with a dot. Then the lock control knob is turned into the position marked with a cross in which the safety belts are secured. By turning the control knob into the position marked "O", the safety belts get loosened. The length of individual straps may be changed by the buckle fixed on each strap. Both the pilot seats have removable elbow rests. At customer’s request the pilot’s seats can be fitted with arm rests. The arm rests can be installed on the LH side of the captain’s seat and on the RH side of the co-pilot’s seat. The arm rests can be set to five positions in the up-down direction. To adjust a suitable arm rest position, the safety pin is to be removed, the arm rest raised or lowered, and the safety pin inserted back into an appropriate hole in the arm rest frame.
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FIG. 1
PILOT’S SEAT (1) Pilot’s seat; (2) Front strut; (3) Rear strut; (4) Front bracket; (5) Rear bracket; (6) Adjusting mechanism; (7) Front bracket; (8) Rear bracket; (9) Central bracket; (10) Control wheel; (11) Cable; (12) Safety belts; (13) Lock knob; (14) Pin; (15) Lock; (16) Buckle Lock knob positions: ⋅ - insertion of individual straps into the lock x - belts fastened o - belts loosened
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FIG. 2
ELBOW REST ON PILOT’S SEATS (IF INSTALLED) (1) Rest; (2) Pin; (3) Safety pin; (4) Spring; (5) Plate; (6) Screw with washer; (7) Safety pin ONL 3313 NOTE:
The elbow rest is placed on the left hand side of the 1st pilot seat and on the right hand side of the 2nd pilot seat.
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FIG. 3
PILOT’S SEAT (IF INSTALLED) (1) Pilot’s seat; (2) Safety belts; (3) Lock knob; (4) Lock; (5) Buckle; (6) Truck; (7) Lever of adjusting equipment for adjusting the seat up and down; (8) Adjusting equipment; (9) Lever of adjusting equipment for adjusting the seat to the front - to the back; (10) Complete bowden; (11) Roller; (12) Catch; (13) Detachable back rest; (14),(15) Seat; (16) Head rest; (17) Collapsible bench - at the right-hand pilot seat only - see figure 4 Lock knob positions: ⋅ - insertion of individual belts into the lock x - belts secured o - belts loosened
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FIG. 4
COLLAPSIBLE SEAT (IF INSTALLED) (1) Collapsible seat; (2) Detachable back rest; (3) Safety pin; (4) Shift-out bar; (5) Guide tube; (6) Strut
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PILOTS’ SEATS FAULT ISOLATION No.
Trouble
Possible causes
Correction
1.
Adjusting mechanism does not turn or Seizing due to insufficient lubrication. Lubricate the adjusting mechanism. turns only with difficulty.
2.
The spring pins cannot be removed Deposits of dirt where spring pins are Clean the places of installation and from the attachment brackets on the installed. the pins. Lubricate the pins. floor.
3.
Wheel of adjusting device slips spontaneously.
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Excessive quality of vaseline
Wheel of adjusting device must be lubricated adequately.
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PILOTS’ SEATS REMOVAL / INSTALLATION 1. Removal and installation of pilots’ seats and elbow rests A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Removal of the pilot’s seats. (a) Remove the elbow rest by pulling it upwards. (b) By pulling the rings, take five spring pins out of the attachment brackets on the floor (4 pins in the struts, one pin in the adjusting mechanism). (c) Remove the pilot’s seat. (2) Installation of the pilots’ seats. (a) If the adjusting mechanism has been removed, it has to be re-installed on the seat into one of the eyelets of the suspension assembly in such a way that it is directed towards the bracket on the floor (note the differences between the left-hand and right-hand sides). (b) Set the seat on four brackets. (c) Match the holes and insert the spring pins (pin rings must be directed away from the fuselage centerline). (d) Slip the limiting cable under the head of the inner rear pin. (e) Slip the elbow rest from the top onto the pins provided on the front and rear struts of the seat so that the pins take such a position in which the elbow rest safety pins fit into recesses provided in the pins. (f)
Fit the arm rest on the pins of the front and rear struts of the seat in such a way that the safety pins of the arm rest fit into the recesses of the pins in the seat struts.
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SAFETY BELTS AMSAFE P/N 504388 SERIES DESCRIPTION AND OPERATION
1. Purpose The Restraint System is intended for use by the flight crew as a safety belt. The system is specially designed to restrain a human body (seat occupant) during all flight attitudes and landings. The lap belts can be used separately or with the shoulder harness.
2. Operation A. Shoulder Harness Straps The shoulder harness has a left and right hand strap. When the shoulder straps are unfastened, the inertia reels roll up both straps. B. Inertia Reels When the Restraint System is in use, the inertia reel allows unrestricted movement in the seat. The reel extends and retracts the shoulder harness as required. If a sudden acceleration force is applied to the shoulder harness, the inertia reel and shoulder strap will automatically lock. The occupant in the seat is held by the shoulder harness. When the shoulder harness is relieved of the force, the locking action of the inertia reel is released and unrestricted movement within the seat is once again permitted. For identification purposes the inertia reel is fitted with an equipment identification decal. C. Lever and Control Cable The Restraint System includes a two position lock lever and control cable assembly. When the lever is in the "automatic lock" position, the inertia reel (shoulder harness) lock will engage only when acceleration is applied to the shoulder harness. In the "manual lock" position, the shoulder harness lock assembly is firmly locked. The inertia reels will not allow webbing to release from the reel until the handle is moved to the "automatic lock" position. D. Lap Belts and Crotch Strap (if installed) There is a right and left hand lap belt portion. In addition to the sewn in connectors, the lap belts and crotch straps (if installed) also have a sewn in adjuster for length adjustments. For identification purposes the lap belts and crotch strap have a textile label.
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E. Rotary Buckle The rotary buckle has a housing with five slotted sockets. Each socket has a specially designed pawl, which latches and holds the connectors of the shoulder harness, lap belts, and crotch strap. The pawl is designated at the factory so the rotary buckle will remain attached to one connector. You can release the remaining connectors by rotating the buckle cover in either direction. The shoulder harness can be separately released by pushing forward on the black tab located between the shoulder harness fittings. F. Fastening Fasten the belts and straps as follows: (1) In the seated position, grasp the rotary buckle with one hand and position it over the center of the body. Use the other hand to bring over the connector of the lap belt. Insert the connector into the lateral slot opposite to the other connector half. (2) Adjust the length of the lap belts so that the rotary buckle takes up a central position and that the lap belts pass over the pelvis. (3) Tighten belts by pulling on the free end of webbing at the adjusters. Loosen belts by pulling on the pull tabs on the adjusters. (4) Insert the connector of the crotch strap in the lower slot of the rotary buckle (if not crotch fixed). Adjust by pulling on the free end of webbing at the adjustable connector. (5) Withdraw the shoulder straps from the inertia reel and insert the connectors into the upper slots of the rotary buckle. G. Release NOTE:
Do not allow the shoulder straps to be wound up unrestrained.
(1) Rotate the buckle cover in either direction to release the connectors. (2) If the lap belts are to remain attached to the rotary buckle, push on the black tab on top of the rotary buckle to release the shoulder harness.
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SAFETY BELTS AMSAFE P/N 504388 SERIES FAULT ISOLATION
1. Task - Testing on Aircraft Use the following procedures to make an analysis of the performance of the restraint system while on the aircraft. Table 102 is a fault isolation guide, which has been keyed to the test procedures. Use it to isolate malfunctions that occur when you do the test. A. Equipment and Materials No equipment or materials required B. Inspection Intervals •
Concurrently with WP- 025.00.00.G
•
When malfunction is reported for failing requirements described in paragraph 1.
C. Procedure •
Follow procedures as dictated in table 101
•
If restraint fails any tests in table 101, remove restraint for further evaluation or overhaul by AmSafe Inc.
Table 101 - Restraint system test Test No.
Procedure
Limits
1.0
Initial Test
1.1
Insert all connectors into rotary buckle.
Connector engages.
1.2
Release connectors by rotating the rotary
All but one of the connectors release. The
buckle cover clockwise.
buckle cover should return to the closed position.
1.3
1.4
Repeat step 1.1 then release connectors by
All but one of the connectors release. The
rotating the rotary buckle cover
buckle cover should return to the closed
counterclockwise.
position.
Put the lever on the manual lock handle assy in the “automatic locking” position.
1.5
Slowly pull the shoulder harness webbing all Webbing extends. of the way out of the inertia reel assembly. Observe webbing for freedom of reel action
Webbing should not exhibit excessive web
and general appearance.
fray or any cuts.
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Test No.
Procedure
1.6
Slowly let the webbing retract into the inertia
Limits
Webbing retracts.
reel assembly. 1.7
Repeat steps 1.5 and 1.6 four times.
The harness webbing extends and retracts smoothly.
1.8
Hold the inertia reel assembly and withdraw
The locking system should lock and the
approximately 25% of webbing from the reel
webbing should not extend.
and rapidly accelerate the webbing until the system locks. 1.9
Slowly let the webbing retract into the inertia
Webbing retracts.
reel assembly. 1.10
Repeat steps 1.8 and 1.9 four times.
The locking system should lock and the webbing should retract.
2.0
Verify handle assembly control
2.1
Move the lever on the handle assembly from Linkage should move as handle is moved. the "manual lock" position to the "automatic lock" position.
2.2
Repeat step 2.1 four times.
Linkage should move as handle is moved.
2.3
Move the lever on the handle assembly to
The inertia reel assembly is locked. The
the “manual lock” position.
webbing can not be extended.
Move the lever to the "automatic lock"
The webbing can be extended. The inertia
position.
reel assembly locks when sudden
2.4
acceleration is applied to the shoulder straps.
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2. Procedure for Fault Isolation When a Test Fails: A. Find the number of the test in table 101 where the failure occurs. B. Use the fault isolation procedure in table 102 to isolate the malfunction. All fault isolation procedures are keyed to the Test No. column of Table 101.
Table 102 - Fault Isolation Test No. Where Failure Occurs
Probable Cause of Failure
Repair Task
1.1
Damaged buckle or connector.
Replace belt portion.
1.2
Damaged buckle or connector.
Replace belt portion.
1.3
Damaged buckle or connector.
Replace belt portion.
1.5
Damaged inertia reel assembly or
Replace shoulder harness assembly.
webbing. 1.6
Damaged inertia reel assembly.
Replace shoulder harness assembly.
1.7
Damaged inertia reel assembly or
Replace shoulder harness assembly.
webbing. 1.8
Damaged inertia reel assembly.
Replace shoulder harness assembly.
1.9
Damaged inertia reel assembly.
Replace shoulder harness assembly.
1.10
Damaged inertia reel assembly.
Replace shoulder harness assembly.
2.1
Damaged handle or cable assembly.
Replace the handle or cable assembly.
2.2
Damaged handle or cable assembly.
Replace the handle or cable assembly.
2.3
Damaged inertia reel assembly.
Replace shoulder harness assembly.
2.4
Damaged inertia reel assembly.
Replace shoulder harness assembly.
CAUTION:
THE RESTRAINT SYSTEM MAY NOT BE DISASSEMBLED BEYOND THE LEVEL INDICATED BELOW. FURTHER REPAIR OF THIS SYSTEM MAY ONLY BE CARRIED OUT BY AMSAFE INC. (USA), AMSAFE LTD. (UK) OR AN AMSAFE APPROVED REPAIR STATION. AMSAFE INC. IS NOT RESPONSIBLE FOR DAMAGE OR MALFUNCTIONS RESULTING FROM ANY UNAUTHORIZED ATTEMPT TO REPAIR OR DISASSEMBLE THE RESTRAINT SYSTEM.
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INTENTIONALLY LEFT BLANK
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SAFETY BELTS AMSAFE P/N 504388 SERIES CLEANING / PAINTING 1. Cleaning the safety belts A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Isopropyl Alcohol - Optional source, HAZARD CODE 130D Mild Soap - Optional source (household dishwasher liquid soap, household laundry detergent) Cloth lint-free - Optional source Sponge or soft brush - Optional source
WARNING:
BEFORE YOU USE A CLEANING MATERIAL, YOU MUST KNOW THE HAZARD CODE AND OBTAIN THE NECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODES FOR MATERIALS IN THE AMSAFE INC. ABBREVIATED COMPONENT MAINTENANCE MANUAL.
NOTE:
Equivalent alternatives are permitted for the equipment and materials in THE AMSAFE Inc. ABBREVIATED COMPONENT MAINTENANCE MANUAL.
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Task To clean the restraint system, remove dirt and unwanted oil and grease. This helps the restraint system to last longer and prevents corrosion of the metal parts. The webbing is to be cleaned with fresh water and a mild soap. The metal fittings are cleaned with a cloth moistened with isopropyl alcohol. After cleaning the assemblies, protect them from moisture, dirt, or other contamination. Keep them protected until you do a visual check and return the restraint system to service. CAUTION:
1. THE RESTRAINT SYSTEM MUST NOT BE MACHINE-WASHED, BECAUSE THE WEBBING WILL SHRINK AND ITS PERFORMANCE CHARACTERISTICS WILL BE CHANGED SIGNIFICANTLY. 2. THE RESTRAINT SYSTEM MAY BE DRY-CLEANED. HOWEVER, THE WEBBING WILL LOSE ITS ABRASION-RESISTANCE COATING AFTER
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EACH CLEANING AND ITS SERVICE LIFE WILL THEREFORE BE DECREASED. 3. REFER TO THE “CHECK” SECTION OF THIS MANUAL TO DETERMINE WHEN THE WEBBING OF A RESTRAINT SYSTEM MUST BE REPLACED BY AM-SAFE OR AN AM-SAFE APPROVED REPAIR STATION. 4. WHEN CLEANING THE RESTRAINT SYSTEM, CARE MUST BE TAKEN TO KEEP AWAY FOREIGN MATTER AND CLEANING MEDIA FROM THE HARDWARE ASSEMBLIES. 5. NO SOAP OR WATER IS TO BE USED ON METAL PARTS. (2) Cleaning the webbing. (a) Attach pieces of cloth to cover the metal fittings (b) Either: Dry clean the webbing, (see cautions) or Hand wash the webbing: a gentle scrub with a soft brush and cold soapy solution is permissible. (c) Dry the restraint system in an area that has a good flow of air. Do not dry the restraint system in sunlight or near any source of heat. (d) Inspect the dry restraint system. (3) Cleaning hardware. WARNING:
WHEN USING ISOPROPYL ALCOHOL, FOLLOW THE DIRECTIONS AND WARNINGS GIVEN BY THE MANUFACTURER. AVOID ANY CONTACT WITH THE WEBBING MATERIAL.
(a) Clean the hardware with a lint free cloth moistened with isopropyl alcohol.
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CURTAINS DESCRIPTION AND OPERATION 1. General The roll-down curtains in the cockpit are intended for the blind-flight training of crews (IFR - flights). The curtains cover the windshield and the lateral triangular glazing of the flight compartment – Refer to the fig. 1. The flight compartment of the airplane can be equipped on request with the roll-down curtains on the side windows between frames No. 6 and 7 – Refer to the fig. 2.
FIG. 1
ROLL - DOWN CURTAINS (1) Upper left-hand curtain; (2) Upper right-hand curtain; (3) Left hand side curtain; (4) Right-hand side curtain; (5) Upper central attachment fitting; (6) Pad; (7) Joint; (8) Cover; (9) Screw with washer; (10) Upper left-hand attachment fitting; (11) Upper right-hand attachment fitting; (12) Plate; (13) Attachment fitting arm; (14) Pin; (15) Screw; (16) Hook with screw and washer; (17) Left-hand bottom attachment fitting; (18) Right-hand bottom attachment fitting; (19) Left-hand top attachment fitting; (20) Right-hand top attachment fitting; (21) Pin; (22) Screw; (23) Screw with washer a, b - holes in the curtain
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FIG. 2
ROLL-DOWN CURTAINS ON THE SIDE WINDOWS BETWEEN FRAMES No. 6 AND 7 (1) B092062L/R Lower hinge LH, RH – 1+1 pcs; (2) B095073L/P Upper hinge LH, RH- 1+1 pcs; (3) B406021N Backplate – 4 pcs; (4) B092061N Hook – 2 pcs; (5) B092065N Washer – 4 pcs; (6) M4x8 CD 5S ONL 3147 (Ord. No. 31850408) – 4 pcs; (7) M3x12 CD 5S ONL 3147 (Ord. No. 31850312) – 4 pcs; (8) M3 CD Nut DIN 980 V type (Ord. No. 33721053) – 4 pcs; (9) M4x10 CD 5S ONL 3147 (Ord. No. 31850410) – 4 pcs; (10) B406022L Roll-down curtain on the LH side window – 1 pc; (11) B406022P Roll-down curtain on the RH side window – 1 pc; (12) ) 4.3 CD DIN 125-1 type A (Ord. No. 35655643) – 4 pcs;
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CURTAINS REMOVAL / INSTALLATION 1. Removal and installation of curtains A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Curtain installation. (a) Insert the upper left-hand curtain (1) - see fig. 1 - into the joint (7) of the upper central attachment fitting (5). Push the attachment fitting arm (13) aside and insert the opposite end of the left-hand curtain into it. Remove the pin (14) from the hole "a" provided in the curtain and insert it into the attachment fitting arm hole, thus fixing the curtain in this assembly. NOTE:
The pin (14) is marked with red colour.
(b) Install the upper right-hand top curtain (2) proceeding analogically to paragraph (1-a) of this work procedure. (c) Insert the left-hand side curtain (3) into the left-hand bottom attachment fitting (17). Set the top end of left-hand curtain into the left-hand top attachment fitting (19). Remove the pin (21) from the hole "b" provided in the curtain and insert it into the left-hand top attachment fitting arm hole, thus fixing the curtain in the assembly arm. NOTE:
The pin (21) is marked with red colour.
(d) Install the right-hand side curtain (4) proceeding analogically to paragraph.(1-c) of this work procedure. (e) Roll out the upper curtains and fix them in the hooks (16). Roll out the side curtains and fix them on the pins (23). (2) Curtain removal (a) After loosening the curtains from hooks (16) and pins (23), the curtains will be rolled on the bars by the springs installed in the latter. (b) Remove the pin (21) of the left-hand top attachment fitting (19) hole and insert it into the hole "b" in left-hand side curtain (3). Remove the left-hand side curtain (3) from the left-hand top attachment fitting (19) and from the left-hand bottom attachment fitting (17). EFFECTIVITY ALL
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MAINTENANCE MANUAL (c) Remove the right-hand side curtain (4) proceeding analogically to paragraph (2-b) of this work procedure. (d) Remove the pin (14) of the attachment fitting arm (13) hole and insert it into the hole "a" in the upper left-hand curtain (1). Remove the upper left-hand curtain (1) from the attachment fitting arm (13) and from the upper central attachment fitting (5) joint (7). To do this, push the attachment fitting arm (13) aside. (e) Remove the upper right-hand curtain (2) according to paragraph.(2-d) of this work procedure.
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PASSENGER COMPARTMENT DESCRIPTION AND OPERATION 1. General The passenger compartment is situated behind the flight compartment as far as the bulkhead No. 21. The passenger compartment is separated from the flight one by a stationary partition with curtains. The passenger compartment is upholstered and protected against noise by sound insulation. Passenger compartment floor is covered by a carpet. Emergency exits are located in the centre section the passenger cabin, on both the LH and RH sides. Situated on the left-hand side in the rear part of the passenger compartment is the entrance door. Near the entrance door there is a shelf with hooks where headwear and clothes may be put off. The passenger compartment is provided with foldable serving plates and a newspaper magazine holder (if installed). At customer’s request the aircraft can be modified and delivered in the following versions:
1.1 Passenger transport version – 19 seats (basic version) The passenger compartment is provided with 5 single seats on the LH side and 7 double seats on the RH side (see fig.1)
FIG. 1
PASSENGER COMPARTMENT FURNISHINGS (1) Single passenger seat, (2) Double passenger seat, (3) Rear baggage compartment, (4) Shelf for headwear and rack, (5) Toilet, (6) Foldable serving plate (if installed), (7) Newspaper and magazine holder (if installed), (8) Refresh bar (if installed)
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MAINTENANCE MANUAL 1.2 Passenger transport version – 17 seats The passenger compartment is provided with 5 single seats on the LH side and 6 double seats on the RH side (see fig. 2)
FIG. 2
PASSENGER COMPARTMENT (COMMUTER AIRCRAFT) (1) Single passenger seat, (2) Double passenger seat, (3) Air stair locker, (4) Toilet, (5) Folding table, (6) Newspaper and magazine holder, (7) Rear baggage compartment, (8) Pilot emergency exit door, (9) Passenger emergency exit door, (10) Rack, (11) Room for baggage, (12) Signaling panel (Signalization to call in the crew ), (13) Curtain, (14) Fan
1.3 Passenger transport version – 11 seats In the front section of passenger compartment three rows of seats are installed (i.e. 7 seats). The seats are provided with foldable serving plates. In the rear section (between frames No.13 and 18), two double seats with armrests are installed facing a conference table with foldable leaves (see Fig. 3).
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FIG. 3
PASSENGER COMPARTMENT (EXECUTIVE VERSION) Passenger seats, (2) Front double seat with armrests, (3) Conference table, (4) Rear double seat with armrests, (5) Box for storing air stairs, (6) Buffet, (7) Toilet, (8) Baggage compartment, (9) Shelf for headwear and rack, (10) Curtains, (11) Newspaper holder, (12) Emergency exit NOTE: Glass holders, Map spring brackets and Pilot’s head rest not shown.
1.4 Passenger executive version – 8 seats In the front and rear section of passenger compartment, two double seats with armrest are installed facing a conference table with foldable leaves (see Fig. 4).
FIG. 4
PASSENGER COMPARTMENT LAYOUT (EXECUTIVE VERSION) (1) Newspaper rack, (2) Forward double-seat, (3) Table, (4) Rear double seat, (5) Toilet, (6) Curtain, (7) Refrigerator (if installed), (8) Galley (if installed), (9) Air stair locker, (10) Fan, (11) Attendant seat
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MAINTENANCE MANUAL 1.5 Flying ambulance There is a possibility of installing medical equipment. The medical equipment serves for transportation of wounded (ill) persons on seats and nurse. The medical equipment comprises: No.
Name
Type (Dwg. No.) B 099 209 N
Qty
1.
Carrier bar No.1
2
2.
Carrier bar No.2
B 094 219 N
2
3.
Adjustable support bar No.3
B 094 225 N
3
4.
Connection bar No.4
B 094 230 N
2
5.
Fastening belt No.5
B 094 240 N
4
6.
Nurse table No.7
B 094 280 N
1
7.
Lower spar No.8
B 094 245 N
1
8.
Lower spar No.9
B 094 250 N
1
9.
Upper spar No.10
B 094 254 N
1
10.
Side spar No.11
B 094 265 N
1
11.
Rest No.15
B 094 290 N
1
12.
Back curtain No.16
B 094 270 N
2
13.
Clamp No.17
B 094 275 N
2
14.
Bracket No.18
B 094 203 N
2
15.
Foot No.19
B 094 204 N
2
16.
Curtain No.20
B 094 205 N
1
17.
Curtain No.21
B 094 202 N
1
18.
Canister for drinking water
B 591 501 N
1
19.
Litter bin No.24 (holder)
B 094 381 N
1
20.
Pad (without number)
B 094 241 N
2
21.
Screw with clasp (without
B 094 649 N
3
number)
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No.
Name
Type (Dwg. No.)
Qty set
22.
Standard connection part
as per list stored in the case
23.
Three-place seat
B 094 441 N
1
24.
Three-place seat
B 094 443 N
1
25.
Stretcher
CSN 847012
6
26.
Box for a stretcher
C 050073 N
1
NOTE: The medical equipment is supplied packed and stored in the pocket. Description of ill person transport equipment: Seats are located on the left hand side of the passenger compartment between frames No.8 and No.14. They serve for transport of 5 wounded persons. The support seat frame is locked by landing secure pins into holes in the floor and by screwing the holder. Above seats below windows are rests. The rests are fixed with screws in frames. The nurse table is fixed in a rotating way into the suspensions between frames No.14 and 15 on the left side of the passenger compartment. The table for a nurse is in operation fixed and locked with the support frame. The table support frame is locked with a holder screwed to the floor. In the initial (tilted) position the nurse table is fixed with a special knob at the 14th frame. The table support bar is secured with a leather clip on the table. The standard stretch fixing design consist of bars (1), (2) – see Fig.6 and the fastening belts (5). The support bars are connected to the feet (13), to the beam (6) on the floor, to the bracket (12) and to the beam (9) on the aircraft compartment side. Always two bars and two bars are connected with adjustable connection rod (4). Safety belts are hung on suspensions (11) and spar (8) near to the compartment ceiling. They pass through the clamps (10) and the beam (7) and are locked with clamps on the belts. To strengthen frames No.13 and 17 adjustable support bars (3) are fixed into holes in the clamps and the attachments. Another equipment consists of a litter bin located below the nurse table and canister with drinking water located in the room of the 17th frame on the right side. Medical material (necessary for medical care and transport of ill or wounded persons) is stored in the baggage compartment.
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FIG. 5
ARRANGEMENT OF ILL PERSONS TRANSPORT EQUIPMENT (1), (2) Stretcher, (3), (4) Seat, (5) Table for a nurse, (7) Litter bin, (8) Canister with drinking water, (9) Rests
FIG. 6
STRETCHER FIXING DESIGN (PART 1) (1), (2) Support bars, (3) Adjustable support bars, (4) Connection rod, (5) Fastening belts, (6), (7) Lower beam, (8) Upper beam, (9) Side beam, (10) Clamp, (11) Upper suspension, (12) Bracket, (13) Foot, (14), (15) Safety pin.
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FIG. 6
STRETCHERS FIXING DESING (PART 2)
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FIG. 7
INSTALLATION OF SEATS AND TABLE FOR NURSE (1) Table for nurse, (2) Auto knob, (3) Attachment, (4), (5) Seats. (6), (7) Rests, (8) Pad, (9) Holder
1.6 Parachute jumping The parachute jumping consist of the following basic items:
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•
seats
•
anchor cables
•
signaling
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FIG. 8
LOCATION OF SEATS AND AVAILABLE SPACES IN THE AIRCRAFT CABIN – PARACHUTE VERSION (1) Seats of parachutist, (2) Holes and covers in the ceiling for PARA ropes, (3) Rear baggage compartment, (4) Toilet, (5) Paratroop guide seat
Seats Seats (1) – see Fig. 8 aircraft cabin. There are 6 places on the right side (two three-seated benches), twelve places in total. The seat for the parachute guide is assigned (5) on the right side by the baggage compartment in the opposite of the main door. The seats are fixed on the air channels of the airconditioning system. Each seat is provided with its own abdominal fastening belt and a pocket for depositing of a life jacket. NOTE: Rests above the seats are not mounted in a paradropper version.
Anchor cables Anchor cables (4) – see Fig. 9 serve for forced opening of the parachute of paratroopers. Each row of the paratroopers is provided with own cable which is fixed in front on the 8th bulkhead (each separately). The anchor cables couple in the rear on the suspensor (on the 18th bulkhead).
Signaling parachuting Signaling of parachuting serves for intercommunication between the co-pilot and the parachute guide. Signaling of parachuting consists of: •
signaling box of a parachuting
•
signaling panel
•
acoustic signaling
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FIG. 9
LOCATION OF THE PARACHUTE JUMPING (1) Seats of paradroopers (three seated), (2) Seat of the parachute guide, (3) Fastening belts, (4) Anchor cables, (5) Turnbuckle, (6) Front suspensors, (7) Rear suspensors, (9) Holder, (10) Securing belt, (11) Cover B 593 779 N, (12) Screw M 3, (13) Screw M 6
The signaling box (1) – see Fig. 10 is placed between the 5th and 6th bulkheads. On the box there are three push-button change-over switch LUN 3211-8 (READY, GO, STOP), four check lights SLC-51 (yellow – READY, green – GO, red – STOP, white – FINISHED) and (9) key switch VG 15K-2S (JUMPING). Signaling panel (10) is placed in front of the main door between the 14th and 15th bulkhead on the left. On the signaling panel there are 3 lights –modified CHS-39 (yellow – READY, green – GO, red – STOP) and a push button switch LUN 3211-8 (FINISHED). Acoustic signaling consists of a bell (15) SEZ-45-2 placed between the 16th and 17th bulkheads. A circuit breaker (16) AZRGK-5 (JUMPING) is placed on the overhead panel.
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FIG. 10
SIGNALING PARACHUTING (1) Signaling box of parachuting, (2) Push button change-over switch LUN 3211-8 (READY), (3) Push button change-over switch LUN 3211-8 (GO), (4) Push button change-over switch LUN 3211-8 (STOP), (5) Checking light SLC-51 (yellow – READY), (6) Checking light SLC-51 (green – GO), (7) Checking light SLC-51 (red – STOP), (8) Checking light SLC-51 (white FINISHED), (9) Key switch VG15K-2S (JUMPING), (10) Signaling panel, (11) Light CHS-39modified (yellow – READY), (12) Light CHS-39-modified (green – GO), (13) Light CHS-39modified (red – STOP), (14) Press button change-over switch LUN 3211-8 (FINISHED), (15) Bell SEZ-45-2, (16) Circuit breaker AZRGK-5 (JUMPING).
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FIG. 11
INSTRUMENT PANEL OF PARACHUTE GUIDE (1) Instrument clock ACS-1M; (2) Airspeed indicator LUN 1113.12; (3) Altimeter LUN 1124.12; (4) Shield LUN 3591.22; (5) Pushbutton 205K
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FIG. 12
SCHEME OF SIGNALLING RACKET (IF INSTALLED) (1) Flare gun EKSR-46 (9); (2) Signalling panel 571854 045771 or 443854 040771; (3) Circuit breaker – JUMPING AZGRK 5
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MAINTENANCE MANUAL Supplementary equipment Supplementary equipment consists of: •
instrument panel of parachute guide
•
fastening belts
1.7 Cargo version (if installed – see section 025.52.00)
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PASSENGER COMPARTMENT SERVICING 1. Wounded person loading (if flying ambulance is installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures Wounded person loading is carried out in the following way: (1) Open the main door and lock then in the open position (2) Tilt the table to the aircraft wall, secure with belt at the auto knob and lock the table support with a leather clamp to the table plate. (3) Hang the standard stretcher from up to down and start with the upper front stretcher NOTE: - Before your start loading stretcher check locks condition the support bar. The lock shall be in accordance with the state drawn in Fig. 301. - Adjustable support (3) – see Fig. 6 shall be removed during landing wounded persons. (4) After hanging stretcher secure the stretcher with clamps on safety belts, pass safety belts through clamps in the floor and secure with buckles. (5) To strengthen frames 8, 13 and 17 fix the adjustable support bars (3) – Fig. 6 (6) Embark slightly wounded persons. (7) Tilt the unused table and fix to the floor.
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FIG. 301
LOCKER (1) Unlocked position, (2) Locked position
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PASSENGER COMPARTMENT REMOVAL / INSTALLATION 1. Removal and installation equipment for wounded persons (if flying ambulance is installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures NOTE 1:
Carry out the following work before you start installation of the equipment.
NOTE 2:
Remove passenger seats on the left and right side of the passenger compartment.
NOTE 3:
Remove 8 upholstered lids below the windows on the left side of the aircraft and 3 upholstered lids on the right side.
(1) Installation of stretcher fixing (a) Remove blinders from the compartment side at the 8th frame (on the right side of the fuselage by the emergency exit). Unscrew 4 blinder screws at the edge on the floor and 6 blinders in the aircraft axis. (b) Fix foot No.19 into the floor and fix the clamp No.17 with 10 CSN 021101.44 screws. Fix the upper attachment No.16 with six CSN 021101.44 screws M6x22. Fix the bracket No.18 to the aircraft side wall with CSN 021101.44 screws M6x22. Slip carrier bar No.1 on aircraft side wall and hang the fastening belt No. 5 into the ceiling on a CSN 3342.04 secure pin 8x40. (c) Remove the blinders from the aircraft side wall at the 12th, 13th, and 14th frame (on the right side of the aircraft compartment between the 3rd and 6th window from the front part of the compartment). Unscrew 24 blinders at the edge or the floor and in the fuselage axis. (d) Fix the lower spar No.8 at 12th, 13th and 14th frame into the floor next to the edge with 8 CSN 021101.44 screws M6x30. In the aircraft compartment axis fix the lower spar No. 9 at the 12th, 13th and 14th frame to the floor with 8 CSN 021101.44 screws M6x23. Fix the side wall at 12th and 14th frame with 8 CSN 021101.44 screws M6x25. Screw the upper spar No.10 to the compartment ceiling with 8 CSN 022101.49 screws M6x22.
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In the space beyond the 24th frame and in front of the 14th frame it is necessary to follow prescribed screws length – nuts are sealed. Install the carrier bar No. 2 on the aircraft compartment side behind the 12th frame and connect it to the forward carrier bar No. 1 at the 1st and 3rd frame by a connection bar No. 4 with two LEN 3342.04 secure pins 8x40.
(e) Remove the blinder from the side of the 17th frame (on the right aircraft compartment side opposite the main door). Unscrew 4 blinder screws at the edge of the floor and 6 blinders in aircraft axis. (f)
Screw the foot No. 19 and the clamp No. 17 with 10 CSN 021101.44 screws M6x25 into the floor.
(g) Screw the bracket No. 18 with 6 pieces of CSN 021101.44 screws M6x22 on the side aircraft wall. Screw the back curtain No. 16 with pieces of CSN 021101.44 screws to the ceiling. Hang the fastening bolt No. 5 on the LeN 3342.04 secure pin 8x40. Slip the carrier bar No. 2 on the aircraft compartment side and connect to the bar No. 1 at the 13th frame by the connection bar No. 4 with two LeN 3342.04 secure pins 8x40. (h) To straighten the 8th, 13th and 17th frame fix the adjustable support bar No. 3. (2) Installation of slightly wounded person seats. (a) Adjust the seat so that pins will fit into the floor and set the holes for screws at the airconditioning channel (heating). (b) Set washers and screw the screws (7 pieces) into the air - conditioning channel. (c) Set the holder at the pipe frame and at the hole for a screw on the floor. Screw the holder. (3) Installation of the nurse table (a) Remove the blinders at the 14th and 15th frames (at the main door) on the left side of the aircraft compartment. Screw attachments No. 20 and 27 with two CSN 021146-2K screws M5x15 at the place of the 14th frame. Slide the table No. 7 on the attachments and slip the ONL 3331 pins 5x26 (to the 14th frame with the head forward) which lock the ONL 3271 washers 5.0.5 ONL 3271 and the ONL 3345 fuses 1.5. Put the support table frame pins into the holes on the floor and secure the frame with a screw with B 094 649 N clam. (4) Installation of the canister with water and of the litter bin. (a) In the space of the 21st frame screw the support (2) and the litter bin with canister with drinking water refer to Fig. 401. The canister support is fixed to the floor with the help of a shim (3) which must be set on the proper place during installation of the carrier bar (1). (b) Install the litter bin holder under the nurse table install this holder at heat channel on the screws remaining after removing the passenger seat. Adjust the holder at the holes with riveted nuts on the heating channel. Fix the holder by two screws and set the litter bin. EFFECTIVITY ALL
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MAINTENANCE MANUAL (5) Removal of the stretcher fixing design (if removed) nurse table, canister with drinking water and litter bin.
FIG. 401
INSTALLATION OF THE CANISTER WITH DRINKING WATER Carrier bar, (2) Support, (3) Shim (a) Removal of the stretcher fixing design (if installed), nurse table and canister with drinking water perform in the reverse sequence as describe in items 1, 2, 3, 4 of this work procedure.
NOTE:
After removal of equipment as per item 5-a install the blind screws. Install passenger seats in the passenger compartment back. The blind (14 pieces in all), which was removed before installation put again into the empty holes.
2. Removal and installation of the parachute seats (three-seated benches) (if parachute jumping is installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Removal of the seats (a) Screw out the screw in the floor fixing the holder of the tube frame of the seat. Take off the holder.
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MAINTENANCE MANUAL (b) Screw out the screw (7 pieces) fixing the seat to the channel of the airconditioning (heating) and take off the washer. (c) Draw out the seat on pins from the floor and put aside on the auxiliary table. (2) Installation of the seats (a) Fix the seat by ppins to the floor and holes on the channel of the airconditioning system (heating). (b) Adjust the washer and screw the screws (7 pieces) to the channel of the airconditioning system (heating). (c) Adjust the holder on the tube frame and on the hole for the screw in the floor. Fix the holder by means of a screw. NOTE:
The removal and installation of the other three seats of parachutes is being done in the same maner.
3. Removal and installation of the anchor cables (if parachute jumping is installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Removal of the anchor cables (a) Take out the securing pins at the front hinges of the anchor cables and take out the pins. The anchor cables to be put down the floor of the aircraft cabin. (b) Take out the split pin at the rear hinge, take out thewasher with the pin talce down the cables with the hing. (c) Coil the cables and get them stored. (2) Installation of the anchor cables (a) Put the anchor hinge of the cables to the hinges on the ceiling in the rear part of the aircraft cabin. Put in the pin with the washer and secure by a new split pin. (b) The front part of the anchor cables is to be put into the hinges on the ceiling and the pins slided. Secure the pins by securing pins. (c) Straighten the anchor cables so that the slacken is 150 mm – 20 mm (measured from the ceiling of the cabin for passengers 600 mm from the rear hinge by the action of strength 49 N(5 kp)).
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4. Removal and installation of the tables of passenger executive (VIP) version (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
B595088N Installation kit of Front table; B593209N Installation kit of Rear table
C. Tools
Necessary tools from the tool kit
D. Referenced information
-
E.
Procedures (1) Installation of B595088N salon front table – Refer to the fig. 402: WARNING:
FOR TABLE FIXING ONLY THE PRESCRIBED SCREWS SHALL BE USED. SALON TABLE SHALL BE INSTALLED ON A CARPETED FLOOR ONLY.
(a) Remove the respective covers from Velcro tapes on the right side of fuselage and tilt the two top holders (3) of the table (1). At first installation, install the leg (2) on the desk of table (1) with use screws (10). (b) Match the round holes of the leg (2) with holes in the floor of fuselage and the holes of table with holes of the top holders (3) on the right side of fuselage. (c) After that put on the screws (4) see fig. 402 into the washes (6) and round holes of the table and holders (3) from top side of the table. Install the washers (5) and nuts (8) on the screws and tighten them. (d) Install the screws (9) into the round holes of the leg and tighten them. (2) Removal of B595088N salon front table: (a) Loosen and unscrew the screws (9) attaching the salon table to the salon compartment floor. (b) Loosen and unscrew the screws (4) (nuts (8), washers (5, 6)) attaching the salon table to the top holders (3) on right side of fuselage. (c) Remove the salon table by pulling the table upward. (d) Tilt up the two top holders (3) on the right side of fuselage and install the covers on the Velcro tapes on respective places on the right side of fuselage.
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FIG. 402
B595088N FRONT TABLE OF THE PASSENGER EXECUTIVE (VIP) VERSION (1) B093257N Front table; (2) B595773N Leg; (3) Top holder; (4) M8x45 – A2 FABORY 51060 Screw (2 pc); (5) 8.4 CD Washer (2 pc); (6) B595087N Washer (2 pc); (8) M8 CD ONL 3248 Nut (2 pc); (9) M6x25 ISO 4762 Screw (2 pc); (10) 4.8x13 A2 DIN 7971C Screw (6 pc) (3) Installation of B593209N salon rear table – Refer to the fig. 403: WARNING:
FOR TABLE FIXING ONLY THE PRESCRIBED SCREWS SHALL BE USED. SALON TABLE SHALL BE INSTALLED ON A CARPETED FLOOR ONLY.
(a) Remove the respective covers from Velcro tapes on the right side of fuselage and tilt the two top holders (3) of the table (1). At first installation, install the leg (2) on the desk of table (1) with use screws (10). (b) Match the round holes of the leg (2) with holes in the floor of fuselage and the holes of table with holes of the top holders (3) on the right side of fuselage. (c) After that put on the screws (4) see fig. 402 into the washes (6) and round holes of the table and holders (3) from top side of the table. Install the washers (5) and nuts (8) on the screws and tighten them. (d) Install the screws (9) into the round holes of the leg and tighten them.
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MAINTENANCE MANUAL (4) Removal of B593209N salon rear table: (a) Loosen and unscrew the screws (9) attaching the salon table to the salon compartment floor. (b) Loosen and unscrew the screws (4) (nuts (8), washers (5, 6)) attaching the salon table to the top holders (3) on right side of fuselage. (c) Remove the salon table by pulling the table upward. (d) Tilt up the two top holders (3) on the right side of fuselage and install the covers on the Velcro tapes on respective places on the right side of fuselage.
FIG. 403
B593209N REAR TABLE OF THE PASSENGER EXECUTIVE (VIP) VERSION (1) B093258N Front table; (2) B595773N Leg; (3) Top holder; (4) M8x45 – A2 FABORY 51060 Screw (2 pc); (5) 8.4 CD Washer (2 pc); (6) B595087N Washer (2 pc); (8) M8 CD ONL 3248 Nut (2 pc); (9) M6x25 ISO 4762 Screw (2 pc); (10) 4.8x13 A2 DIN 7971C Screw (6 pc)
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5.
Removal and installation of the salon seats of passenger executive (VIP) version (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
B515440N Screw (8 pc); B093437N Screw (4 pc)
C. Tools
12x11 CSN 230611.6 open-end spanner
D. Referenced information
-
E.
Procedures (1) Installation of salon seats: WARNING:
FOR SEAT FIXING ONLY THE PRESCRIBED SCREWS WITH NON -REMOVABLE WASHER SHALL BE USED. SALON SEATS SHALL BE INSTALLED ON A CARPETED FLOOR ONLY.
(a) Make sure that the clearance between the screw heads and the floor surface is sufficient. (b) Match the round holes of the legs with holes in the floor of fuselage fig. 404 pos.2. After that put on the screws fig. 404 pos.1 and 5 into the round holes of the legs and tighten the screws. NOTE:
For tightening the screws attaching the salon seats to the floor use the 12x11 CSN 230611.6 open-end spanner.
(2) Removal of salon seats: (a) Loosen and unscrew the screws fig. 404 pos.1 and 5 attaching the salon seats to the salon compartment floor. NOTE:
For loosening the screws attaching the salon seats to the floor use the 12x11, CSN 23 0611.6 open-end spanner.
(b) Remove the double salon seat fig. 404 pos.3 and.4) sets by pulling the seats upward. (c) Replace damaged attachment screws by new ones.
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5
FIG. 404
SALON SEATS (1) B515440N Screw (8 pc); (2) Hole; (3) (4) Double salon seats, (2) B093437N Screw (4 pc)
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PASSENGER’S SEATS DESCRIPTION AND OPERATION 1. General The passenger’s seat are designed as single-seat units situated on the LH side and as double-seat sets situated on the RH side. The single-seat units and double-seat sets differ from each other only by the legs by means of which the seats are fixed to the passenger compartment floor. The seat structure consists of a metallic skeleton filled with foamy material and coated with fabric. Design of seats protects luggage from moving round the floor. The seats are fitted with inflammable removable washable covers buttoned to them. Each passenger’s seat is provided with a safety belt. The safety belt consists of two straps, two anchoring buckles and a lock. The length of the safety belt is adjusted on the lock. The safety belt is fastened by coupling both lock parts. By depressing the red pushbutton on the top lock side the safety belt is loosened. The pockets for life jackets are attached to the underside of the seats (in the middle). The passenger seats can be provided with foldable serving plates and integral headrests.
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FIG. 1
PASSENGERS’ SEATS (1) Single-seat unit; (2) Double-seat set; (3),(4),(5) Legs; (6) Flange; (7) Safety belt; (8) Lock; (9) Removable cover
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FIG. 2
PASSENGERS’ SEATS WITH THE INTEGRAL HEADRESTS (IF INSTALLED) (1) Single-seat unit; (2) Double-seat set; (3),(4),(5) Legs; (6) Flange; (7) Safety belt; (8) Lock; (9) Removable cover
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PASSENGERS’ SEATS REMOVAL / INSTALLATION 1. Removal and installation of single and double passenger seat sets A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
12x11 CSN 230611.6 open-end spanner B 096 039 N special wrench
D. Referenced information E.
-
Procedures (1) Removal of the passengers’ seats. (a) Loosen the screws attaching the passengers’ seats to the passenger compartment floor and to the heating channels on both fuselage sides. NOTE:
For loosening the screws attaching the passengers’ seats to the heating channels on both fuselage sides use the B 096 039 N special wrench. For loosening the screws attaching the seats to the floor use the 12x11, CSN 23 0611.6 open-end spanner from the B 096 471 N kit.
(b) Shift the single-seat (or double-seat) sets backwards and then remove them by pulling the seats upwards. (c) Replace damaged attachment screws by new ones. (2) Installation of passengers’ seats. WARNING:
FOR SEAT FIXING ONLY THE PRESCRIBED SCREWS WITH NON-REMOVABLE WASHER SHALL BE USED. PASSENGERS’ SEATS SHALL BE INSTALLED ON A CARPETED FLOOR ONLY.
(a) Make sure that the clearance between the screw heads and the floor surface (or the heating channel) is sufficient. (b) Match the round holes on the rear side of the legs with the screws and then slip the legs on the screws and shift the seats forwards as far as the stop. Grooves on the front side of the legs must be set on the screws.
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MAINTENANCE MANUAL (c) Tighten the screws. NOTE:
For tightening the screws attaching the passengers’ seats to the heating channels on both fuselage sides use the B 096 039 N special wrench. For tightening the screws attaching the seats to the floor use the 12x11 CSN 230611.6 open-end spanner.
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SAFETY BELTS AMSAFE P/N 2019 SERIES DESCRIPTION AND OPERATION
1. Purpose The Lap Belt Assembly is intended for use by the seat occupant as a safety restraint. The system is designed to keep a human body (seat occupant) seated during all flight altitudes and landings. NOTE:
Safety belts AmSafe P/N 2019 Series: •
P/N 2019 - 1-XXX-XXXX (for passengers)
•
P/N 2019 - 5-011-XXXX (for child)
2. Operation A. Fastening In the seated position, pull the two lap belt portions over towards the body center. Insert the connector into the buckle until the latch block audibly engages the recess in the connector. For shortening the lap belt, pull at the free end of the webbing at the buckle. The belt is held at the chosen length by the jamming action of the load bar in the buckle. For lengthening the belt, grasp the buckle and rotate it approximately 45 degrees. Pulling at the buckle will lengthen the belt. If the extension assy is required, insert the connector of the extension into the buckle of the lap belt. Insert the connector of the lap belt into the buckle of the extension. B. Releasing For releasing the lap belt, lift the buckle cover. This action will release the connector, which can then be withdrawn from the buckle. Place the lap belt portions on the seat to prevent them from being damaged and soiled.
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SAFETY BELTS AMSAFE P/N 2019 SERIES FAULT ISOLATION
1. Task - Testing on Aircraft Use the following procedures to make an analysis of the performance of the lap belt while on the aircraft. Table 102 is a fault isolation guide, which has been keyed to the test procedures. Use it to isolate malfunctions. A. Equipment and Materials No equipment or materials required B. Inspection Intervals •
Concurrently with WP- 025.00.00.G
•
When malfunction is reported for failing requirements described in paragraph 1.
C. Procedure •
Follow procedures as dictated in table 101
•
If restraint fails any tests in table 101, remove restraint for further evaluation or overhaul by AmSafe Inc.
Table 101 - Restraint system test Test No.
Procedure
Limits
1.0
Lap belt and Extension
1.1
Insert connector into buckle.
Connector engages.
1.2
Release connector by lifting the buckle
Connector releases. The buckle cover
cover.
should return to the close position.
Repeat step 1.1 and 1.2 four times.
The connector engages and releases the
1.3
buckle cover returns to the close position. 1.4
1.5
Adjust webbing in buckle by pulling on the
Webbing must adjust and should not
free end of webbing.
exhibit excessive web fray or any cuts.
Repeat step 1.4 four times
Webbing must adjust and should not exhibit excessive web fray or any cuts.
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2. Procedure for Fault Isolation When a Test Fails: A. Find the number of the test in table 101 where the failure occurs. B. Use the fault isolation procedure in table 102 to isolate the malfunction. All fault isolation procedures are keyed to the Test No. column of Table 101.
Table 102 - Fault Isolation Test No. Where Failure Occurs 1.1
Probable Cause of Failure
Damaged buckle or connector
Repair Task
Replace lap belt and/or extension assembly.
1.2
Damaged buckle or connector
Replace lap belt and/or extension assembly.
1.3
Damaged buckle or connector
Replace lap belt and/or extension assembly.
1.4
Damaged buckle assembly or webbing
Replace lap belt and/or extension assembly.
1.5
Damaged buckle assembly or webbing
Replace lap belt and/or extension assembly.
CAUTION:
THE LAP BELT MAY NOT BE DISASSEMBLED. FURTHER REPAIR OF THIS ASSEMBLY MAY ONLY BE CARRIED OUT BY AM-SAFE INC. (USA), AM-SAFE LTD. (UK) OR AN AM-SAFE-APPROVED REPAIR STATION. AM-SAFE INC. IS NOT RESPONSIBLE FOR DAMAGE OR MALFUNCTIONS RESULTING FROM ANY UNAUTHORIZED ATTEMPT TO REPAIR OR DISASSEMBLE THE RESTRAINT SYSTÉM.
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SAFETY BELTS AMSAFE P/N 2019 SERIES CLEANING / PAINTING 1. Cleaning the safety belts A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Isopropyl Alcohol - Optional source, HAZARD CODE 130D Mild Soap - Optional source (household dishwasher liquid soap, household laundry detergent) Cloth lint-free - Optional source Sponge or soft brush - Optional source
WARNING:
BEFORE YOU USE A CLEANING MATERIAL, YOU MUST KNOW THE HAZARD CODE AND OBTAIN THE NECESSARY PROTECTION. REFER TO THE PAGE ABOUT HAZARD CODES FOR MATERIALS IN THE AMSAFE INC. ABBREVIATED COMPONENT MAINTENANCE MANUAL.
NOTE:
Equivalent alternatives are permitted for the equipment and materials in this list (in THE AMSAFE Inc. ABBREVIATED COMPONENT MAINTENANCE MANUAL.
C. Tools
Not applicable
D. Referenced information
-
E.
Procedures (1) Task To clean the restraint system, remove dirt and unwanted oil and grease. This helps the restraint system to last longer and prevents corrosion of the metal parts. The webbing is to be cleaned with fresh water and a mild soap. The metal fittings are cleaned with a cloth moistened with isopropyl alcohol. After cleaning the assemblies, protect them from moisture, dirt, or other contamination. Keep them protected until you do a visual check and return the restraint system to service. CAUTION:
1. THE RESTRAINT SYSTEM MUST NOT BE MACHINE-WASHED, BECAUSE THE WEBBING WILL SHRINK AND ITS PERFORMANCE CHARACTERISTICS WILL BE CHANGED SIGNIFICANTLY. 2. THE RESTRAINT SYSTEM MAY BE DRY-CLEANED. HOWEVER, THE WEBBING WILL LOSE ITS ABRASION-RESISTANCE COATING AFTER
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MAINTENANCE MANUAL EACH CLEANING AND ITS SERVICE LIFE WILL THEREFORE BE DECREASED. 3. REFER TO THE “CHECK” SECTION OF THIS MANUAL TO DETERMINE WHEN THE WEBBING OF A RESTRAINT SYSTEM MUST BE REPLACED BY AM-SAFE OR AN AM-SAFE APPROVED REPAIR STATION. 4. WHEN CLEANING THE RESTRAINT SYSTEM, CARE MUST BE TAKEN TO KEEP AWAY FOREIGN MATTER AND CLEANING MEDIA FROM THE HARDWARE ASSEMBLIES. 5. NO SOAP OR WATER IS TO BE USED ON METAL PARTS.
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PARTITION BETWEEN FLIGHT AND PASSENGER COMPARTMENT (if installed) DESCRIPTION AND OPERATION 1. General The partition which separates the passenger compartment from the flight compartment is located at the No. 7 fuselage frame station and is intended for securing the safety of the crew during flight. The partition consists of a central stationary part with folding wings on both sides. The stationary part of the partition consists of a central panel covering the vertical channel which houses flight control system elements and of two lateral parts. The two folding wings are hinged on the central stationary part. From the flight compartment side the wings are locked by turning and arresting a safety catch. From the passenger compartment side the wings are locked with a special key (B 091 164 N). NOTE:
When leaving the flight compartment, first the arrester of the safety catch must be disabled (by lifting and turning it). When the safety catch is arrested, the folding wings cannot be opened from the passenger compartment side.
If the passengers must be evacuated through the emergency exit door, the partition wings are unlocked and the emergency exit door opened (the emergency exit door can be opened even without unlocking the partition wings, if necessary). The partition wings are provided with threads for the installation of armor plates. The newspaper and magazine holder and the foldable serving plate are located on the fixed part of the frame.
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PARTITION BETWEEN FLIGHT AND PASSENGER COMPARTMENT (if installed) SERVICING 1. Inspection of the doors of the partition between flight and passenger compartment (if installed) A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
B 091 164 N Special key
D. Referenced information
025.22.00.A Periodical
E.
Procedures (1) Unlock the partition using a special key (B 091 164 N). (2) Inspect the left and the right-hand compartment partition doors. Defects not allowed: Deformed piano hinges, loosened or damaged riveted joints, loosened rivets, incorrect function of the wing locking mechanism. (3) Check correct functioning of the wing locking mechanism and make sure that the folding doors open and close easily. NOTE:
When leaving the flight compartment, first the arrester of the safety catch must be disabled (by lifting and turning it). When the safety catch is arrested the wings cannot be opened from the passenger compartment side.
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PASSENGER AND FLIGHT COMPARTMENT UPHOLSTERY DESCRIPTION AND OPERATION 1. General The passenger and flight compartment upholstery consists of: •
ceiling upholstery
•
lateral wall upholstery
•
lining of the partition between flight and passenger compartment
•
flight compartment window frame upholstery
•
carpets
The passenger compartment upholstery has mainly the form of panels. The panels above the windows are with battens, the panels under the windows panels and light assembly panels are made of LEXAN plastic. The panels under and above the windows are of sandwich structure, the ceiling panels are of frame structure made of duralumin sections. All the panels are covered with a leatherette. The interwindow panels made of Prepregs are fixed with screws. The ventilation channel and the light assembly panels have a glued-on leatherette. The air channel of the heating system has a protective varnish coating. The partition between flight and passenger compartment is covered both from the passenger and pilot compartments with leatherette. The flight compartment window frame upholstery is made of form-backed black plastic leather. The floors of both passenger and flight compartment are covered with the crest carpet biscuit, sample No.4. The carpets are removable after removal of the seat sets and of the fastening battens.
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FIG. 1
FLIGHT AND PASSENGER COMPARTMENT UPHOLSTERY (1) Window panel, (2) Inter-window panel, (3) Batten, (4) Front panel, (5) Above the door panel, (6) Rear panel, (7) Ceiling panel, (8) Front tape, (9) Lining, (10) Light assembly, (11) Light assembly screen, (12) Above the window panel, (13) Cover panel, (14) Front door upholstery, (15) Main door upholstery, (16) Dado, (17) Cover, (18) Lining, (19) Cockpit ceiling panel, (20) Flight compartment upholstery panel, right hand, (21) Flight compartment upholstery panel, rear left-hand, (22) Flight compartment upholstery panel, from left hand, (23) Pocket, (24) Sun visor, (25) Carpet, (26) Rear baggage compartment lining.
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ADDITIONAL EQUIPMENT DESCRIPTION AND OPERATION 1. Head wear shelf (rack) (if installed) The head wear shelf with rack is situated near the main door between the frames No. 18 and 21. Carry on baggage is transported in the passenger compartment. The head wear shelf with rack consist of a beam on which clothes hooks are fixed. Attached to the beam is the shelf proper consisting of a frame with nylon net.
FIG. 1
HEAD WEAR SHELF (RACK) (1) Beam, (2) Hook, (3) Shelf frame, (4) Nylon net
2. Newspaper and magazine holder (if installed) The newspaper and magazine holder is placed at the rigid part off the pilot’s partition. The holder is formed by a frame and netting. The netting is stabilized with a rubber cord in its upper open part.
3. Foldable serving plate (if installed) All the passenger seats are provided with foldable serving plates. The foldable serving plates for the passengers occupying the first seat row are placed at the fuselage sides and at the rigid part of the pilot’s partition. The foldable serving plates for the rest of passengers are always placed at the seats rear side of the previous seat row.
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FIG. 2
FOLDABLE SERVING PLATE ARRANGEMENT AT SEAT AND AT FUSELAGE SIDES A – Foldable serving plates arrangement at fuselage sides B - Foldable serving plates arrangement at a seat
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LAVATORIES DESCRIPTION AND OPERATION 1. General The toilet is situated in a separate section of the rear part of the passenger compartment. The toilet is accessible after opening a door. The closet basin proper is described in chapter 038. A box for paper towels and a box for toilet paper are installed on the side wall near the toilet.
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LAVATORIES SERVICING 1. Inspection of the equipment of the toilet section A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Detergent Clean cloth
C. Tools
Not applicable
D. Referenced information
025.40.00.A Periodical
E.
Procedures (1) Check the condition of the toilet section equipment i.e. the box for paper towels, the box toilet paper, pegs for clothes, mirror, handles and door lock. Defects not allowed: any defects of the toilet section equipment. Clean soiled upholstery and equipment with a detergent. Repair or replace damaged equipment.
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CARGO COMPARTMENTS DESCRIPTION AND OPERATION 1. General The aircraft passenger version has the front and rear baggage compartment – refer to section 025.51.00. Dimensions and volume of front baggage compartment: •
floor 0.8 x max. 1.85 m – volume 0.6 cu m
Dimensions and volume of rear baggage compartment: •
width 0.67 m x max. depth 0.98 m
•
height of bottom compartment 0.83 m
•
height of upper compartment max. 0.65 m
•
volume 0.77 cu m
The aircraft in cargo version has cargo compartments located in the passenger compartment – refer to section 025.52.00.
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CARGO COMPARTMENTS IN PASSENGER VERSION DESCRIPTION AND OPERATION 1. General The front and the rear baggage compartments (if installed) are used as cargo compartments. 3
The front baggage compartment is situated between the bulkheads No. 1 and 4. Its volume is 0.7 m , and its permissible load is 100 kg. It is accessible from the outside after opening of covers on the left-hand and right-hand sides. Optional is installed the fixing bags of the front baggage compartment (see Fig 1.) The rear baggage compartment is located between the frame No. 19 and bulkhead No. 21 and is divided by means of sandwich panel into two sections. Two detachable sandwich covers are provided to close both sections which can secure in place with lock. When stowing the baggage, remove and store the covers behind the passenger’s seat – see Fig. 2 – so that cover damage may be prevented. The technical compartments in which the different major components of the aircraft systems are installed have no special design and are a constituent part of the aircraft structure.
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FIG. 1
FIXING BAGS OF THE FRONT BAGGAGE COMPARTMENT (IF INSTALLED) (1) Binding belt (83159951); (2) Net (B 593 841 N); (3) Single-point grips (83159961); (4) Bags
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FIG. 2
REAR BAGGAGE COMPARTMENT COVER STORING (1) Rear baggage compartment covers, (2) Front wall of rear baggage compartment
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CARGO COMPARTMENTS IN PASSENGER VERSION SERVICING 1. Inspection of the front and rear baggage compartment structure A.
Fixture, Test and Support Equipment
Portable lamp, Stepladder (e.g. B097300N)
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.51.00.A Periodical
E.
Procedures (1) Set the stepladder (e.g. B097300N) near the front baggage compartment. (2) Open the LH and RH hand doors of the front baggage compartment. (3) Unlock and remove the upper and lower covers (if installed) of the rear baggage compartment. Defects not allowed: Difficult opening, sticking of covers and locks. (4) Inspect (with help of the portable lamp) the rear and front baggage compartment walls, liners, nets and shelves for sound condition. Defects not allowed: deformed walls and shelves, cracks in riveted joints, loosened rivets, deformed covers or liners, and damaged nets or the fixing of the nets. (5) Re-install and lock the lower and upper covers (if installed) of the rear baggage compartment. Defects not allowed: difficult closing, sticking (6) Close the LH and RH hand doors of the front baggage compartment. (7) Remove the stepladder.
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CARGO COMPARTMENTS IN CARGO VERSION DESCRIPTION AND OPERATION 1. Cargo version A.
General The cargo version of the aircraft is intended for quick transport of different cargo as goods and equipment of limited dimensions with the total mass up to 1250 kg, namely: •
1000 kg in a container
•
100 kg in the front baggage compartment
•
150 kg in the rear baggage compartment
The cargo version is characterized by a stationary transport container placed in the passenger compartment of the aircraft. The cargo version equipment is given in the legends of Figs. 1, 2 and 3. The cargo compartments include also the front baggage compartment located between the bulkheads No. 1 and 4, and the rear baggage compartment located between the frames No. 19 and 21. The rear baggage compartment is divided into two sections by means of a sandwich panel. Two removable sandwich covers are provided to close both sections. The covers can be secured with a lock.
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FIG. 1
CARGO VERSION EQUIPMENT (1) Container with cargo (sections A, B); (2) Seat for the person accompanying the cargo, B 094 125 N (aircraft technician); (3) Double passenger seat (if installed); (4) Rear baggage compartment (if installed); (5) Toilet (if installed); (6) Headwear shelf with rack
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FIG. 2
CARGO VERSION EQUIPMENT LAYOUT (PART I) Legend to this figure - see page 5
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FIG. 3
CARGO VERSION EQUIPMENT LAYOUT (PART II) Legend to this figure - see page 5
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MAINTENANCE MANUAL Legend to fig. 2,3: Item No.
Name
Dwg. No.
Quantity
1.
Side wall
B 095 021 N
1
2.
Dividing grid
B 095 023 N
1
3.
Rear face
B 095 022 N
1
4.
Floor cover
B 094 085 N
1
5.
Doorsill cover, long
B 095 010 N
1
6.
Doorsill cover, short
B 095 011 N
1
7.
Lateral strut
B 094 114 N
3
8.
Middle strut
B 094 104 N
2
9.
Fastening belt
B 095 099 N
28
10.
Washer
B 094 148 N
17
11.
Screw with washer
B 094 153 N
2
12.
Pallet floor
B 095 020 N
1
13.
Front face
B 095 026 N
1
14.
Front protective wall
B 095 024 N
1
15.
Rear protective wall
B 095 025 N
1
16.
Front strut
B 094 094 N
3
17.
Fixing eyebolt
B 094 144 N
15
18.
Double eyelet
B 094 156 N
2
19.
Single eyelet
B 094 158 N
6
20.
Net
B 003 056 N
2
NOTE:
The cargo version equipment components are transported in the 9-613-294 box. The B 094 125 N seat for the person accompanying the cargo is transported in the 9-613-025A box.
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FIG. 4
B 094 125 N SINGLE SEAT FOR THE PERSON ACCOMPANYING THE CARGO (1) Leg; (2) Seat; (3) Angle; (4) Screw; (5) Screw; (6) Screw; (7) Screw; (8) Fastening belt; (9) Lock
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MAINTENANCE MANUAL B.
Description The main part of the cargo version equipment is the pallet floor (12) - see fig. 2, 3. It is a riveted structure made of duralumin sections and sheets. In the pallet floor there are holes for attaching the pallet floor to the passenger compartment floor structure and to the left-hand heating channel. The pallet is fixed by means of packed screws through the holes provided in the side wall (1) the front face (13), the rear face (3) and in the dividing grid (2) via the pallet floor to the passenger compartment floor structure. The front face, the rear face and the side wall have microporous rubber stuck along their circumference so that they form together with the pallet floor a waterproof vat. The dividing grid divides - as a structures member - the loading area of the pallet floor into two halves. The grid is supported by two middle struts (8). The front face is supported by three struts (16) anchored by screws in riveted nuts in the passenger compartment floor structure. The side wall is supported by three lateral struts (7) anchored by screw in riveted nuts on the heating channel. Between the side wall and the fuselage right-hand side an aisle remains free for the crew to pass to the flight compartment. The passenger compartment floor structure is protected in the main door area from damage by a floor cover the structure of is a metal core sandwich. The door frame is fitted with a protective doorsill cover (the short one if only the entrance door is opened, whereas the long one if also the cargo door is opened). The cargo itself is secured by two polyamide nets (20), fixed by means of fastening belts (9) to the faces, side wall, passenger compartment floor structure and to the heating channel structure. The passenger compartment upholstery is protected against damage during loading and unloading as well during the flight by a protective wall (14), (15) screwed to the heating channel on the fuselage left-hand side. The seat for the person accompanying the cargo is located near the frame No. 17. NOTE:
The seat for the cargo accompanying person is a mirror image of the single passenger seat described in section 025.21.00.
Between the frames No. 18 and 19 a double passenger seat (see section 025.21.00) of the passenger version (when converting the passenger version into the cargo one this seat is not removed) is installed.
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MAINTENANCE MANUAL C. Loading and securing of the cargo NOTE:
Before loading the cargo it is necessary to install the floor cover (4) and the short (6) or long (5) doorsill cover in the main door area.
The pallet floor loading zone is divided into two sections A and B. Each of them may be loaded to max. 500 kg. The maximum load height in section A, B is 1000 mm. When transporting the cargo without installed dividing grid, the cargo mass must not exceed 500 kg. Cargo section dimensions: Section
Length, m
Width, m
A (front)
1.14
1.11
B (rear)
1.14
1.11
WARNING:
FOR THE SAKE OF SECURITY CARGO TRANSPORT WITHOUT INSTALLED AND FIXED REAR FACE IS STRICTLY FORBIDDEN.
If the transported cargo takes up one section only, it must always be loaded into section A, and the cargo must be fastened according to Fig. 6. WARNING:
DURING LOADING A SUDDEN LOWERING OF THE AIRCRAFT MAY TAKE PLACE AS THE LANDING GEAR SHOCK ABSORBERS ARE DEPRESSED DUE TO THE CHANGE IN AIRCRAFT WEIGHT, ESPECIALLY WHEN THE AIRCRAFT IS BEING REFUELLED SIMULTANEOUSLY! TO AVOID AIRCRAFT DAMAGE IT IS NECESSARY TO SEE THAT THE VERTICAL DISTANCE BETWEEN THE HIGHEST POINT OF THE LOADING TRUCK OR THE LOAD AND THE AIRCRAFT STRUCTURE IS AT LEAST 150 mm. LOADING AND UNLOADING OF THE AIRCRAFT MUST BE CARRIED OUT SO THAT NEITHER THE AIRCRAFT NOR ITS EQUIPMENT IS DAMAGED DURING LOADING, UNLOADING OR FLIGHTS. ANY DAMAGE OF THE AIRCRAFT MUST BE REPORTED TO THE GROUND STAFF FOREMAN A OR TO THE CREW.
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MAINTENANCE MANUAL D. Variations of cargo layout in dependence on cargo dimensions and mass. (1) Cargo of large dimensions and low mass WARNING: NOTE:
CARGO MASS SHALL NOT EXCEED 500 KG.
In order to achieve the necessary tension of the fastening nets the cargo must be by at least 400 mm higher than the pallet floor. The necessary height may be obtained by using an appropriate filling material.
Remove the dividing grid (2) incl. the middle struts (8). Load the cargo into both sections A and B (zone D). Always start loading from the front face. After loading reinstall the rear face. Fig. 5 shows the method of cargo layout and fixing.
FIG. 5
CARGO OF LARGE DIMENSIONS AND LOW MASS (a) Fixing cargo with a single fastening net Cover the cargo with one fastening net, tension it with help of the fastening belts fixed on the container sides. If the cargo is shorter, do not fix the rear two belts in the rear face eyelets but in two fixing eyebolts in the rear container part. (b) Fixing cargo with two fastening nets This method is used is case of a high cargo. Cover the cargo with two nets and interconnect them - in the longitudinal aircraft axis - with four fastening belts. Tension both nets with fastening belts fixed in the fixing eyelets on the container sides. (2) Cargo taking up both sections A, B with height and mass limitations observed First, load the cargo into the section A. Then cover the cargo with polyamide net (20) and tension it thoroughly using fastening belts (9). Then load the section B. After loading cover the cargo with polyamide net (20) and tension it thoroughly using fastening belts (9). Prior to loading it has to be considered whether it is necessary to remove the dividing grid and the
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MAINTENANCE MANUAL rear face. If so, remove them. After loading reinstall the dividing grid. The methods of cargo layout and fixing are shown in Fig. 6.
FIG. 6
CARGO TAKING UP BOTH SECTIONS A AND B WITH HEIGHT AND MASS LIMITATIONS OBSERVED (3) Low cargo (up to 400 mm) exceeding dimensions of one section Due to low cargo height the method of fixing the fastening belts in the eyelets on the container sides is unsuitable. When laying on and fixing the cargo proceed as follows: (a) For cargo layout use the whole pallet area (section C) according to Fig. 7. Place the cargo as near to the fuselage centre line as possible. (b) Cover the cargo with one fastening net and tension it with the fastening belts fixed to the lower side wall brackets and to the eyelets on LEFT-HAND side. On the front and the rear side tension the net using 3 + 3 fastening belts fixed on the front and rear faces. (c) In this way, a cargo of max. 2.6 x 0.75 m area and of max. 400 mm height can be loaded. The cargo mass shall not exceed 500 kg.
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FIG. 7
LOW CARGO (UP TO 400 MM) EXCEEDING DIMENSIONS OF ONE SECTION (d) Cargo unfixing and unloading Cargo unfixing and unloading is to be carried out reversing the procedures outlined in paragraph D. (e) Loading instructions IT IS FORBIDDEN: - TO LOAD THE CONTAINER WITH UNPACKED GOODS OR CARGO PACKED IN PACKINGS WITH SHARP EDGES, PROTRUDING NAILS, SCREWS, METAL DANDS, WIRES ETC. - TO LOAD THE CONTAINER WITH LOOSE MATERIALS WITHOUT CORRESPONDING PACKINGS. - TO LOAD THE CONTAINER WITH LIQUIDS TRANSPORTED IN GLASS VESSELS. The person accompanying cargo is obliged to watch the cargo during the flight. The loosening of cargo is to be reported to the crew using the crew call pushbutton (3 short signals) and corrective action shall be undertaken immediately.
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CARGO COMPARTMENTS IN CARGO VERSION (if installed) SERVICING 1. Inspection of the polyamide net A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.52.00.A Periodical
E.
Procedures (1) Check the polyamide net. (2) Defects not allowed: broken net fibbers.
2. Inspection of the fastening belts A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.52.00.B Periodical
E.
Procedures (1) Check the fastening belts. (2) Defects not allowed: damaged fastening belts.
3. Inspection of cargo version equipment A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Not applicable
D. Referenced information
025.52.00.C Periodical
E.
Procedures (1) Check tightening of all screws and bolts.
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MAINTENANCE MANUAL (2) Check the struts, eyelets and fastening belts for cracks. (3) By visual inspection make sure of sufficient sealing function of microporous rubber. (4) Check that there is no permanent deformation or damage of cargo version equipment components. (5) Defects not allowed: - insufficiently tightened screws, - crack on struts, eyelets, fastening belts, - insufficient sealing function of microporous rubber, - permanent deformation or damage of any component of cargo version equipment.
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CARGO COMPARTMENTS IN CARGO VERSION REMOVAL / INSTALLATION 1. Cargo version equipment installation A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Tool kit B 097 600 N (spanners No. 8, 9, 10, 12, 13)
D. Referenced information E.
-
Procedures NOTE:
Carry out the installation of cargo version equipment after previous: - removal of 5 rows of single seats on the LEFT-HAND side of the passenger compartment (according to the work procedure mentioned in section 025.21.00) - removal of 6 rows of double seats on the RIGHT-HAND side of the passenger compartment (in accordance with the work procedure mentioned in section 025.21.00)
(1) Open the main door and secure it in the opened position. (2) Position the pallet floor (12) in the cabin - see Fig. 2, 3, so that the side edge of the pallet floor lies on the LEFT-HAND heating channel and the front edge of the pallet floor be at a distance of 317 mm from the first row of 3 screw holes on the aircraft cabin floor. (3) Position the front face (13) onto the pallet floor and attach it with 3 screws to the aircraft cabin floor and with 2 screws to the heating channel. (4) Attach the front struts (16) to the front face. Connect the front struts with the front face by means of catch pins. (5) Install the front (14) and rear (15) protective walls on the LEFT-HAND heating channel. Start installation on the upper window edge and continue on the heating channel. (6) Screw six single eyelets (19) and two double eyelets (18) into the free holes on the heating channel. (7) After fixing the front strut (16) forks adjust the strut length so that the front face be vertical with respect to the cabin floor. After adjustment tighten the nuts and secure them with lockwashers. (8) Position the side wall (1) on the pallet floor. Attach the side wall with 6 screws to the cabin floor. Connect the side wall with the front face with two screws. (9) Screw the rear face (3) to the pallet floor (12). Attach the rear face with 3 screws to the cabin floor, with 2 screws to the vertical edge of the side wall and with one screw to the heating channel.
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MAINTENANCE MANUAL (10) Screw the lateral struts (7) to the RIGHT-HAND heating channel. Adjust the length of the lateral struts. Fix the connections with catch pins. (11) Screw the dividing grid (2) to the vat formed by the pallet floor, the front face, the side wall and the rear face. (12) Attach the dividing grid (2) to the pallet floor with two screws. (13) Attach two middle struts (8) to the dividing grid. Screw the middle struts to the cabin floor (insert a washer under the screw head). (14) Adjust the length of the middle struts and fix the strut connections with the dividing grid with catch pins. (15) Screw 8 fastening eyebolts with washers through the pallet floor holes to the cabin floor. (16) Attach the floor cover (4) to the cabin floor behind the entrance door with two screws. (17) Fix 28 fastening belts to all eyelets on the heating channel, the side wall the rear face, the front face, the dividing grid and the middle struts. (18) Install the seat for the person accompanying cargo following the work procedure mentioned in this section. (19) Install the short (6) or the long (5) doorsill cover on the door frame sill. NOTE:
Interconnect the items (1), (2), (3), (4), (7), (8), (12), (13), (14), (15), (16) with screws (see 025.52.00, Fig. 2, 3) in such away so that during the assembly the screws are tightened only partially at first. After completion of the assembly tighten screws thoroughly.
2. Cargo version equipment removal A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
Tool kit B 097 600 N (spanners No. 8, 9, 10, 12, 13)
D. Referenced information E.
-
Procedures (1) Remove the short (6) - fig. 3 or the long (5) doorsill cover from the door frame sill. (2) Remove the seat for the cargo accompanying person following the work procedure mentioned in this section. (3) Remove 28 fastening belts from all eyelets to which they have been fastened. (4) Unscrew two screws (11) of the floor cover (4) and remove the cover.
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MAINTENANCE MANUAL (5) Unscrew 8 fixing eyebolts (17) on the pallet floor and remove the washers. (6) Remove the catch pins to disconnect the dividing grid (2) and the middle struts (8). (7) Unscrew the screws attaching the middle struts (8) to the pallet floor (12) and remove the struts with washers. (8) Disconnect the pallet floor (12) and the dividing grid (2) by loosening two screws. (9) Remove the dividing grid. (10) Remove the catch pins to disconnect the lateral struts from the side wall and unscrew two screws to disconnect the lateral struts from the heating channel. (11) Unscrew two screws on the pallet floor (12), two screws on the side wall (1) vertical edge and one screw on the heating channel to loosen the rear face (3). Remove the rear face. (12) Unscrew six screws on the pallet floor (12) and two screws on the front face (13) to loosen the side wall (1). Remove the side wall. (13) Unscrew six single eyelets (19) and two double eyelets (18) on the heating channel to disconnect the front (14) and rear (15) protective walls. (14) Remove the front and the rear protective walls. (15) Unscrew 3 screws on the pallet floor (12) and two screws on the heating channel and remove the catch pins from the front struts (16) to loosen the front face (13). (16) Unscrew three screws on the floor to loosen the front struts (16). Remove the struts. (17) Remove the loosened pallet floor (1). (18) Shut the main door and fix it in closed position. NOTE:
Having removed the cargo version equipment: - install 6 rows of double seats on the right-hand side of the passenger compartment (following the work procedure mentioned in section 025.21.00) - install 5 rows of single seats on the left-hand side of the passenger compartment (following the work procedure mentioned in section 025.21.00)
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3. Installation and removal of the seat for the person accompanying cargo A.
Fixture, Test and Support Equipment
Not applicable
B.
Materials
Not applicable
C. Tools
B 096 039 N spanner 12x11 CSN 203611.6 spanner
D. Referenced information E.
-
Procedures (1) Installation of the cargo accompanying person seat. (a) Install the seat so that the round holes of the leg are matched with the floor holes (in the right-hand rear part of the cargo compartment). (b) Insert and partially tighten the screws attaching the seat to the floor and shift the seat forwards so that the screws are set in the leg grooves as far as the stop. Screw in the screws attaching the seat to the heating channel and tighten all 4 screws, two screws on the heating channel, with the B 096 039 N spanner and two screws on the floor with the 12x11, CSN 230611.6 spanner. NOTE:
If there are no holes in the carpet for fixing the seat to the floor, they must be made according to the location of the anchor nuts.
(2) Removal of the cargo accompanying person seat. (a) Using the B 096 039 N spanner loosen two screws attaching the seat to the heating channel and using the 12x11 CSN 203611.6 spanner, loosen two screws attaching it to the floor. Shift the loosened seat backwards, and remove it (by lifting it a little). Replace damaged attachment screws by new ones.
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EMERGENCY EQUIPMENT DESCRIPTION AND OPERATION 1. General Aircraft emergency equipment consists of the following items: •
first-aid kits
•
emergency axe
•
crew call signalling
•
inflatable life jackets (for example ASZh-63P)-(if installed)
•
inflatable life rafts (for example SP-12)-(if installed) and emergency packages (for example NAZ-7) (if installed)
•
emergency exists (see chapter 052)
•
emergency locator transmitter ELT (model specification is optional)
•
inscriptions explaining the emergency exit opening sequences and markings of the places where the emergency axe and first-aid kits are located, as well as of the cut-out area for an emergency manhole
•
hand fire extinguisher (see chapter 026)
•
emergency lighting (see chapter 33)
FIG. 1
EMERGENCY EQUIPMENT LOCATION (the crew call pushbuttons are shown in fig. 2) NOTE:
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Location of the emergency equipment may vary according to the aircraft version
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MAINTENANCE MANUAL
2. List of components No.
Name
Type (Dwg. No.)
Qty
Location
1.
First-aid kit
B590451N or B405722N
1
In the ceiling above the main door
2.
First-aid kit
B091694N
2
In the ceiling near the vertical control channel
3.
Axe
-
1
Behind the copilot’s seat
4.
Life jackets (if installed)
ASZh-63P (for example)
-
Under the seats
5.
Life rafts (if installed)
SP-12 (for example)
2
On the passenger’s seats of the 7th row-passenger version On the left-hand passenger’s seat of the 7th row-passenger version On the single passenger seatscargo version
1 1 6.
Emergency packages (if installed) NAZ-7 (for example)
3 2
7.
Pushbutton, PUSH-TO-CALL-CREW
5 KS (8)
1 1
On the right-hand passenger’s seat of the 7th row-passenger version On the single passenger versioncargo v