Trudeau Civil Case Document 737 737 1 and 737 2 Partial 08-05-13
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Document No. AMS-737-345-28881
AIRCRAFT MANUAL
SUPPLEMENT To comply with EASA Regulation CS-25.1529 and CS-25 Appendix H and FAA Regulation CDR 14 25.1529 and to support the continued airworthiness of:
B737-300/400/500 – MSN 28881 Document No: AMS-737-345-28881
Intro Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
®
Document No. AMS-737-345-28881
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
HIGHLIGHTS Issue 3 COMPLETE RE-ISSUE OF MANUAL SUPPLEMENT Issue 4 WDM – 23-24-11 – ADDED AMM – 25-11-11 – ADDED, 34-22-00 – ADDED Issue 5 AMM – 23-24-00 – AMENDED AMM – 23-24-11 – AMENDED AMM – 34-22-00 – AMENDED Issue 6 Wiring Diagram Manual 22-11-75 – Added Aircraft Maintenance Manual 22-11-01 – Added Issue 7 Aircraft Maintenance Manual 23-71-00 - Changed Issue 8 Wiring Diagram Manual 25-33-58 – Added Illustrated Parts Catalogue 25-31-11-99Z - Added Aircraft Maintenance Manual 23-24-00 THRU 23-24-11 Changed
Document No. AMS-737-345-28881
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®
RECORD OF REVISION
Issue DIN No. Date Issue DIN No. Date Initial DIN-0166 JUL 01/06
2 DIN-0494 MAR 01/07 3 DIN-2279 FEB 01/11 4 DIN-2289 MAR 01/11 5 DIN-2358 APR 01/11 6 DIN-2761 JAN 01/12 7 DIN-3606 APR 01/13 8 DIN-3888 SEP 01/13
The Aircraft Manual Supplement (AMS) is to be used in conjunction with the related aircraft’s manuals. The information contained within this manual relates to various alterations/changes/modifications that have been carried out on the associated aircraft. A list of effective alterations/changes/modifications can be found in the Introduction pages to this manual. These alterations/changes/modifications are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related convention. This manual complies with EASA Regulations CS-25.1529 and CS-25 Appendix H, which in turn mirror the FAA regulation CDR 14 25.1529. DINs are Document Issue Notes and are administration documents used to issue this manual to the customer and are used for record purposes only.
RRA-00 Page 1
Document No. AMS-737-345-28881
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
INTRODUCTION
1. General A. This publication was prepared by Aerospace Design and Engineering Consultants (AeroDEC®) Ltd and is in accordance with
Air Transport Association of America Specification No. 100, Specification for Manufacturers Technical Data. The data contained within is related to certain changes/modifications/alterations that are in addition to the associated airplane’s type design.
NOTE: THIS MANUAL IS PREPARED SPECIFICALLY TO COVER THE AIRPLANE LISTED IN THE "INTRODUCTION"
SECTION, FOR THE OWNER/OPERATOR NAMED ON THE TITLE PAGE.
THIS MANUAL IS NOT SUITABLE FOR USE, INCLUDING WITHOUT LIMITATION, GENERAL INSTRUCTIONS OR TRAINING, FOR ANY AIRPLANES NOT LISTED HEREIN.
B. The convention for the use of this publication is in the same convention (ATA 100) as the associated manufacturers AMM,
WDM, and IPC. Therefore, this publication is a SUPPLEMENT to the associated AMM, WDM, and IPC, and instructions on how to use this manual are equivalent to the instructions on how to use the manufacturers AMM, WDM and IPC.
C. This Manual Supplement has been raised to give historic design information pertaining to the following related aircraft
manuals: WDM – Wiring Diagram Manual
WL– Wire List IPC – Illustrated Parts Catalogue AMM – Aircraft Maintenance Manual
D. For information on the approval of the technical content of this document, please refer to the Change/Mod/Alteration listing E. Aircraft Effectivity Information:
MODEL/ TYPE
CUST EFFECT CODE
CUST EFFECT CODE
(IPC ONLY)
VARIABLE ENGR
NUMBER
ENGINE SET
NUMBER LINE
NUMBER
MFG SERIAL
NUMBER REGISTRY NUMBER
CUSTASSIGNED AIRPLANE
IDENT
B737-49R 001 PV301 2833 28881
INTRO-00 Page 1 SEP 01/13
Document No. AMS-737-345-28881
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
Front Page IPC Front Page Highlights IPC Contents 1 Record of Revision and Approval 1 IPC Contents 2 Introduction 1 SEP 01/13 Chapter 23 Front Page Introduction 2 SEP 01/13 23-24-00-01Z 0 FEB 01/11 List of Effective Pages 1 SEP 01/13 23-24-00-01Z 1 FEB 01/11 List of Effective Pages 2 SEP 01/13 23-24-00-02Z 0 FEB 01/11 Report/Feedback Sheet 23-24-00-02Z 1 FEB 01/11 WDM Front Page 23-24-00-03Z 0 FEB 01/11 WDM Contents 1 23-24-00-03Z 1 FEB 01/11 WDM Contents 2 23-71-13-01Z 0 FEB 01/11 Chapter 22 Front Page 23-71-13-01Z 1 FEB 01/11 22-11-52 1 FEB 01/11 Chapter 25 Front Page 22-11-62 1 FEB 01/11 25-11-11-18Z 0 FEB 01/11 22-11-75 1 JAN 01/12 25-11-11-18Z 1 FEB 01/11 Chapter 23 Front Page 25-11-11-66Z 0 FEB 01/11 23-22-01 1 FEB 01/11 25-11-11-66Z 1 FEB 01/11 23-24-11 1 MAR 01/11 25-11-21-22Z 0 FEB 01/11 23-71-01 1 Sht 1 FEB 01/11 25-11-21-22Z 1 FEB 01/11 23-71-01 1 Sht 2 FEB 01/11 25-31-11-07Z 0 FEB 01/11 Chapter 25 Front Page 25-31-11-07Z 1 FEB 01/11 25-33-58 113 Sht 6 SEP 01/13 25-31-11-07Z 2 FEB 01/11 25-33-58 113 Sht 7 SEP 01/13 25-31-11-07Z 3 FEB 01/11 Chapter 31 Front Page 25-31-11-07Z 4 FEB 01/11 31-31-01 1 FEB 01/11 25-31-11-99Z 0 SEP 01/13 Chapter 33 Front Page 25-31-11-99Z 1 SEP 01/13 33-17-01 1 FEB 01/11 25-31-21-04Z 0 FEB 01/11 Chapter 34 Front Page 25-31-21-04Z 1 FEB 01/11 34-22-11 1 FEB 01/11 25-31-21-04Z 2 FEB 01/11 34-22-21 1 FEB 01/11 25-31-41-07Z 0 FEB 01/11 34-26-11 1 FEB 01/11 25-31-41-07Z 1 FEB 01/11 34-26-13 1 FEB 01/11 25-31-41-07Z 2 FEB 01/11 34-26-21 1 FEB 01/11 Chapter 31 Front Page 34-26-23 1 FEB 01/11 31-24-24-99Z 0 FEB 01/11 34-49-04 1 FEB 01/11 31-24-24-99Z 1 FEB 01/11 34-53-12 1 FEB 01/11 Chapter 33 Front Page 34-53-16 1 FEB 01/11 33-11-00-05Z 0 FEB 01/11 34-53-22 1 FEB 01/11 33-11-00-05Z 1 FEB 01/11 34-61-02 1 FEB 01/11 Chapter 34 Front Page 34-61-11 1 FEB 01/11 34-28-31-02Z 0 FEB 01/11 Chapter 49 Front Page 34-28-31-02Z 1 FEB 01/11 49-31-12 1 FEB 01/11 34-53-21-01B 0 FEB 01/11 Wire List (WL) 34-53-21-01B 1 FEB 01/11 Index Chapter 35 Front Page W0007 1 FEB 01/11 35-12-00-02Z 0 FEB 01/11 W0009 1 FEB 01/11 35-12-00-02Z 1 FEB 01/11 W0011 1 FEB 01/11 35-12-00-02Z 2 FEB 01/11 W0069 1 FEB 01/11 35-12-00-20Z 0 FEB 01/11 W0967 1 FEB 01/11 35-12-00-20Z 1 FEB 01/11 W9001 1 FEB 01/11 Chapter 49 Front Page W9002 1 FEB 01/11 49-70-00-02Z 0 FEB 01/11 W9076 1 FEB 01/11 49-70-00-02Z 1 FEB 01/11
LEF-00 Page 1 SEP 01/13
Document No. AMS-737-345-28881
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
Chapter 53 Front Page 34-53-02 5 FEB 01/11 53-42-00-80Z 0 FEB 01/11 34-53-02 6 FEB 01/11 53-42-00-80Z 1 FEB 01/11 34-53-02 7 FEB 01/11 53-42-00-81Z 0 FEB 01/11 34-53-02 8 FEB 01/11 53-42-00-81Z 1 FEB 01/11 34-53-02 9 FEB 01/11 AMM Front Page 34-53-02 501 FEB 01/11 AMM Contents 1 34-53-02 502 FEB 01/11 AMM Contents 2 34-53-02 503 FEB 01/11 Chapter 22 Front Page 34-53-02 504 FEB 01/11 22-11-01 501 JAN 01/12 34-53-02 505 FEB 01/11 22-11-01 502 JAN 01/12 34-53-02 506 FEB 01/11 Chapter 23 Front Page 34-53-02 507 FEB 01/11 23-24-00 1 SEP 01/13 34-53-02 508 FEB 01/11 23-24-00 101 SEP 01/13 34-53-02 509 FEB 01/11 23-24-00 201 SEP 01/13 34-62-01 501 FEB 01/11 23-24-00 501 SEP 01/13 34-62-01 502 FEB 01/11 23-24-11 401 SEP 01/13 34-62-01 503 FEB 01/11 23-71-00 501 APR 01/13 Chapter 49 Front Page 23-71-00 502 APR 01/13 49-72-11 401 FEB 01/11 23-71-00 503 APR 01/13 49-72-11 402 FEB 01/11 23-71-00 504 APR 01/13 49-72-11 403 FEB 01/11 23-71-00 505 APR 01/13 49-72-11 404 FEB 01/11 23-71-00 506 APR 01/13 49-72-11 405 FEB 01/11 23-71-00 507 APR 01/13 Chapter 25 Front Page 25-11-11 201 MAR 01/11 25-11-11 202 MAR 01/11 25-11-11 203 MAR 01/11 25-11-11 204 MAR 01/11 25-11-11 205 MAR 01/11 25-11-11 206 MAR 01/11 25-11-11 207 MAR 01/11 25-11-11 208 MAR 01/11 25-11-11 209 MAR 01/11 25-11-11 210 MAR 01/11 25-11-11 211 MAR 01/11 25-11-11 212 MAR 01/11 Chapter 31 Front Page 31-24-24 201 FEB 01/11 31-24-24 202 FEB 01/11 Chapter 34 Front Page 34-22-00 501 APR 01/11 34-22-00 502 APR 01/11 34-49-03 501 FEB 01/11 34-49-03 502 FEB 01/11 34-53-02 1 FEB 01/11 34-53-02 2 FEB 01/11 34-53-02 3 FEB 01/11 34-53-02 4 FEB 01/11
LEF-00 Page 2 SEP 01/13
Document No. AMS-737-345-28881
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
REPORT/FEEDBACK SHEET
This Report/Feedback Sheet is provided for the purpose of communicating to Aerospace Design and Engineering Consultants (AeroDEC) Ltd. any errors or suggested improvements arising fro this Aircraft Manual Supplement
AMS Section: Applicants Name:ATA Ref(s): Applicants Signature: Date:(Please provide details below):
FEEDBACK ONLY (Please provide details below):
WIRING
DIAGRAM
MANUAL
Contents
WDM-CONTENTS Page 1
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
Chapter 11 PLACARD & MARKINGS
Chapter 21 AIR CONDITIONING
Chapter 22 AUTO FLIGHT
22-11-52 – DFCS “A” MCP/FCC INTERFACE
22-11-62 – DFCS “B” MCP/FCC INTERFACE
22-11-75 – DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS
Chapter 23 COMMUNICATIONS
23-22-01 – SELCAL
23-24-11 – EMERGENCY LOCATOR TRANSMITTER
23-71-01 – COCKPIT VOICE RECORDER
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-33-58 – DRIESSEN AIRCRAFT SYSTEMS CMM P/N 101719 PAGE 113 SHEET 6
25-33-58 – DRIESSEN AIRCRAFT SYSTEMS CMM P/N 101719 PAGE 113 SHEET 7
Chapter 26 FIRE PROTECTION
Chapter 27 FLIGHT CONTROLS
Chapter 28 FUEL
Chapter 29 HYDRAULIC POWER
Chapter 30 ICE AND RAIN PROTECTION
Chapter 31 INDICATING/RECORDING SYSTEMS
31-31-01 – DFDRS INTERCONNECT GROUP 1
Chapter 32 LANDING GEAR
Chapter 33 LIGHTS
33-17-01 – MAP, FLIGHT KIT, AND READING LIGHTS
Chapter 34 NAVIGATION
34-22-11 – EFIS POWER/PROGRAM PIN - LEFT
34-22-21 – EFIS POWER/PROGRAM PIN - RIGHT
34-26-11 – INERTIAL REFERENCE SYSTEM NO.1 POWER
34-26-13 – INERTIAL REFERENCE NO.1 OUTPUT BUSSES
34-26-21 – INERTIAL REFERENCE SYSTEM NO.2 POWER
34-26-23 – INERTIAL REFERENCE NO.2 OUTPUT BUSSES
34-49-04 – GROUND PROXIMITY WARNING
34-53-12 – ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
WDM-CONTENTS Page 2
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
34-53-16 – NO.1 AND NO.2 ATC ENHANCED SURVEILLANCE BUSSES
34-53-22 – ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-61-02 – FLIGHT MANAGEMENT COMPUTER SYSTEM DATA BUS AND CONTROL
34-61-11 – FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS
Chapter 35 OXYGEN
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
Chapter 49 AIRBORNE AUXILIARY POWER
49-31-12– APU – MANUAL START-STOP
Chapter 52 DOORS
Chapter 53 FUSELAGE
Chapter 54 NACELLES / PYLONS
Chapter 55 STABILIZERS
Chapter 56 WINDOWS
Chapter 57 WINGS
Chapter 71 POWER PLANT
Chapter 73 ENGINE FUEL AND CONTROL
Chapter 74 IGNITION
Chapter 75 AIR
Chapter 77 ENGINE INDICATING
Chapter 78 EXHAUST
Chapter 79 OIL
Chapter 80 STARTING
Chapter 91 CHARTS
Chapter 93 PANELS
CHAPTER
AUTO FLIGHT
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DFCS “A” MCP/FCC INTERFACE 22-11-52 INCORPORATES: 22-11-52 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DFCS “B” MCP/FCC INTERFACE 22-11-62 INCORPORATES: 22-11-62 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS
22-11-75 INCORPORATES: 22-11-75 AERODEC MOD 1093
Page 1 Page 1
JAN 01/12 JAN 01/12 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
M924FLIGHT CONTROL COMPUTER "A"
W011
W011−737−20
D1671A
2
18
19
26
STD OPT ILS DEVN WARN
25
BIT 1
22
D1795A
D1795B
44
61
STD OPT ALT ALERT
CONFIG PINS
G/S SUPERFLAG
2
D1671B
28
30
32
35
44
62
27
29
33
42
57
BIT 2
STD OPT AIRSPEED WARNSTD OPT CWS WARN
STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO
STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL
STD OPT ODD PARITYSTD OPT EFIS
STD OPT DUAL CHANNELAUTO F/D TOGA
LOC BEFORE G/S
6
7
LVOR/LOC DEVN
R
10
11
BDATA BUS IRU−L−3
A
12
34
20
FRN IRS XFR−A
FMC/ANCDU SELAFDS WARN
43
67
51
R/A FLAG
NAV SELF TESTILS TEST INHIBIT
D1791A
DNG/S DEVN
UP
LORADIO ALTITUDE
HI
1
1
6
7
58
BDATA BUS IRU−L−2
A
9
D1791B
8 BDATA BUS FMC−1
A
26
D1793A
25 BDATA BUS DAA−L−2
A
54 DME HOLD
D1793B
67 26V AC IN LNAV REF
2
6
LOLNAV STRG CMD
HI
30
34
35
36
39
42
51
52
LVOR/LOC DEVN
R
VOR/LOC SUPERFLAG
1ADI BAR GRADIENT
2AUTO/MANUAL TUNE
ADATA BUS ANCDU−1
B
FWD LOC ANTENNA SELECT
LOCAL IRS XFR
D4317P
1
J
3
5
7
9
11
14
16
13
2
4
6
8
12
15
17
Z9
Z4
Z3
XA1
XD5
XA5
E1−3 SHELF
W069
34−31−05
34−33−11
34−31−08
34−26−13
34−31−04
34−26−23
34−33−11
34−31−09
34−61−02
34−61−05
34−31−04
34−26−12
34−31−08
34−26−12
34−31−08
34−31−01
NOT USED
NOT USED
NOT USED
NOT USED
NOT USED
GDX22−DC
GDX22−DC
GD701−DC
GD701−DC
GD701−DC
T1015STA 314.5WL 182.5LBL 19.2
P7 GLARESHIELD PANEL
M198DFCS MODE CONTROL PANEL
27
D1815
26
29
34−31−11
49
31
50
30
51
27
D299
34−31−11
26
29
30
31
49
50
51
15
1433−11−31
D301
6LCD TEST 33−18−05
RESOLVER
GND
5V ACLIGHTING
731−20
738−20
725−20
729−20
727−20
730−20
753−20
726−20
735−20
733−20
796−20
736−20
732−20
734−20
728−20
W011−739−20
W011−013−20
W011−003−20
3110
NOTES:UNLESS OTHERWISE SPECIFIED, ALL REFERENCE DESIGNATIONS ARE PREFIXED 3343−.UNLESS OTHERWISE SPECIFIED, ALL WAYCODES ARE W9.PIN LOCATIONS SUFFIXED BY (−) DENOTES LOWER CASE LETTERS.THE FOLLOWING ENGINEERING DRAWINGS WERE USED: 83340200/T/2, 83340204/A/2, 82430054/G/4 AND AL344−1264.INDICATES PROTECTIVE TUBING.
W737−071−22
072−22
075−22
074−22
073−22
076−22
077−22
078−22
079−22
080−22
081−22
082−22
084−22
085−22
086−22
087−22
W737−083−22
M923FLIGHT CONTROL COMPUTER "B"
W069−557−20
D1655A
2
D1661A
D1661B
44
61
G/S SUPERFLAG
2
D1655B
6
7
LVOR/LOC DEVN
R
10
11
BDATA BUS IRU−L−3
A
12
34
20
FRN IRS XFR−B
FMC/ANCDU SELAFDS WARN
43
67
51
R/A FLAG
NAV SELF TESTILS TEST INHIBIT
D1657A
DNG/S DEVN
UP
LORADIO ALTITUDE
HI
1
1
6
7
58
BDATA BUS IRU−R−2
A
9
D1657B
8BDATA BUS FMC−1
A
26
D1657A
25BDATA BUS DAA−R−2
A
54DME HOLD
D1657B
6726V AC IN LNAV REF
2
6
LOLNAV STRG CMD
HI
30
34
35
36
39
42
51
52
LVOR/LOC DEVN
R
VOR/LOC SUPERFLAG
1ADI BAR GRADIENT
2AUTO/MANUAL TUNE
ADATA BUS ANCDU−2
B
FWD LOC ANTENNA SELECT
LOCAL IRS XFR
D4117P
32
J
34
36
38
40
42
45
47
44
33
35
37
39
43
46
48
34−31−05
34−33−21
34−31−08
34−26−23
34−31−04
34−26−13
34−33−21
34−31−09
34−61−02
34−61−06
34−31−04
34−26−12
34−31−08
34−26−12
34−31−08
34−31−01
NOT USED
NOT USED
NOT USED
NOT USED
NOT USED
GDX6−DC
GDX6−DC
541−20
539−20
535−20
548−20
537−20
540−20
511−20
536−20
545−20
524−20
554−20
542−20
544−20
538−20
549−20
W069−560−20
W011−011−20
W011−009−20
41
W373−032−22
033−22
036−22
035−22
034−22
037−22
038−22
039−22
040−22
041−22
042−22
043−22
045−22
046−22
047−22
048−22
W373−044−22
W737−061−20
W737−062−20
W737−063−20
XB1
XA2
XC2
XB5
Z9
Z4
Z3
XA1
XD5
XA5
GD701−DC
GD701−DC
GD701−DC
T1017STA 314.5WL 182.5LBL 19.2
W737−061−20
062−20
W373−063−20
XB1
XA2
XC2
XB5
18
19
26
STD OPT ILS DEVN WARN
25
BIT 1
22
STD OPT ALT ALERT
CONFIG PINS
28
30
32
35
44
62
27
29
33
42
57
BIT 2
STD OPT AIRSPEED WARNSTD OPT CWS WARN
STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO
STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL
STD OPT ODD PARITYSTD OPT EFIS
STD OPT DUAL CHANNELAUTO F/D TOGA
LOC BEFORE G/S
31
CHAPTER
COMMUNICATIONS
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
SELCAL 23-22-01 INCORPORATES: 23-22-01 AERODEC MOD 0935
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
EMERGENCY LOCATOR TRANSMITTER 23-24-11 INCORPORATES: 23-24-11 AERODEC MOD 0889
Page 1 Page 1
MAR 01/11 MAR 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0916
Page 1 Page 1 Sheet 1 Sheet 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
AG
M S
ER
VIC
ES
DR
AW
ING
: A
GM
10-
B7
3W-0
138
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0916
Page 1 Page 1 Sheet 2 Sheet 2
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
AG
M S
ER
VIC
ES
DR
AW
ING
: A
GM
10-
B7
3W-0
138
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DREISSEN AIRCRAFT SYSTEMS COMPONENTS MAINTENANCE MANUAL
P/N 101719
25-33-58 INCORPORATES: 25-33-58 AERODEC MOD 1022 Page 113 Page 113
Sheet 6 of 9 Sheet 6 of 9 SEP 01/13 SEP 01/13
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
D
A001 8
C
B
A
C003 8
B002 8
N004 8 4
3
2
1 A006 8
C008 8
B007 8
N012 10
C044 8
B030 8
2
L2
3
F
C
B
A
D
E
G
P8
1
2
3
3
5
8
4
67
GND
B036 20
B037 20
B038 20
B039 20B040 20
B041 20
3
5
8
GND
4
67
B1 L1
A/C POWERINTERFACE
MS6029−4S−4TERMINAL COVER
P1 TB1
−9 (−101 MOD 001 & −301 MOD 001 ONLY)
5
6
7
N042 16
N032 20
N043 20
N033 20
3
B1 B2
CB4
A1 A2
CB2
B1 B2
C1 C2
F
C
B
A
D
E
G
J8
4
3
2
1
6
5
4
3
2
1
6
5
J4
SP1
C1 C2
5
3
2
1
J3
S2
53
WORK LIGHT
C
A/C GND
CASE GND
COPPER STRAP
3
LIGHT ASSY(DRIESSEN)
239002−21
S1
1A 5
2
64
3
1
BONDINGPLATE
A/C GNDINTERFACE
COPPER STRAP
COFFEEMAKERSUMP
PLUMBING
WORKCOUNTER
AC GND
115 VAC C
115 VAC B
115 VAC A PHASE A
PHASE B
PHASE C
AC NEUTRAL
CASE GROUND
CASE GROUND
COFFEEMAKER64753−001−003RAIL ASSY64759−151
HOT CUPDLH545−017DRIESSEN
MAKERCOFFEE
GNDELECTRICALPANEL
CB3HOT CUP
7.5A
BRT
DIM
OFF
4
2
3
15
S3
2
L2
6
4
3
BRT
DIM
1 OFF
AREA LIGHTING
1
3
10A C023 16
B022 16
A021 16
S025 16
S027 16
N024 14
S090 10
S026 10
C093 16
B092 16
A091 16
S095 16
N094 16
S096 16
C045 20 C047 16
C046 16
S048 16
S049 10
D50 22
D51 22
D53 22
D52 22
N033 20
B034 20
N035 20
B031 20
N032 20
B030 8
S029 12
S028 12
S005 8 S009 8
S010 8
3
4
CASE GND
AC GROUND
5 STATIC GROUND TO BRACKET, PANEL OR TO SHELL OF INSERT
A1 A2
CB9001HOT JUG
4 A A9001 20 25−33−58 SHEET 7A9004 10
Note: This Drawing relates to Sheet 6 of 9, of Dreissen CMM 25-33-58 for P/No. 101719
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DREISSEN AIRCRAFT SYSTEMS COMPONENTS MAINTENANCE MANUAL
P/N 101719
25-33-58 INCORPORATES: 25-33-58 AERODEC MOD 1022 Page 113 Page 113
Sheet 7 of 9 Sheet 7 of 9 SEP 01/13 SEP 01/13
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
Note: This Drawing relates to Sheet 7 of 9, of Dreissen CMM 25-33-58 for P/No. 101719
2
16
5
7
6
32
115 VAC
CASE GND
6
J5
S055 16
B101 16
C400 16
B401 16
A402 16
DCN058 20
S084 10
3
4
CASE GND
AC GROUND
3
1
21
25
31
10
9
8
13
14
15
26
28
30
29
115 VAC
HEATER
FAN
NTRL
DC +
DC −
DC +
LOW
HIGH
MED
DC −
DC059 20
DC060 20
DC061 20
DC062 20
A063 16
B064 16
C065 16
A066 16
D067 16
C068 16
DCN057 20
DC056 20
N103 16
4
1
5
16
14
DC −
P6
3
2
18
20
22
24
21
23
25
6
7S073 20
S072 20
N071 20
N070 20
N069 20
C
A PHASE
P7
B079 20
D
B
T1
4
3
2
1
TB2
5
6
4
3
2
1
TB1
5
6
7
SP2
SP3
SP4
B1 B2
CB5DC CONTROL
1A
SP4COPPER
STRAP
NEUTRAL
− DC
+ 28 VDC
TRANSFORMERRECTIFIER
N080 20
5S083 15COPPER
STRAP
3
3
COPPERSTRAP
3
CNTL BOX FORTEMPERATURESELECTION
28 VDC
HEATINGELEMENTS
PHASE A
PHASE B
PHASE C
FANMOTOR
PHASE A
PHASE B
PHASE C
AC NEUTRAL
CASE GND
CASE GND
OVEN #2RUMBOLD67063
OVENCONTROLLERRUMBOLD64213−001−001
C
B
A
C
B
A
C
B
A
A
B
C
7
COPPERSTRAP
3
A100 16
C102 16
B078 8
N017 8
C016 14
B015 14
A014 14
B081 20
25−33−58 SHEET 6
S076 10
−9 (−101 MOD 001 & −301 MOD 001 ONLY)
5 STATIC GROUND TO BRACKET, PANEL OR TO SHELL OF INSERT
6 CAP AND STOW AND ALLOW ADEQUATE LENGTH TO CONNECT TO CIRCUIT BREAKER
3
2
1
A9001 20
COPPERSTRAP
3
HOT JUGJF003001DRIESSEN
S9003 18
A9001 20
N9002 18
CHAPTER
INDICATING/ RECORDING
SYSTEM
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
DFDRS INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 0952
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
AE
RO
DE
C D
WG
: AL3
45-1
454
P18−2
4
8
13
2.5
C109 FLT REC AC
12115V AC
ELEX PWR−1 24−58−11
053−22
2.5
C468
1228V DC
BATT. BUS24−58−11
W089−110−22
2.5
C544 POS SENSORS
1226V AC XFR
NO.224−58−11
127−22
W029
D4100PJ
D4397PJ
D4395PJ
8
W089−199−22FLT REC DC
ELECTRONIC LOAD CIRCUIT BREAKER PANEL
P18 LOAD CONTROL CENTRE − LEFT
STA 254DISC.
W105−008−22
W109−013−22
W047−032−22
W047−033−22
7
W047
1
D8945JP
STA 178DISC.
2
SM4 516−22
517−22
515−2210
11518−22
W419−001−22
008−22
005−22
20519−22 020−24
23058−22 023−24
22035−22 022−24
9252−24B 220−22B
4T230
18
11
251−24R 219−22R
15520−24 007−242
12 015−24NOT USED
8
32254−24B
253−24R 31
34
33
35
14 014−24NOT USED
228−24B
227−24R
225−24R
226−24B
25
26
28
29
30
221−24R
222−24B
223−24R
224−24B
27
NOT USED
4 213−24R
214−24B5
3
6
D483
034−22
19
20
23
22
P5−19 FLIGHT RCRDR AND MACH AIRSPEED PNL
P5 OVERHEAD PANEL
5
3
2
1
FLT RCDRTEST SWITCH
L1 FLIGHT RECORDER LIGHT
1
4
3
2
33−18−04
33−18−04
33−18−16
030−22
W419−003−24
M9009 MICRO QARD1637
1
2
11
3
5
4
9
8
10
6 W419−9001−20
W419−010−20 GD128−DC
A
A
PD8987J
1
2
3
4
5
7
8
9
6
10
11
13
14
15
12
17
18
19
20
PD5955J
3
PD4101J
3 501−22
502−24
503−24
504−24
505−24
W017
522−24
519−24
508−24
633−24R
633−24B
607−24R
608−24B
601−24R
602−24B
619−24R
620−24B
SM536 014−22
013−22
31−31−31
SM503
SM504
31−31−35
518−24
512−24 1
D2295C
7
H
C
115V AC
M675 DIGITAL FLIGHT DATA
513−20GDX22−AC
16 16
J9
D2295A
K9
A
B
DFDR PLAY OUT
10
182−22GDX21−S
G9
H9
A
B
G11
H11
A
B
FDEP DATA IN
180−22GDX21−S
A11
D2295A
A9
B9
A
B
BITE OUT
DIGITAL INPUT
609−24R
610−24B
SM534
SM535
SM533
625−24R
626−24B
J11
K11
A
B
PLAYBACK IN
611−24R
612−24B
183−22 GDX21−S
B11MAINT FLAG
J15DIGITAL GND
K15ANALOGUE GND
515−24
516−22
517−22 GDX23−DC
D2295E
J15
D2295D
K15
DIGITAL GND
CHASSIS GND
H1
510−22
511−22GDX23−DC
H2
A
B
ACARS DATA IN
H3
H4
A
B
ACARS DATA OUT
23−27−12
ACQUISITION UNIT
FDEP DATA OUT
21
22
24
26
27
25
28
29
SM545 509−24
R263 FDAUD1805
X2
X1
A2
A3
STATUS RLY
514−24
520−22GDX23−DC
507−24 SM539
31−31−03
A1
506−24
D1805062−24 SM517
31−31−52
31−31−55
23
W419−021−22
019−22
209−24R
210−24B
215−22R
216−22B
017−20
E2−2 ELECTRONIC SHELF
21
D8987JP D183AM96 DIGITAL FLIGHT
STATUS
22 MAINT FLAG
GD815−S
9
10
A
B
PLAYBACK
7
8
A
B
DIGITAL INPUT
011−22 23 28V DC
029−22 1 115V AC H
002−20 2 115V AC L
6 CHASSIS GNDW419−006−20
GD391−AC
GD393−DC
28
D8997JP
27
E3−2 ELECTRONIC SHELF
M528 ENG ACC UNIT
D1458A
41
28
ENG NO. 1
D1458B
41
28
ENG NO. 2
8361−24
8362−24
8359−24
8360−24 SM160
SM162
8327−24
8328−24
8363−24
8364−24
27
D8909JP
28
24
D5212JP
5
W409−027−24
W409−028−24
W2016−017−24
W2016−054−24
32
33
D2596
GND
A3
A2
A1
AIR
E11 LDG GEAR LOGIC SHELF
R277 GND SENSINGRELAY
DATA RECORDER
31−31−51
181−22GDX21−S
CHAPTER
LIGHTS
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
MAP, FLIGHT KIT, AND READING LIGHTS
33-17-01 INCORPORATES: 33-17-01 AERODEC MOD 0948
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
CHAPTER
NAVIGATION
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
EFIS POWER/PROGRAM PIN - LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 0861
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
EFIS POWER/PROGRAM PIN - RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 0861
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
INERTIAL REFERENCE SYSTEM NO.1 POWER
34-26-11 INCORPORATES: 34-26-11 AERODEC MOD 0866
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
34-21-01
24-58-11NO.1 PWR28V DC
(MP)D2161B
POSITION MOUNT 1EXTENDED MAGVAR MAPMAGVAR MAP OLD/NEWPOSITION MOUNT 2PROG COMMON
SDI CODE
IRU-1M1161
011-22010-22009-22013-22012-22014-22
001-20002-20005-16004-12003-12
NOT USED
NOT USED
A2K9K3A3A1A6A5
W833
SM1
025-22
008-22007-22006-22
024-22
MSTR TEST IN
24-58-11STBY PWR115V AC
24-58-11STBY PWR BUS
28V DC
36
27
25
SP4007
SM30
23
26
24
33-18-12
ON DC
DC FAIL
INPUTSDISCRETE
CH18
CH
C1011
C1029
C1007
C1013
C1009
23
24
25
D4001J P
14
16
D4151J P
4
61151
SDI
GDX16-AC
D2165C
40
(BP)
1
1187
51
GDX5-DCGDX6-SGDX4-AC
D2161C(BP)
E11E10E12E13F2F1
D2161B(MP)
1 23
W029162-20
DAA/IRS 1 - AC
1 23 163-20DAA/FMC 1 - AC
1 2
IRS 1 - AC3
1 210DAA 1 - DC
1 210IRS 1 - DC
ANNUNCIATOR
PNL LTS
P18-2 CAPT ELEX SYS CIRCUIT BREAKER PANELP18 LOAD CONTROL CENTER - LEFT
069-22DIM CNTL
5V ACCOMM
M1M2
ALIGN
FAULT
MODE SELECT COMM
P5-69 MODE SELECTOR UNIT
P5 PILOTS OVERHEAD PANEL
15
17
1314
12
11181016
12
D2171
W047
33-18-05
33-12-01
DC FAIL
STA 285DISC.
1315
14201716
P D4327J
HC
28V DC INPUT
CHASSIS GNDCH115V AC INPUT
ON DC
M2M1DISCRETE IN
ISDU CONTROLALIGN
FAULT
W175-
E3-5 FWD ELECTRONIC SHELF
W101-040-20
041-20
W101-042-20
W089-
046-16
W175-047-12
W007177-20
176-20
174-20
175-16
173-14
178-20181-16180-20
115V AC IRS INPUT
FMC INPUT28V DC
CHASSIS GNDAC GND
FMC INPUT115V AC
M1163 DAA 1
34-26-14172-14 SM2
756234
D8323P J
166-2234-26-14
SM3
W127-013-22
014-22
015-22
016-22017-22
W127-
020-22
1315
14201716
D4017J P
165-22
170-22171-22167-22
168-22
169-22
E1-2 ELECTRONIC SHELF
164-20
W089-055-16
062-22
056-12
D2165A
D6
GDX10-DC 179-12
(TP)
C
W101-
2 13C1060 DAA/FMC 1 - DC
W089-057-16
H28V DC INPUT
545-16546-20
W175-048-16
810-22
1817151684921203
D2269
066-22067-22068-22
064-22
065-22
P10
405-22
406-22403-22
401-22402-22
404-22
SM8
SM9
SP332334-26-14
484-22481-22483-22482-22480-22485-22486-22
33-18-22
33-18-0233-18-05
W044
GD100B-DCGD100C-DC
M1206 MASTER CAUTION UNIT
MAXIMUM LENGTH 24 INCHES
PANEL
A/G LOGICON DC OUTPUT
FAULTDC FAIL
ON DC INPUTCHASSIS GND
DC GNDIRS WARNING
MASTER CAUTION RECALLMASTER TESTPOWER SUPPLY
P D4238J
DISCRETE
NOTES:
1
GROUND FROM ALL OTHER GROUNDS.SINGLE POINT GROUND. ISOLATE THIS
1
32
030-22GDX10-DC
78
40
STA 254DISC.
D4047PJ
4
2
6
D4393PJ
42
41
24-58-11BAT. BUSSW HOT28V DC
34-26-21
2
SM4007
D12
D13
C4C5
E4E5
J9K9
B12B13
2
2
2
2
GDX30-S
GDX30-S
GDX30-S
GDX30-S
747-22R
748-22B
741-22R742-22B
749-22R750-22B
753-22R754-22B
D2165B
C
C
HC
H
C
H
HC
H
EXCITATIONNAV
EXCITATIONATT-1
EXCITATIONATT-2
EXCITATIONHDG-4
EXCITATIONHDG-5
34-26-12
34-21-01
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
INERTIAL REFERENCE SYSTEM NO.1 OUTPUT BUSSES
34-26-13 INCORPORATES: 34-26-13 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
INERTIAL REFERENCE SYSTEM NO.2 POWER
34-26-21 INCORPORATES: 34-26-21 AERODEC MOD 0866
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
005-16004-12003-12
002-20
001-20
D2163C
EXTENDED MAGVAR MAPMAGVAR MAP OLD/NEW
28V DC SWITCHED INPUT PWR
IRU-2M1162
A2
W103-
M1206
6
4
2 14537-20
591-20
56
J
ON DC OUT
D4339P
18
047-12
DC FAIL
027-20
15
2
9478
111112
ELECTRONIC SHELF
D4337J
J
SP3957
SP3939
18
14
587-20
56
AIR/GROUND LOGIC
FAULTON DC IN
GDX7-AC
56
P
23
D2271
18
34-26-11
NOTES: 1GROUND FROM ALL OTHER GROUNDS.SINGLE POINT GROUND. ISOLATE THIS
163-20
161-20
586-20
538-20
046-20
W091-
D4401P
1
SM33
J
W091-
W103-
W03145
47
E1-3
060-12
044-20
K9
P10
F2
ON DC E11E12E10F1
E13
073-22072-22
144-22
W047
W383-
046-16
1016
047-20
J
162-20
P6-1 ELECTRONIC LOAD CIRCUIT BREAKER PANELP6 LOAD CONTROL CENTER - RIGHT
045-20
D4409P
585-20
194-16
195-12
8
MSTR TEST
DIM CNTL
W383-
ON DC
DC FAIL
FAULTM1M2
ALIGN
MODE SELECT-COMM
ANN
DISCRETE
P5-69
P5 OVERHEAD PANEL
33-18-05
33-18-12
457-22
142-22
070-22
W044
460-22
143-22
E3-5 FWD ELECTRONIC SHELF
115V AC INPUT
28V DC GNDCHASSIS GND
SDI
PROG COMMON
POSITION MOUNT NO.1
POSITION MOUNT NO.2
ALIGNM2M1
FAULTDC FAIL
D2163B
11
7
1
K3
A1
A6
009-22010-22011-22012-22013-22014-22
GDX1-AC
GDX2-DCGDX3-S
SM501
(MP)
20
SM501
171615
14
13
590-16
1
40
2
3
4
5
67
D4257J
D8325P
D5953J
539-20
198-16
J
P
P
46
W091-
W163-
D2167C
846-20
GDX8-AC
7
11
115V AC FMC INPUT
115V AC IRS INPUT
AC GND28V DC INPUT
DC GND
FMC AC GND INPUTCHASSIS GND
27
(BP)
(BP)
709-12
708-12W069-
D4193J
7
D4063P
P
W069-
(TP)
E1-2 ELECTRONIC SHELF
W00915
16
17
D4019J P
1
4
A2
34-26-14 W835
C
H
34-26-14
17
15
34
8244-20
W069-
D235B
15
17121314
11
D2173
071-22 SM18
SM19
SP3323
407-22
409-22408-22412-22
410-22
411-22
34-26-14
458-22
459-22
461-22
2024302926
13
14
15161720
STA 285DISC.
048-16
P D5981J
W467-013-22
014-22
015-22016-22017-22020-22W467-
802-22
801-22
803-22
804-22805-22806-22807-22
28V DC FMC INPUT
GND
MASTER CAUTION UNIT
16
845-16
3GDX24-DC
NOT USED
NOT USED
INPUTDISCRETE
P D4240J
STA 259DISC.
D235B
D235A
A2
A1
C1
X1
K8
A1
8248-20
735-20
8247-208246-20
8243-20
W011
M1474 INTEG FLT SYS ACCESS UNIT (TP)
X2
X1
DAA/FMC NO.2 DC
IRS NO.2 DC
DAA/FMC NO.2 AC
IRS NO.2 AC
C1010
C1014
C1061
C1008
DAA/IRS NO.2 AC
DAA NO.2 DC
C1012
2
2
21
1
2
1
C1030
1
1
1
10
10
3
3
2
23
3
24-58-21SWITCHEDHOT BAT. BUS28V DC
24-58-21ELEX BUS NO.2115V AC
24-58-21NO.2ELEX BUS115V AC
24-58-21ELEX BUS NO.228V DC
24-58-21NO.2ELEX BUS28V DC
31DS-3XDG
1
1
GDX3-S
1
1
1
GDX3-S
GDX3-S
GDX3-S
GDX3-S
C4
D12
1
SM510
721-22R722-22B
D2167A
719-22R720-22B
723-22R724-22B
725-22R726-22B
727-22R728-22B
729-22R730-22B
D2167B
C5
E4E5
A4A5
J9K9
C14C15
H
C
HC
H
C
H
C
H
C
H
C
EXCITATIONNAV
EXCITATIONATT-1
EXCITATIONATT-2
EXCITATIONHDG-3
EXCITATIONHDG-4
557-22
EXCITATIONATT-3
34-26-22
T/DELAY5 MIN
582-12
W069-597-20596-20
W069-
8225-20
GDX6-DC
SP400934-21-02
1
52
M1164
GDX16-DC
MODE SELECTOR UNIT
DAA 2
34-31-07
024-22
FIRST OBSERVERS PANEL
008-22
025-22K9
A5
A3
5
8
006-22007-22
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
INERTIAL REFERENCE SYSTEM NO.2 OUTPUT BUSSES
34-26-23 INCORPORATES: 34-26-23 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
GROUND PROXIMTY WARNING 34-49-04 INCORPORATES: 34-49-04 AERODEC MOD 0865
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
AE
RO
DE
C D
WG
: AL3
45-1
329
C8ALTITUDE CALLOUT ENABLE
B15PPCNF19 (WGS−84 GPS ALT REF SELECT)
D1153B
A3PPCOM (PROGRAMME PIN COMMON)
W021−501−24
W021−507−22
W9021−050−22
W021−515−24
GDX10−DC
SM1153
B10PPCNF2
A10PPCNF1
D1153A
W9021−047−22
W9021−048−22
W9021−076−24C10PPCNF3
W021−517−24
W021−518−24
AIRCRAFT TYPE SELECT
SP9012D6PPCNF17 (PROGRAMME PIN PARITY) W9021−055−22
B5PPCNF12 (WINDSHEAR CONTROL) W9021−069−22
C4PPCNF11 (AUDIO DECLUTTER / VOLUME / WGS−4)
W9021−054−22
W9021−053−22
W9021−049−22
W9021−052−22
SM50534−49−03
D4PPCNF4
B4PPCNF5
A8PPCNF6
ALTITUDE CALLOUT MENU
D1153B
D14PPCNF7 (OPTIONAL GPS / GPIRS)
C2PPCNF9 (2 ILS / 2 LRRA / 3 LRRA)
B5PPCNF13 (TCF DIS / TAD DIS / SIM REPO)
D15DOUTL1 (GLIDESLOPE CANCEL)
W9021−051−22 SP9009
C12DOUTL4 (WINDSHEAR CAUTION)
B12DOUTL 6 (AUDIO ON)
D1153A
C2PPCNF14 (BANK ANGLE)
W9021−058−22
W9021−077−22 SP9010
W9021−061−22
W9021−060−22
W9021−059−22 SP9013
W9021−079−22
M652 ENHANCED GROUND PROXIMITY COMPUTER
E2−4 SHELF
34−49−03
W021−704−24
34−45−02SM506
34−49−03
34−45−02
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV301
ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-12 INCORPORATES: 34-53-12 AERODEC MOD 0951
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
A
ER
OD
EC
DW
G: A
L345
-140
3
E3
D149B
875−24MODE S ADDRESS BIT COMMON
D3 874−24BIT 24
C3 873−24BIT 23
B3 872−24BIT 22
A3 871−24BIT 21
K2 870−24BIT 20
J2 869−24BIT 19
H2 868−24BIT 18
G2 867−24BIT 17
F2 866−24BIT 16
E2 865−24BIT 15
D2 864−24BIT 14
C2 863−24BIT 13
B2 862−24BIT 12
A2 861−24BIT 11
K1 860−24BIT 10
J1 859−24BIT 9
H1 858−24BIT 8
G1 857−24BIT 7
F1 856−24BIT 6
E1 855−24BIT 5
D1 854−24BIT 4
C1 853−24BIT 3
B1 852−24BIT 2
A1 851−24BIT 1
J5 850−24ANT BITE PROGRAM
MODE S ADDRESS
C5
D149A
877−24MAX TAS PROGRAMME
D5 876−24PROGRAMME COMMON
SM800
W017
M1469D2681
25
24
23
22
21
20
19
18
17
16
15
14
13
12
11
10
9
8
7
6
5
4
3
2
1
E2−2
1.
SHORTING RECEPTACLE
ELECTRONIC SHELF
M163 ATC−1 TRANSPONDER (MP)
(TP)
A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3
MODE S CODE
ADDRESS BIT
REGISTRY OCTAL
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24
AIRPLANE
D149B AND D2681
1.
OO−TNO 21150717PV301 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 0 1 1 11
1.NOTES:
FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D149B AND D2681
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
NO.1 AND NO.2 ATC ENHANCED SURVEILLANCE BUSSES
34-53-16 INCORPORATES: 34-53-16 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV301
ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-22 INCORPORATES: 34-53-22 AERODEC MOD 0951
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
AE
RO
DE
C D
WG
: AL3
45-1
403
E3
D155B
875−24MODE S ADDRESS BIT COMMON
D3 874−24BIT 24
C3 873−24BIT 23
B3 872−24BIT 22
A3 871−24BIT 21
K2 870−24BIT 20
J2 869−24BIT 19
H2 868−24BIT 18
G2 867−24BIT 17
F2 866−24BIT 16
E2 865−24BIT 15
D2 864−24BIT 14
C2 863−24BIT 13
B2 862−24BIT 12
A2 861−24BIT 11
K1 860−24BIT 10
J1 859−24BIT 9
H1 858−24BIT 8
G1 857−24BIT 7
F1 856−24BIT 6
E1 855−24BIT 5
D1 854−24BIT 4
C1 853−24BIT 3
B1 852−24BIT 2
A1 851−24BIT 1
J5 850−24ANT BITE PROGRAM
MODE S ADDRESS
C5
D155A
877−24MAX TAS PROGRAMME
D5 876−24PROGRAMME COMMON
SM800
W087
M1470D2683
25
24
23
22
21
20
19
18
17
16
15
14
13
12
11
10
9
8
7
6
5
4
3
2
1
E2−4
1.
SHORTING RECEPTACLE
ELECTRONIC SHELF
M381 ATC−2 TRANSPONDER (MP)
(TP)
A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3
MODE S CODE
ADDRESS BIT
REGISTRY OCTAL
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24
AIRPLANE
D155B AND D2683
1.
OO−TNO 21150717PV301 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 0 1 1 11
1.NOTES:
FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D155B AND D2683
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
FLIGHT MANAGEMENT COMPUTER SYSTEM DATA BUS AND CONTROL
34-61-02 INCORPORATES: 34-61-02 AERODEC MOD 0090
Page 1 Page 1
FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PV301
FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS
34-61-11 INCORPORATES: 34-61-11 AERODEC MOD 0857
Page 1 Page 1
FEB 01/11 FEB 07/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
A
ER
OD
EC
DR
AW
ING
: A
L34
6-12
90
F11
E11
C11
D11
G11
H11
CAA FLT RULES
AIR FRAME / ENG CODE
C13
D10
F10
F12
F14
F15
G10
B13
H12
J10
K15
H10
C10
D2179BM1175 FMC NO.1
DEGGREES F DEFAULT
VOR INHIBIT
TAKEOFF SPEED
ASPIRATED TAT PROBE
PERFORMANCE OPTION
FLT NUMBER ENTRY
KILOGRAM OPTION
TAKEOFF PROFILE
RUNWAY POSITION UPDATE
NON AGILITY DME TYPE
NAV AID SUPPRESSION ON EFIS
SELECTED COURSE INHIBIT ON EFIS
8022−22
8021−22
8025−22
8026−22
8023−22
8024−22
8010−22
8002−22
8011−22
8012−22
8013−22
8014−22
8015−22
8016−22
8017−22
8018−22
8019−22
8007−22
8008−22
2
1
5
6
3
4
9
10
11
12
13
14
15
16
17
18
19
7
8
D6739P
E1−2 ELECTRONICS SHELF
J
W737−002−22
001−22
025−22
026−22
023−22
024−22
049−22
050−22
051−22
052−22
053−22
054−22
055−22
056−22
057−22
058−22
059−22
047−22
XB1
XA1
XC1
XC2
XB2
XA2
XA6
XB6
Z11
Z12
XA8
XC8
XD5
T1013STA 314.5LBL 19.2WL 182.5
W737−003−22WK
028−22WO GD127−S
W737−027−22WV
GD127−SW737−065−22
GD127−SW737−066−22
B10FAA / CAA QRH SPEEDS 8320−22 20 W737−020−22
048−22
XD8
W007
CHAPTER
AIRBORNE AUXILIARY
POWER
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV301
APU – MANUAL START-STOP 49-31-12 INCORPORATES: 49-31-12 AERODEC MOD 0949
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Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
WIRE
LIST
INDEX
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST Section INDEX Page 1
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
SECTION PAGE NO. DATE SECTION PAGE NO. DATE
W0007 1 FEB 01/11 W0009 1 FEB 01/11 W0011 1 FEB 01/11 W0069 1 FEB 01/11 W0967 1 FEB 01/11 W9001 1 FEB 01/11 W9002 1 FEB 01/11 W9076 1 FEB 01/11
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W0007
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0007 E1-2 ELECTRONIC SHELF PART A 9001 22 R 34-53-16 D9205P 20 SM12 PV301 0057 / 0090 9001 22 B 34-53-16 D9205P 21 SM13 PV301 0057 / 0090 9001 22 34-53-16 D9205P 22 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM14 PV301 0057 / 0090 9002 22 R 34-53-16 D9205P 23 SM131 PV301 0057 / 0090 9002 22 B 34-53-16 D9205P 24 SM132 PV301 0057 / 0090 9002 22 34-53-16 D9205P 25 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR SM8 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W0009
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0009 E1-2 ELECTRONIC SHELF PART B 9001 22 R 34-53-16 D9205P 29 SM517 PV301 0057 / 0090 9001 22 B 34-53-16 D9205P 30 SM518 PV301 0057 / 0090 9001 22 34-53-16 D9205P 31 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM519 PV301 0057 / 0090 9002 22 R 34-53-16 D9205P 26 SM131 PV301 0057 / 0090 9002 22 B 34-53-16 D9205P 27 SM132 PV301 0057 / 0090 9002 22 34-53-16 D9205P 28 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR SM8 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W0011
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0011 E1-3 AUTO PILOT SYSTEM A 9001 22 R 34-53-16 D5977P 50 SM128 PV301 0057 / 0090 9001 22 B 34-53-16 D5977P 51 SM129 PV301 0057 / 0090 9001 22 34-53-16 D5977P 52 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM130 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W0069
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0069 E1-3 AUTO PILOT SYSTEM B 9001 22 R 34-53-16 D5977P 53 SM612 PV301 0057 / 0090 9001 22 B 34-53-16 D5977P 54 SM613 PV301 0057 / 0090 9001 22 34-53-16 D5977P 55 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM614 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W0967
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0967 ATC 1 E2-2 WIRING 9001 22 R 34-53-16 D9004P 11 D149A C2 PV301 0057 / 0090 9001 22 B 34-53-16 D9004P 12 D149A D2 PV301 0057 / 0090 9001 22 34-53-16 D9004P 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR GDX-14 PV301 0057 / 0090 9002 22 R 34-53-16 D9004P 14 D149A A6 PV301 0057 / 0090 9002 22 B 34-53-16 D9004P 15 D149A B6 PV301 0057 / 0090 9002 22 34-53-16 D9004P 16 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR GDX-14 PV301 0057 / 0090 9003 22 R 34-53-16 D9004P 17 D149A A7 PV301 0057 / 0090 9003 22 B 34-53-16 D9004P 18 D149A B7 PV301 0057 / 0090 9003 22 34-53-16 D9004P 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR GDX-14 PV301 0057 / 0090 9004 22 R 34-53-16 D9004P 8 D149A A2 PV301 0057 / 0090 9004 22 B 34-53-16 D9004P 9 D149A B2 PV301 0057 / 0090 9004 22 34-53-16 D9004P 10 9004 SCR PV301 0057 / 0090 9004 22 34-53-16 9004 SCR GDX-14 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W9001
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9001 E2-2 TO E1-2, E1-3 9001 22 R 34-53-16 D9004J 11 D9205J 20 PV301 0057 / 0090 9001 22 B 34-53-16 D9004J 12 D9205J 21 PV301 0057 / 0090 9001 22 34-53-16 D9004J 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR D9205J 22 PV301 0057 / 0090 9002 22 R 34-53-16 D9004J 14 D9205J 23 PV301 0057 / 0090 9002 22 B 34-53-16 D9004J 15 D9205J 24 PV301 0057 / 0090 9002 22 34-53-16 D9004J 16 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR D9205J 25 PV301 0057 / 0090 9003 22 R 34-53-16 D9004J 17 D5977J 50 PV301 0057 / 0090 9003 22 B 34-53-16 D9004J 18 D5977J 51 PV301 0057 / 0090 9003 22 34-53-16 D9004J 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR D5977J 52 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W9002
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9002 E2-4 TO E1-2, E1-3 9001 22 R 34-53-16 D9006J 11 D9205J 29 PV301 0057 / 0090 9001 22 B 34-53-16 D9006J 12 D9205J 30 PV301 0057 / 0090 9001 22 34-53-16 D9006J 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR D9205J 31 PV301 0057 / 0090 9002 22 R 34-53-16 D9006J 8 D9205J 26 PV301 0057 / 0090 9002 22 B 34-53-16 D9006J 9 D9205J 27 PV301 0057 / 0090 9002 22 34-53-16 D9006J 10 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR D9205J 28 PV301 0057 / 0090 9003 22 R 34-53-16 D9006J 17 D5977J 53 PV301 0057 / 0090 9003 22 B 34-53-16 D9006J 18 D5977J 54 PV301 0057 / 0090 9003 22 34-53-16 D9006J 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR D5977J 55 PV301 0057 / 0090
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST
91-21-11 Section W9076
Page 1 FEB 01/11
Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9076 ATC 2 E2-4 WIRING 9005 22 R 34-53-16 D9006P 17 D155A A7 PV301 0057 / 0090 9005 22 B 34-53-16 D9006P 18 D155A B7 PV301 0057 / 0090 9005 22 34-53-16 D9006P 19 9005 SCR PV301 0057 / 0090 9005 22 34-53-16 9005 SCR GDX-14 PV301 0057 / 0090 9006 22 R 34-53-16 D9006P 8 D155A A6 PV301 0057 / 0090 9006 22 B 34-53-16 D9006P 9 D155A B6 PV301 0057 / 0090 9006 22 34-53-16 D9006P 10 9006 SCR PV301 0057 / 0090 9006 22 34-53-16 9006 SCR GDX-14 PV301 0057 / 0090 9007 22 R 34-53-16 D9006P 11 D155A C2 PV301 0057 / 0090 9007 22 B 34-53-16 D9006P 12 D155A D2 PV301 0057 / 0090 9007 22 34-53-16 D9006P 13 9007 SCR PV301 0057 / 0090 9007 22 34-53-16 9007 SCR GDX-14 PV301 0057 / 0090 9008 22 R 34-53-16 D9006P 14 D155A A2 PV301 0057 / 0090 9008 22 B 34-53-16 D9006P 15 D155A B2 PV301 0057 / 0090 9008 22 34-53-16 D9006P 16 9008 SCR PV301 0057 / 0090 9008 22 34-53-16 9008 SCR GDX-14 PV301 0057 / 0090
ILLUSTRATED
PARTS
CATALOGUE
Contents
IPC-CONTENTS Page 1
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
Chapter 11 PLACARD & MARKINGS
Chapter 21 AIR CONDITIONING
Chapter 22 AUTO FLIGHT
Chapter 23 COMMUNICATIONS
23-24-00-01Z – MODULE INSTL – AFT OVERHEAD PANEL P5 (EMERGENCY LOCATOR TRANSMITTER ONLY)
23-24-00-02Z – TRANSMITTER INSTL – EMER LOCATOR (ELT)
23-24-00-03Z – ANTENNA INSTL – EMER LOCATOR (ELT)
23-71-13-01Z – MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY)
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-11-11-18Z – SEAT INSTL – SECOND OBSERVER
25-11-11-66Z – ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)
25-11-21-22Z – PANEL INSTL – LINING STA 261 TO STA 269
25-31-11-07Z – GALLEY INSTL – UNIT NO.1
25-31-11-99Z – HOT CUP INSTL – GALLEY 1
25-31-21-04Z – GALLEY INSTL – UNIT NO.2
25-31-41-07Z – GALLEY INSTL – UNIT NO.4B
Chapter 26 FIRE PROTECTION
Chapter 27 FLIGHT CONTROLS
Chapter 28 FUEL
Chapter 29 HYDRAULIC POWER
Chapter 30 ICE AND RAIN PROTECTION
Chapter 31 INDICATING/RECORDING SYSTEMS
31-24-24-99Z – EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY)
Chapter 32 LANDING GEAR
Chapter 33 LIGHTS
33-11-00-05Z – LIGHT INSTL – CONT CAB CREW
Chapter 34 NAVIGATION
34-28-31-02Z – EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY)
34-53-21-01B – EQUIPMENT INSTL – ELECT. RACKS (ATC TRANSPONDER ONLY)
IPC-CONTENTS Page 2
Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
®
Chapter 35 OXYGEN
35-12-00-02Z – OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY)
35-12-00-20Z – OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
Chapter 49 AIRBORNE AUXILIARY POWER
49-70-00-02Z – ENGINE ASSY – APU (INDICATING ONLY)
Chapter 52 DOORS
Chapter 53 FUSELAGE
53-42-00-80Z – ROD INSTL – NO.1 AND NO.4B GALLEY POSITION TIE
53-42-00-81Z – ROD INSTL – NO.2 GALLEY POSITION TIE
Chapter 54 NACELLES / PYLONS
Chapter 55 STABILIZERS
Chapter 56 WINDOWS
Chapter 57 WINGS
Chapter 71 POWER PLANT
Chapter 73 ENGINE FUEL AND CONTROL
Chapter 74 IGNITION
Chapter 75 AIR
Chapter 77 ENGINE INDICATING
Chapter 78 EXHAUST
Chapter 79 OIL
Chapter 80 STARTING
Chapter 91 CHARTS
Chapter 93 PANELS
CHAPTER
COMMUNICATIONS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-01Z 23-24-00 MOD 0889 Fig 1Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
MODULE INSTL – AFT OVERHEAD PNL P5 (EMERGENCY LOCATOR TRANSMITTER ONLY) Figure 1Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-01Z 23-24-00 MOD 0889 Fig 1Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
1Z --1 AGM10-B73E-0063 INSTALLATION OF ARTEX C406-1 ELT 001001 RF
10 345-6196-04 • REMOTE SWITCH 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-02Z 23-24-00 MOD 0889 Fig 2Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
TRANSMITTER INSTL – EMER LOCATOR (ELT) Figure 2Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-02Z 23-24-00 MOD 0889 Fig 2Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
2Z --1 AGM10-B73E-0063 ELT TRANSMITTER INSTALLATION 001001 RF --1 B737-ELT-1 KIT, ARTEX C406-1 ELT INSTALLATION
10 2-23501-302-01 • SUPPORT TRAY ASSY 1
--20 2-23501-302-03 • BRACKET 2--30 2-23501-302-04 • BRACKET 2--40 2-23501-302-05 • BRACKET 1--50 2-22566-302-01 • BUZZER BRACKET 1--60 2-21483-401-004 • PLACARD 1--70 MS27039-1-09 • SCREW 6--80 AN960-10L • WASHER 6--90 MS21042-3 • NUT 6--100 2-23501-301-09 • FILLER 1--110 2-23501-301-08 • FILLER 1120 453-5002-( ) • ELT XMTR 1
--130 455-4010-01 • ELT DONGLE 1--140 452-0133 • BATTERY PACK 1--150 130-4004 • BUZZER 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-03Z 23-24-00 MOD 0889 Fig 3Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
ANTENNA INSTL – EMER LOCATOR (ELT) Figure 3Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-24-00-03Z 23-24-00 MOD 0889 Fig 3Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
3Z --1 AGM10-B73E-0063 ELT ANTENNA INSTALLATION 001001 RF --1 B737-ELT-1 KIT, ARTEX C406-1 ELT INSTALLATION
10 110-340 • ANTENNA – ELT 120 MS27039C-1-15 • SCREW 6
--30 2-23501-301-01 • CHANNEL 1--40 2-23501-301-02 • CLIP 4--50 2-23501-301-03 • CLIP 2--60 2-23501-301-04 • CLIP 2--70 2-23501-301-05 • CHANNEL 2--80 2-23501-301-06 • NUTPLATE 2--90 2-23501-301-07 • NUTPLATE 1--100 NAS1473A3 • NUT 6--110 2-21483-401-003 • PLACARD 1--120 2-23501-301-08 • FILLER 1--130 2-23501-301-09 • FILLER 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-71-13-01Z 23-71-13 MOD 0916 Fig 1Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY) Figure 1Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-71-13-01Z 23-27-13 MOD 0916 Fig 1Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
1Z --1 AGM10-B73E-0138 CVR SWITCH INSTALLATION 001001 RF
10 233A3211-1 • MODULE – COCKPIT VOICE RECORDER 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-11-18Z 25-11-11 MOD 0948 Fig 18Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
SEAT INSTL – SECOND OBSERVER FIGURE 18Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-11-18Z 25-11-11 MOD 0948 Fig 18Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
18Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTALLATION 001001 RF
10 11-007-1 • SEAT ASSY 1--20 65-76688-3 • FILLER 1--30 69-43995-1 • LOOP STRAP 1--40 69-44684-1 • SHIM 1--50 65-46836-2 • VELCRO 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-11-66Z 25-11-11 MOD 0948 Fig 66Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 66Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-11-66Z 25-11-11 MOD 0948 Fig 66Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
66Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTL 001001 RF
10 69-44447-2 • ASHTRAY ASSY 120 69-43944-1 • BRACKET ASSY 130 69-44458-3 • SUPPORT ASSY 140 BACS40R05C05F • SHIM - LAMINATED 250 26S55-5AB • STUD 2
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-21-22Z 25-11-21 MOD 0948 Fig 22Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
PANEL INSTL – LINING STA 261 TO STA 269 FIGURE 22Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-21-22Z 25-11-21 MOD 0948 Fig 22Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
22Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTALLATION 001001 RF
10 69-45405-20 • PANEL – LINING 120 69-45405-21 • PANEL – LINING 1
ATTACHING PARTS --30 SFSW10F8DL26GY • SCREW 14
- - - - - - - - - * - - - - - - - - - -
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.1 Figure 7Z (SHEET 1 OF 4)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.1 Figure 7Z (SHEET 2 OF 4)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 2
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.1 Figure 7Z (SHEET 3 OF 4)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 3
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.1
Figure 7Z (SHEET 4 OF 4)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 4
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
7Z --1 65C37843-1 GALLEY INSTL – UNIT NO.1 001001 RF 5 NAS602-6P • SCREW 9
10 MS51861-34C • SCREW 115 65C35726-5 • RETAINER 120 65C35726-100 • SEAL - BLADE 155 69-50328-9 • ROD INSTL – POSITION TIE 1
FOR DETAILS SEE: 53-42-00-80Z
60 69-622-78-1 • GROUND INSTL 165 NAS1801-3-8 •• SCREW 165 NAS1801-4-8 •• SCREW 170 NAS1149D0316H •• WASHER 375 NAS1149D0316H •• WASHER 275 NAS1149D0416H •• WASHER 280 BACW10P6AL •• WASHER 180 BACW10P11AL •• WASHER 185 MS21042L3 •• NUT 185 MS21042L4 •• NUT 190 NAS1801-4 •• SCREW 190 NAS1801-3 •• SCREW 195 NAS1149D0416H •• WASHER 295 NAS1149D0316H •• WASHER 2100 NAS1149D0316H •• WASHER 2100 NAS1149D0416H •• WASHER 2105 MS21042L3 •• NUT 1105 MS21042L4 •• NUT 1110 1002BC15 •• JUMPER ASSY 1110 BACJ40A20-15 •• JUMPER ASSY 1110 BACJ40D20-120 •• JUMPER ASSY 1110 RBEJ40D11-96 •• JUMPER ASSY 1115 BACB30NT3K6 • BOLT 4120 NAS1149D0316J • WASHER 4125 415N4002-24 • FITTING 1135 BACC10JB032C046 • CLAMP 1140 65C35726-12 • SEAL - FLOOR 1300 101719-101 • GALLEY ASSY 1305 BACB30LE5K9 • BOLT 4310 BACB30LE5K14 • BOLT 4315 BACW10BP5CD • WASHER 8
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-99Z 25-31-11 MOD-1022 Fig 99Z SEP 01/1 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
HOT CUP INSTL – GALLEY 1 Figure 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-99Z 25-31-11 MOD-1022 Fig 99Z SEP 01/13 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-1022-001 INTRODUCTION OF DRIESSEN COMBO ASSY ON GALLEY G1A 001001 RF --1 AL253-1577 INSTALLATION OF DREISSEN COMBO ASSY (AERODEC DRAWING) 001001 RF
10 JF003001 • COMBO ASSY – HOT CUP 1
SEE DRIESSEN CMM 25-26-33 50 34-00318 • BRACKET ASSY 160 AL253-0247-001 • BRACKET CONNECTOR 170 9-028-13 • SCREW 2
--80 NAS1836-3-22 • INSERT 490 NAS514P1032-6 • SCREW 2100 NAS1149D0332J • WASHER 4110 NAS603-6 • SCREW 4
--130 AL253-1599-002 • SPACER – ADAPTER PANEL 4160 NAS514P632-12 • SCREW 4170 NAS1149D0616J • WASHER 4180 MS35649-262 • NUT 4190 AC16707 • CONNECTOR 1210 AL113-0248-001 • PLACARD – USER INSTRUCTIONS 1220 AN935-6 • WASHER 4
--230 NAS514P1032-21 • SCREW 4--240 AL253-1599-001 • ADAPTER PANEL 1250 NAS43DD1-10FC • SPACER 4
--260 TC342A-X • CLIP 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-21-04Z 25-31-21 AGMIS06-B73E-0126 Fig 4Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.2 Figure 4Z (SHEET 1 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-21-04Z 25-31-21 AGMIS06-B73E-0126 Fig 4Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.2 Figure 4Z (SHEET 2 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-21-04Z 25-31-21 AGMIS06-B73E-0126 Fig 4Z FEB 01/11 Page 2
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
4Z --5 65C35407-2 GALLEY INSTL – UNIT NO.2 001001 RF
10 65C35407-4 • TAPE - HOOK AR15 415N0019-30 • SEAL ASSY AR25 69-50334-68 • ROD INSTL – POSITION TIE 1
FOR DETAILS SEE: 53-42-00-81Z
30 69-622-78-2 • GROUND INSTL 135 NAS1801-3-8 •• SCREW 135 NAS1801-4-8 •• SCREW 140 NAS1149D0316H •• WASHER 341 NAS1149D0316H •• WASHER 241 NAS1149D0416H •• WASHER 242 BACW10P6AL •• WASHER 142 BACW10P11AL •• WASHER 145 MS21042L3 •• NUT 145 MS21042L4 •• NUT 150 NAS1801-4 •• SCREW 150 NAS1801-3 •• SCREW 155 NAS1149D0416H •• WASHER 255 NAS1149D0316H •• WASHER 260 NAS1149D0316H •• WASHER 260 NAS1149D0416H •• WASHER 265 MS21042L3 •• NUT 165 MS21042L4 •• NUT 170 1002BC15 •• JUMPER ASSY 170 BACJ40A20-15 •• JUMPER ASSY 170 BACJ40D20-120 •• JUMPER ASSY 170 RBEJ40D11-96 •• JUMPER ASSY 175 415N4002-39 • FITTING ASSY 1
ATTACHING PARTS 80 NAS623-3-4 • SCREW 1685 AN960-10 • WASHER 16
- - - * - - - 145 65C35407-5 • SEAL - FLOOR AR145 65C35726-7 • SEAL - FLOOR AR270 101069-1 • GALLEY ASSY 1
--275 BACB30LE5K14 • BOLT 4--280 NAS6605-8 • BOLT 4--285 AN960-516 • WASHER 8
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-41-07Z 25-31-41 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.4B
Figure 7Z (SHEET 1 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-41-07Z 25-31-41 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GALLEY INSTL – UNIT NO.4B
Figure 7Z (SHEET 2 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-41-07Z 25-31-41 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 2
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
7Z --1 65C37843-2 GALLEY INSTL – UNIT NO.4B 001001 RF 5 69-50329-11 • ROD INSTL – POSITION TIE 1 FOR DETAILS SEE: 53-42-00-80Z
10 69-50329-12 • ROD INSTL – POSITION TIE 1 FOR DETAILS SEE: 53-42-00-80Z
15 69-622-78-4 • GROUND INSTL 120 NAS1801-3-8 •• SCREW 120 NAS1801-4-8 •• SCREW 125 NAS1149D0316H •• WASHER 330 NAS1149D0316H •• WASHER 230 NAS1149D0416H •• WASHER 235 BACW10P6AL •• WASHER 135 BACW10P11AL •• WASHER 140 MS21042L3 •• NUT 140 MS21042L4 •• NUT 145 NAS1801-4 •• SCREW 145 NAS1801-3 •• SCREW 150 NAS1149D0416H •• WASHER 250 NAS1149D0316H •• WASHER 255 NAS1149D0316H •• WASHER 255 NAS1149D0416H •• WASHER 260 MS21042L3 •• NUT 160 MS21042L4 •• NUT 165 1002BC15 •• JUMPER ASSY 165 BACJ40A20-15 •• JUMPER ASSY 165 BACJ40D20-120 •• JUMPER ASSY 165 RBEJ40D11-96 •• JUMPER ASSY 170 BACB30NT3K5 • BOLT 1675 NAS1149D0332J • WASHER 1680 415N4002-39 • FITTING ASSY 285 BACC10JB032C046 • CLAMP 190 65C35726-12 • SEAL - FLOOR 1250 101721-101 • GALLEY ASSY 1
--255 BACB30LE5K13 • BOLT 8--260 BACW10BP5CD • WASHER 8
-- ITEMS NOT ILLUSTRATED
CHAPTER
INDICATING/ RECORDING
SYSTEM
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-24-99Z 31-24-24 MOD 0952 Fig 99Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY) FIGURE 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-24-99Z 31-24-24 MOD 0952 Fig 99Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-0952-001 INSTALLATION OF A MINI QUICK ACCESS RECORDER 001001 RF
10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
LIGHTS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
33-11-00-05Z 33-11-00 MOD 0948 Fig 5Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
LIGHT INSTL – CONT CAB CREW Figure 5Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
33-11-00-05Z 33-11-00 MOD 0948 Fig 5Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
5Z --1 AGMIS10-B73E-0147 SECOND OBSERVERS STATION INSTL 001001 RF
10 34265-8 • LIGHT ASSY 120 65-45757-5 • BRACKET 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
NAVIGATION
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-28-31-02Z 34-28-31 MOD 0866 Fig 2Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY) FIGURE 2Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-28-31-02Z 34-28-31 MOD 0866 Fig 2Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
3Z --1 AGM10-B73E-0048 IRS 2005 MAGNETIC VARIATION TABLE ACTIVATION 001001 RF
10 S242T101-117 • UNIT – INERTIAL REFERENCE 1 NOTE: EXISTING IRU PART NO. S242T101-114, WILL BECOME S242T101-117 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AE-34-0027 PER BOEING SERVICE LETTER 737-SL-34-177
10 S242T101-118 • UNIT – INERTIAL REFERENCE 1 NOTE: EXISTING IRU PART NO. S242T101-115, WILL BECOME S242T101-118 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AE-34-0006 PER BOEING SERVICE LETTER 737-SL-34-177
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-53-21-01B 34-53-21 MOD 0057 Fig 1B FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
EQUIPMENT INSTL – ELECTRICAL RACKS (ATC TRANSPONDER ONLY)
Figure 1B
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-53-21-01B 34-53-21 MOD 0057 Fig 1B FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
1B --1 MEO-0057-001 INSTL OF ELEMENTARY/ENHANCED MODE S SYSTEM 001001 RF
10 066-01127-1602 • TRANSPONDER - ATC 2 SUPPLIER CODE: V97896 ELECTRICAL EQUIPMENT NUMBER: M00163 M00381 MAINTENANCE MANUAL REF: 34-53-02 POST AERODEC MOD: MOD 0057
-- ITEMS NOT ILLUSTRATED
CHAPTER
OXYGEN
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-02Z 35-12-00 MOD 0948 Fig 2Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 2Z (SHEET 1 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-02Z 35-12-00 MOD 0948 Fig 2Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 2Z (SHEET 1 OF 2)
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-02Z 35-12-00 MOD 0948 Fig 2Z FEB 01/11 Page 2
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
2Z --1 AGMIS10-B73E-0147 SECOND OBSERVERS STATION INSTL 001001 RF
10 801307-00 • OXYGEN CYLINDER ASSY 120 69-46296-7 • BRACKET 130 65-53541-364 • TUBE ASSY 140 65-53541-397 • TUBE ASSY 150 65-53541-404 • TUBE ASSY 160 69-45719-1 • TUBE GUARD 1
--70 AN924-5D • TUBE NUT 1--80 NAS1149DN832H • WASHER 2--90 BACC10DK5 • TUBE CLAMP 5--100 BACE21AW0505L • ELBOW 1--110 BACN10GH3-12 • SPACER PLATE 1--120 BACR15BB3D4 • RIVET 2--130 BACT16AZ050505L • TEE 1--140 MS21902D5 • UNION 1--150 MS21908D5 • ELBOW 1--160 NAS1801-3-9 • SCREW 1--170 NAS1801-3-15 • SCREW 1--180 NAS1801-3-17 • SCREW 1--190 NAS1801-3-25 • SCREW 2--200 NAS42DD-6-32 • SPACER 3--210 NAS42DD-6-40 • SPACER 2--220 NAS602-7P • SCREW 2
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-20Z 35-12-00 MOD 0948 Fig 20Z FEB 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 20Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-20Z 35-12-00 MOD 0948 Fig 20Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
20Z --1 AGMIS10-B73E-0147 SECOND OBSERVERS STATION INSTL 001001 RF
15 69-50982-12 • PANEL ASSY – SUPPORT 160 69-36613-2 • SHELF ASSY – OXY MASK 165 65-63685-5 • ANGLE 270 65-57439-3 • CLIP 275 69-50983-2 • ANGLE ASSY 180 69-50984-1 • ANGLE ASSY 185 69-74512-3 • BRACKET ASSY 193 69-50981-11 • CLOSURE PANEL ASSY 1105 69-45759-142 • FITTING ASSY 1
--110 AN960PD10L • WASHER 7--120 BACN10JC3 • NUT 15--130 BACN10JR3F • NUTPLATE 2--140 BACR15BA3A6 • RIVET 4--150 BACR15BB4D4 • RIVET 2--160 BACR15BB6D6 • RIVET 2--170 BACW10X4 • RETAINING RING 2--180 NAS1801-3-11 • SCREW 2--190 NAS514P1032-6 • SCREW 6--200 NAS514P632-7 • SCREW 4--210 NAS601-5P • SCREW 2--220 NAS601-8P • SCREW 2--230 NAS603-10P • SCREW 2--240 NAS603-6P • SCREW 3--250 NAS603-8P • SCREW 2--260 66-23277-2 • INSULATION PLATE 1--270 66-3044-1 • HEADPHONE HOOK 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
AIRBORNE AUXILIARY
POWER
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
49-70-00-02Z 49-70-00 MOD 0949 Fig 2Z FEB 01/11 Page 0
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ENGINE ASSY – APU (INDICATING ONLY) FIGURE 2Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
49-70-00-02Z 49-70-00 MOD 0949 Fig 2Z FEB 01/11 Page 1
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FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
2Z --1 AGM10-B73E-0049 APU HOURMETER INSTALLATION 001001 RF
10 698788-2 • HOURMETER 120 LL54N40S4 • SCREW 230 NAS1149CN416R • WASHER 240 698431-1 • SHOCK MOUNT 150 QS200M24S • CLAMP 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
FUSELAGE
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
53-42-00-80Z 53-42-00 AGMIS06-B73E-0126 Fig 80Z FEB 01/11 Page 0
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ROD INSTL – NO.1 AND No.4B GALLEY POSITION TIE Figure 80Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
53-42-00-80Z 53-42-00 AGMIS06-B73E-0126 Fig 80Z FEB 01/11 Page 1
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FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
80Z --5 69-50328-9 ROD INSTL – NO.1 GALLEY 001001 RF
18 MS20392-5C41 • PIN 119 MS20392-5C27 • PIN 125 AN960JD616 • WASHER 152 69-40791-1 • LUG ASSY - SPRT 1
ATTACHING PARTS --53 BACB30NF8 • BOLT 1--54 AN960-816 • WASHER AR--55 69235-820CD • NUT 1
- - - * - - - 56 BACB28B6-323P •• BUSHING 257 AN960C816 •• WASHER 258 69-40791-2 •• LUG 160 1042-6 • ROD ASSY 1
110 69-50329-11 ROD INSTL – NO.4B GALLEY RF115 BACB30NF6-18 • BOLT 2117 MS24665-304 • PIN 2118 MS20392-5C31 • PIN 1122 MS20392-5C31 • PIN 1125 AN960-616 • WASHER 2125 AN960JD616 • WASHER 2140 MS21042L6 • NUT 2150 1042-5 • ROD ASSY 1155 69-40791-1 • LUG ASSY - SPRT 1
ATTACHING PARTS --160 BACB30NF8 • BOLT 1--165 AN960-816 • WASHER 1--170 BMN4122AD3-8 • NUT 1--170 69235-820CD • NUT 1
- - - * - - - 175 BACB28B6-323P •• BUSHING 2180 AN960C816 •• WASHER 2185 69-40791-2 •• LUG 1
500 69-50329-12 ROD INSTL – NO.4B GALLEY RF505 MS24665-304 • PIN 4510 MS20392-5C31 • PIN 4513 MS20392-5C41 • PIN 2515 AN960JD616 • WASHER 4520 1042-5 • ROD ASSY 1522 1042-5 • ROD ASSY 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
53-42-00-81Z 53-42-00 AGMIS06-B73E-0126 Fig 81Z FEB 01/11 Page 0
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ROD INSTL – NO.2 GALLEY POSITION TIE Figure 81Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
53-42-00-81Z 53-42-00 AGMIS06-B73E-0126 Fig 81Z FEB 01/11 Page 1
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
81Z --5 69-50334-68 ROD INSTL – NO.2 GALLEY 001001 RF
15 MS24665-304 • PIN 216 MS20392-5C35 • PIN 118 MS20392-5C41 • PIN 130 AN96JD616 • WASHER 250 1042-5 • ROD ASSY - TIE 160 BACB30NF8 • BOLT 165 69-40794-1 • FILLER 170 AN960-816 • WASHER 175 69235-820CD • NUT 180 69-40791-1 • LUG ASSY 185 AN960C816 •• WASHER 290 BACB28B6-323P •• BUSHING 295 69-40791-2 •• LUG 1
-- ITEMS NOT ILLUSTRATED
AIRCRAFT
MAINTENANCE
MANUAL
Contents
AMM-CONTENTS Page 1
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®
Chapter 11 PLACARD & MARKINGS
Chapter 21 AIR CONDITIONING
Chapter 22 AUTO FLIGHT
22-11-01 – DIGITAL FLIGHT CONTROL SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 23 COMMUNICATIONS
23-24-00 – EMERGENCY LOCATOR TRANSMITTER SYSTEM
PAGE BLOCK 1 – DESCRIPTION AND OPERATION
PAGE BLOCK 101 – FAULT ISOLATION
PAGE BLOCK 201 – MAINTENANCE PRACTICES
PAGE BLOCK 501 – ADJUSTMENT/TEST
23-24-11 – EMERGENCY LOCATOR TRANSMITTER ANTENNA
PAGE BLOCK 401 – REMOVAL AND INSTALLATION
23-71-00 – VOICE RECORDER SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-11-11 – FLIGHT COMPARTMENT EQUIPMENT
PAGE BLOCK 201 – MAINTENANCE PRACTICES
Chapter 26 FIRE PROTECTION
Chapter 27 FLIGHT CONTROLS
Chapter 28 FUEL
Chapter 29 HYDRAULIC POWER
Chapter 30 ICE AND RAIN PROTECTION
Chapter 31 INDICATING/RECORDING SYSTEMS
31-24-24 – QUICK ACCESS RECORDER (MINI)
PAGE BLOCK 201 – MAINTENANCE PRACTICES
Chapter 32 LANDING GEAR
Chapter 33 LIGHTS
Chapter 34 NAVIGATION
34-22-00 – ELECTRONIC FLIGHT INSTRUMENT SYSTEM – EFIS DISPLAY MODES TEST
PAGE BLOCK 501 – ADJUSTMENT/TEST
AMM-CONTENTS Page 2
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®
34-49-03 – GROUND PROXIMITY WARNING SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
34-53-02 – ATC SYSTEM
PAGE BLOCK 1 – DESCRIPTION AND OPERATION
PAGE BLOCK 501 – ADJUSTMENT/TEST
34-62-01 – FLIGHT MANAGEMENT COMPUTER SYSTEM – PROGRAM PIN VERIFICATION
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 35 OXYGEN
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
Chapter 49 AIRBORNE AUXILIARY POWER
49-72-11 – ELAPSED TIME INDICATOR
PAGE BLOCK 401 – REMOVAL/INSTALLATION
Chapter 52 DOORS
Chapter 53 FUSELAGE
Chapter 54 NACELLES / PYLONS
Chapter 55 STABILIZERS
Chapter 56 WINDOWS
Chapter 57 WINGS
Chapter 71 POWER PLANT
Chapter 73 ENGINE FUEL AND CONTROL
Chapter 74 IGNITION
Chapter 75 AIR
Chapter 77 ENGINE INDICATING
Chapter 78 EXHAUST
Chapter 79 OIL
Chapter 80 STARTING
Chapter 91 CHARTS
Chapter 93 PANELS
CHAPTER
AUTO FLIGHT
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
22-11-01001 Page 501 MOD 1093 JAN 01/12
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DIGITAL FLIGHT CONTROL SYSTEM – ADJUSTMENT/TEST 1. General
A. This procedure has one task, to carry an Option Pin Check of the Digital Flight Control System. The Option Pin Check is part of the System Test.
B. Any other test associated with the Digital Flight Control System in accordance with
22-11-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
2. System Test – DFCS – Option Pin Check Only
A. Location Zones
Zone Area
101 Control Cabin - Left 102 Control Cabin - Right
B. Prepare for the System Test
SUBTASK 22-11-01-845-129
(1) Do the preparation for the DFCS BITE test in this task: "Operational Test - Digital Flight Control System".
C. Option Pin Check
SUBTASK 22-11-01-745-020
(1) Do the Option Pin Check:
(a) Open the AFCS B FCC DC circuit breaker on P6-2 Circuit Breaker Panel.
(b) [If POST SB 737-34-1593] Set the FMC transfer switch to NORMAL position.
(c) Push the INIT/REF key on the CDU keyboard to show the POS INIT page or PERF INIT page.
(d) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page.
(e) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page.
(f) Push the LSK adjacent to <DFCS to show the DFCS BITE TEST LINE MAINT
1/2 page.
(g) [If POST SB 737-34-1593] Ignore the message "MOVE FMC TRANSFER SWITCH TO BOTH ON L" shows on the CDU and keep the position of the FMC transfer switch in the NORMAL position.
(h) Stop for approximately 15 seconds.
(i) Push the LSK adjacent to <PUSH IF NO RESPONSE.
(j) Push the LSK adjacent to <CONTINUE.
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EFFECTIVITY
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(k) Push the NEXT PAGE key on the CDU to show the DFCS BITE TEST OVERNIGHT MAINT 2/2 page.
(l) Push the LSK adjacent to <SENSOR VALUES to show the Sensor Values Test
Index page.
(m) Push the LSK adjacent to <OPTIONS (SOP) to show the first page of the standard options.
(n) Push the LSK adjacent to <CONTINUE to show the second page of the
standard options.
(o) For AERODEC MOD-1093, Make sure that the following options on Table 502 are displayed or not displayed on the CDU display.
Table 502
SOP – A/S WARNING NOT DISPLAYED
SOP – PARITY CLOSED DISPLAYED
(p) Close the AFCS B FCC DC circuit breaker on the P6-2 Circuit Breaker
Panel.
(q) Open the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.
(2) Do the steps in the Option Pin Check again for the channel B.
(3) Close the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.
(4) Push the INIT/REF key on the CDU keyboard to get out of the BITE.
D. If required, continue testing in accordance with 22-11-01 Page Block 501 of the
appropriate AMM, or Put the Airplane Back to Its Initial Condition in accordance with 22-11-01 Page Block 501.
CHAPTER
COMMUNICATIONS
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-24-00AIRPLANES WITH ARTEX C406-1 ELT Page 1 MOD 0889 SEP 01/13
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EMERGENCY LOCATOR TRANSMITTER SYSTEM - DESCRIPTION AND OPERATION
1. General Note: For the current description and operation please refer to Emteq AMM Supplement
Document No. 2-22566-908
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EFFECTIVITY
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EMERGENCY LOCATOR TRANSMITTER SYSTEM
- FAULT ISOLATION 1. General Note: For the current Fault Isolation processes please refer to Emteq AMM Supplement
Document No. 2-22566-911
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE PRACTICES
1. General Note: For the current Maintenance Practices please refer to Emteq AMM Supplement
Document No. 2-22566-915
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EFFECTIVITY
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EMERGENCY LOCATOR TRANSMITTER SYSTEM
- ADJUSTMENT & TEST 1. General Note: For the current testing processes please refer to Emteq AMM Supplement
Document No. 2-22566-914
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-24-11AIRPLANES WITH ARTEX C406-1 ELT Page 401 MOD 0889 SEP 01/13
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EMERGENCY LOCATOR TRANSMITTER SYSTEM - REMOVAL AND INSTALLATION
1. General Note: For the Removal and Installation processes please refer to Emteq AMM Supplement
Document No. 2-22566-913
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 501 MOD 0916 APR 01/13
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EFFECTIVITY
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EFFECTIVITY
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EFFECTIVITY
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EFFECTIVITY
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EFFECTIVITY
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H. AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Voice Recorder AUTO/ON Switch Test
(1) TEST WITHOUT ENGINES RUNNING
NOTE: Additional relays are added to tum the CVR "on" when either engine is running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.
(a) Close all applicable circuit breakers to the CVR system.
(b) At the P5 overhead panel, at the cockpit voice recorder (CVR) control panel,
connect a 600 ohm headset to the CVR monitor jack.
(c) Make sure the CVR AUTO/ON switch is in the AUTO position.
(d) Make sure ambient cockpit audio is not heard over the headset. The CVR is OFF.
(e) On the CVR P5 control panel; AIRPLANES WITH VOICE RECORDER CONTROL PANEL
WITH METER; Make sure that the voice recorder control panel meter needle does not move while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light does not come on while you push the TEST switch.
(f) Make sure the CVR AUTO/ON switch is in the ON position.
(g) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(h) On the P5 control panel and make sure that; AIRPLANES WITH VOICE RECORDER
CONTROL PANEL WITH METER; Make sure that the voice recorder control panel meter needle moves and stays in the green area while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light comes on while you push the TEST switch.
(i) At the P18-2 panel, open circuit breaker (C9500) VOICE RECORDER RELAY.
(j) Make sure the CVR Auto/On switch automatically switches to the AUTO position.
(k) Make sure you cannot hear flight deck conversation in the headset. The CVR
is OFF.
(l) Close circuit breaker (C9500) VOICE RECORDER RELAY.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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(2) TEST WITH ENGINES RUNNING
NOTE: Additional relays are added to tum the CVR "on" when either engine is
running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.
(a) Make sure the CVR AUTO/ON switch is in the AUTO position.
(b) Start No. 1 Engine Per AMM 71-00-00/201, ensure the No. 1 Eng N2 Gauge is
>46.33%.
(c) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(d) Shut down No.1 Eng Per AMM 71-00-00/201.
(e) Wait six minutes.
NOTE: The CVR switch circuit relay R9500 will tum the CVR off after five minutes.
(f) Make sure you cannot hear flight deck conversation in the headset. The CVR
is OFF.
(g) Start No. 2 Engine Per AMM 71-00-00/201, ensure the No. 2 Eng N2 Gauge is >46.33%.
(h) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(i) Shut down No.2 Eng Per AMM 71-00-00/201.
(j) Wait six minutes.
NOTE: The CVR switch circuit relay R9500 will turn the CVR off after five
minutes.
(k) Make sure you cannot hear flight deck conversation in the headset. The CVR is OFF.
I. Put the Airplane Back to the Usual Condition S 085-015 (1) Remove the headphone from the control panel.
S 865-036
(2) AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Set the voice recorder AUTO/ON switch to the AUTO position. S 865-016 (3) Remove electrical power if it is not necessary (AMM 24-22-00/201)
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
25-11-11AIRPLANES WITH SECOND OBSERVER’S SEAT Page 201 MOD 0948 MAR 01/11
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CHAPTER
INDICATING/ RECORDING
SYSTEM
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 201 MOD 0952 FEB 01/11
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QUICK ACCESS RECORDER (MINI) – MAINTENANCE PRACTICES 1. General A. This procedure has this task: 1) The return to service test of the mini Quick Access Recorder (QAR). 2. Return to Service Test A. Test Equipment and Material
Reference Description 802-0208 RSU II Kit or functionally equivalent computer with USB port. 700-0179 miniQAR MKII HS USB I/F Software (included with 805-0005) 605-0177 Portable Test Interface (PTI) Cable 805-0005 miniQAR MKII, HS USB I/F KIT Includes PTI cable (605-0177)
and software (700-0179) B. Test Setup
1) Connect PTI cable P/N 605-0177 to the UUT DB9 connector.
NOTE: Do not Connect the USB connector of the PTI cable P/N 605-0177.
C. Procedures
1) Turn-on the PC or RSU II and allow it to boot.
2) If the RSU Menu is displayed, select File, Exit to Windows (refer to the RSU II Operations Manual, Part Number 900-0208 – included in the RSU II Kit.)
3) On the Windows toolbar, select Start, Programs, Avionica, and MiniQAR Support
Util.
4) Connect the USB connector of the PTI cable P/N 605-0177 to the USB Port of the PC or RSU II.
5) Make sure that the BIT LED of the Unit Under Test is illuminated.
6) Select “Tools”.
7) A “Return to service” prompt appears. Select “Yes”
8) A message “Return To Service In-Progress Please Wait” will be displayed.
9) The “Please Wait” will be replaced by a Results screen. Make sure all results
indicate PASSED.
10) Select “Continue”.
11) Verify that the miniQAR LED is blinking.
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EFFECTIVITY
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12) Select “OK”. Make sure the message appears “miniQAR Successfully Erased”
13) Select “OK”. Make sure the message appears “Return to Service Complete. You may now disconnect the miniQAR”
14) Disconnect the USB connector of the PTI cable P/N 605-177 from the USB Port
of the PC or RSU tablet first.
15) Disconnect the DB9 connector of the PTI cable PN 605-0177 from the UUT DB9 connector.
16) End of test. The miniQAR can now be returned to service.
CHAPTER
NAVIGATION
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
34-22-00001 (PV301) Page 501 MOD 0861 APR 01/11
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ELECTRONIC FLIGHT INSTRUMENT SYSTEM – ADJUSTMENT/TEST 1. General
A. This procedure has one task, to carry An EFIS Display Modes Test of the EFIS System. The EFIS Display Modes Test is part of the Operation Test of the EFIS System
B. Any other test associated with the EFIS System in accordance with 34-22-00 Page
Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
C. EFIS Display Modes Test
SUBTASK 34-22-00-865-028-001
(1) Make sure the EFI transfer switch is in the NORMAL position.
SUBTASK 34-22-00-865-149-001
WARNING: DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS ADDED OR REMOVED IN AREA 200 FEET OR LESS OF THE ANTENNA. THIS CAN CAUSE AN EXPLOSION.
DO NOT OPERATE THE WEATHER RADAR WHILE THE AIRPLANE IS IN A HANGAR OR OTHER ENCLOSURE. MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET OR LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN CAUSE INJURY TO PERSONS.
(2) On the two EFIS control panels, set the controls as follows:
(a) The RANGE switch to the 80 position.
(b) The map mode display switches to the on position.
(c) The WXR ON switch to the on position.
SUBTASK 34-22-00-745-030-001
(3) Push the INIT/REF key on the FMCS CDU.
SUBTASK 34-22-00-745-031-001 (4) Push the line select key (LSK) 6L (<INDEX) on the FMCS CDU.
SUBTASK 34-22-00-745-032-001
(5) Push the LSK 6R (MAINT>).
(a) Make sure the FMCS CDU display shows the MAINT BITE INDEX 1/1 page.
SUBTASK 34-22-00-745-033-001 (6) Push the LSK 5L (<EFIS).
(a) Make sure the FMCS CDU display shows the EFIS BITE TEST page.
SUBTASK 34-22-00-745-034-001
(7) Push the LSK 3L (<SELF TEST).
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SUBTASK 34-22-00-755-189-001
(8) AIRPLANES WITH EFIS SYMBOL GENERATOR P/N S242T404-413 AND ON; Make sure the hex code lines on the bottom right of the two EADIs show as follows:
Table 501/34-22-00-993-804-001
FA391B0 87BE000 C080000
SUBTASK 34-22-00-865-035-001
(9) On the left and right EFIS control panels, set the mode switches to the positions as follows:
(a) FULL NAV (b) EXP NAV (c) FULL VOR/ILS
NOTE: To show the VOR mode, a VOR frequency (108.00) must be set on the
VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.
(d) EXP VOR/ILS
NOTE: To show the VOR mode, a VOR frequency (108.00) must be set on the
VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.
(e) MAP (f) CTR MAP (g) PLAN
SUBTASK 34-22-00-755-036-001
(10) For each mode on the left EFIS control panel, make sure the applicable test patterns show on the left display units.
SUBTASK 34-22-00-755-037-001
(11) For each mode on the right EFIS control panel, make sure the applicable test patterns show on the right display units.
SUBTASK 34-22-00-755-038-001
(12) For each mode on the two EFIS control panels, make sure the test patterns are the same on the two EADIs and the two EHSIs.
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GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST 1. General
A. This section carries out an operational test of the Enhanced Ground Proximity Warning System (EGPWS) to support the continuous operation of AeroDEC Modification MOD-0865.
2. Enhanced Ground Proximity Warning System - Operational Test
A. References
Reference Title
24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)
B. Location Zones
Zone Area
101 Control Cabin - Left 102 Control Cabin - Right 205 Electronic Compartment
C. Prepare for the Test
(1) Supply electrical power (Ref PAGEBLOCK 24-22-00/201).
(2) Make sure this circuit breaker is closed:
(a) P18 Circuit Breaker Panel
1) TERRAIN DISPLAY 2) ENHANCED GND PROX
D. Operational Test
(1) Carry out a Level 1 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system:
AURAL WARNING LIGHTS EADI
"Minimums" "1000" "500" "100" "50" "40" "30" "20" "10"
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(2) Carry out a Level 2 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI
“CURRENT FAULTS” “NO FAULTS” “PRESS TO CONTINUE”
(3) Carry out a Level 3 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI
“ALTITUDE CALLOUT MENU 91”
E. Put the Airplane Back to Its Usual Condition
(1) Remove electrical power if it is not necessary (PAGEBLOCK 24-22-00/201).
------------------------- END OF TASK ---------------------------
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ATC SYSTEM - DESCRIPTION AND OPERATION 1. General (Fig. 1)
A. The Air Traffic Control Radar Beacon System, (ATC system), provides airplane tracking, altitude and
identification information to an ATC ground station. The ATC transponder responds to an interrogation from an ATC ground station. The ATC system responds to ground station interrogations in one of three different modes: mode-A, mode-C and mode-S. Mode-A and Mode-C provide identification and altitude information. Mode-S provides selective airplane identification and data link capabilities. After a ground station interrogation, the transponder automatically transmits a pulse coded reply signal in one of the above modes. The mode of reply is determined by the mode of interrogation.
B. Two ATC systems are installed on the airplane, each with its own transponder. Only one transponder operates at
a time. A dual ATC control panel provides independent and isolated control for both systems. Control information is sent to either transponder by signal discretes and an ARINC 429, 572, 718, or 730 bus.
C. There are two ATC antennas on the airplane. The antennas are shared by the two transponders. Two rf relays
switch both antennas from one transponder to the other.
D. Each transponder receives altitude data from both air data computers (ADCs). The altitude data is sent to the transponders by an ARINC data bus.
E. The airplane’s Flight ID information is provided from data relayed by the Flight Management System (FMS).
F. The ATC and DME systems operate in the same L-band frequency range. A suppression circuit is connected
between the ATC transponders and the DME interrogators to prevent simultaneous transmissions.
G. The ATC system operates in three different modes: Mode-A, mode-C and mode-S. The mode of operation is determined by the mode of interrogation from a ground station and the current configuration of the altitude reporting function.
H. The No. 1 ATC system receives 115 volt, 400 Hz ac power from the electronics power bus No. 1. Power is
supplied through the ATC-1 circuit breaker located on the left load control center circuit breaker panel P18.
I. The No. 2 ATC system receives 115 volt, 400Hz ac power from the electronics power No. 2 bus. Power is supplied through the ATC No. 2 circuit breaker which is located on the right load control center circuit breaker panel P6.
2. ATC Control Panel (Fig. 1)
A. The ATC control panel is located on the aft electronic control panel (P8). The control panel contains switches and controls which provide reply codes and mode selection for two ATC/Mode S transponders.
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ATC System Component Location Figure 1
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3. ATC Transponder (Fig. 1)
A. The ATC transponders are located on the E2 electronic equipment rack. B. The active ATC transponder transmits a coded reply when it is interrogated by an ATC ground station.
(1) Both transponders are identical to each other. Each transponder and the following switches and indicators:
(a) A green TPR indicator light which comes on when a transponder self-test is successful.
(b) A red TPR indicator light which comes on when a transponder self-test detects a failure.
(c) A red ALT indicator light which comes on when the altitude input source indicates a barometric altitude
failure.
(d) A red DATA IN indicator light which comes on if an error is detected in the ARINC 429 control word from the control panel.
(e) A red TOP indicator light which comes during a self-test when the upper antenna impedance is incorrect.
(f) A red BOT indicator light which comes during a self-test when the lower antenna impedance is incorrect.
(g) A TEST switch which starts a transponder self-test.
4. ATC Antenna
A. Two ATC antennas are installed in the airplane. The antennas are on the top and the bottom of the airplane. Two rf switching relays connect both antennas to the active transponder. The top antenna is located on the centerline of the fuselage at station 430.25. The bottom antenna is located on the centerline of the fuselage at station 355. The antennas are omnidirectional L-blade type antennas. Each antenna can transmit and receive signals for the active transponder. The active transponder automatically uses the antenna with the greatest signal strength.
5. Operation
A. Mode-A and Mode-C
(1) There is no power switch on the ATC control panel. Power is applied to the system when the ATC-1 and ATC-2 circuit breakers on the P6-1 and P18-1 panels (fig. 2) are closed. On systems with two antennas, power is aplied to both ANTENNA TRANSFER RELAYs when the ATC ANTENNA SW circuit breaker on the P6-1 panel (fig. 2) is closed.
(2) The desired ATC system (No. 1 or No. 2) is set with the transponder select switch. The '1' position causes
the control panel to send an 'ON' discrete to transponder No. 1 if the AIR/GND RELAY is in AIR mode and the altitude reporting switch is set to ALT OFF or ALT ON. The '2' position causes the control panel to send an 'ON' discrete to transponder No. 2 if the AIR/GND RELAY is in AIR mode and the altitude reporting switch is set to ALT OFF or ALT ON.
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ATC System Block Interface Schematic Figure 2
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(3) The desired 4-digit ATC code is set by pressing the FCN key to highlight the ATC code entry within the ATC
Control Panel window. Entry of the desired code is carried out by pressing the relevant alpha/numeric keys. (4) The altitude reporting switch is set to ALT OFF or ALT ON to set the desired altitude reporting function. (5) If the altitude reporting function is on, then the ATC system will reply to mode-A and mode-C ground station
interrogations. If the altitude reporting function is off, then system will reply to mode-A interrogations. Mode-S replies are not affected by the condition of the mode switch.
(6) The Flight identity code and mode configuration information is sent to the transponders through ARINC
busses and discretes. The 4-digit code identifies the airplane to the ground station for mode-A and mode-C interrogations.
(7) When the airplane leaves the ground, the AIR/GND relay is set to AIR. This sends a discrete signal to the
control panel. The control panel then sends an 'ON' discrete to the selected transponder. At this point, the system will respond to ground station interrogations.
B. Mode-S Operation
(1) Mode-S functions operate on an airplane if the mode-S programming plug is configured with a unique mode-
S address. If all the programming pins are grounded (they have a bit value of one), then there is no unique address and the mode-S functions do not operate. The mode-S code is hard wired on mode-S equiped airplanes. The identity code set on the ATC control panel has no effect on the mode-S address code of the airplane. Mode-S functions in the airplane are automatic and are not configured by the pilot.
C. Self-Test Operation
(1) Both ATC transponders have Built-In Test Equipment (BITE). A BITE test can be started if the transponder
to be tested has power. The BITE test is started when the TEST switch on the transponder face is pushed. The BITE test does the following:
⎯ Does a checksum of internal ROM contents. ⎯ Tests the transponder RAM. ⎯ simulates noise sources and monitors the results. ⎯ Tests the antenna impedance. ⎯ Simulates a Mode-S All-Call interrogation and reply. ⎯ Samples the internal power supply monitor. ⎯ Checks the operation of the serial busses connected to the transponder
(2) The green TPR indicator light will come on if no errors were detected during the BITE test. The red TPR
indicator light will come on if any part of the BITE test fails. (3) The BITE monitor continuously tests transponder functions while the ATC system operates normally (not in
test mode). If a failure is detected, the red TPR indicator light will come on and a TRANSPONDER FAIL DISCRETE will be sent to the control panel. If the altitude input from the ADC is in error, the red ALT indicator light will come on.
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MODE-S Programming Pin Locations for ATC-1 and ATC-2 Transponders Figure 3
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ATC System Pulse Codes Figure 4
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ATC System Reply Pulse Codes Figure 5
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ARINC 429 Data Control Word Format Figure 6
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ATC SYSTEM - ADJUSTMENT/TEST 1. General
A. The ATC system adjustment/test procedure contain two tasks. One is an operational test; the other is a system test. The operational test is a fast check of the ATC system and no test equipment is needed. The system test first does the operational test. Then it uses test equipment to examine the ATC code reception, altitude reporting, transponder sensitivity, side lobe suppression and transmitter frequency.
B. The system test uses the Instrument Flight Research 601 ATC ramp test set.
C. Because the ATC transponder responds to signals from the antenna with the strongest signal strength, it is necessary to put the test set antenna close to the airplanes antenna to do a proper test. The test set antenna should be put near the bottom ATC antenna on the airplane to examine the bottom transponder circuitry and the same for the top ATC antenna.
TASK 34-53-02-715-003
2. Operational Test - ATC System
A. General
(1) The operational test is a fast check of the ATC system. It uses only the system's BITE function. No special test or ground equipment is necessary.
(2) The ATC transponder internal BITE circuitry do a self-test on all internal circuitry. This includes the injection
of Mode S signals into the receiver unit to examine if the signals are processed properly. If the Mode S function fails, the red TPR FAIL LED indicator comes on.
B. References
(1) AMM 24-22-00/201, Manual Control
C. Access
(1) Location Zones
101/102 Flight Compartment 205 Electronic Compartment
(2) Access Panel
1201 Electronics Equipment Access Door
D. Prepare for the Operation Test
S 865-004 (1) Supply electrical power (AMM 24-22-00/201).
S 865-005
(2) Close these circuit breakers.
(a) P18 Load Control Center – Left 1) ATC 1
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(b) P6 Load Control Center – Right 1) ATC 2
E. Procedure
S 865-236
(1) On the ATC control panel, set the transponder select switch to the applicable system.
(a) Start the self test on the front of the transponder.
(b) Make sure the LEDs sequence that follow occurs:
1) All LEDs come on for about three seconds
2) All LEDs go off for about two seconds 3) The green LED comes back on.
(c) Release the TEST switch. S 865-253
(2) Set the ATC system to STBY.
TASK 34-53-02-735-049 3. System Test - ATC System for Airplanes with Elementary Surveillance (With the IFR ATC-601 Test Set with
Software Version 3 or later)
A. General
(1) This system test is a more complete check of the ATC system. The system test first does the ATC - Operational Test. Then it uses ground test equipment to examine the left and right ATC systems.
(2) The IFR 601 test set is used to test the functionality of the mode S transponder. All twenty tests can be run
automatically in the AUTO mode or individually in single test mode. Results from the last test are shown on each test page. The PASSED/FAILED indication is shown on top of the page. To do a single test, use the select keys to get to the desired test and push the RUN/STOP key.
B. Special Tools and Equipment
(1) ATC Transponder Ramp Test Set IFR ATC-601
C. References
(1) AMM 24-22-00/201, Manual Control
(2) AMM 34-12-01/501, Air Data Computer System
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D. Access
(1) Location Zones 101/102 Flight Compartment 205 Electronic Compartment
E. Prepare for the System Test
S 845-050
CAUTION: DO NOT PLACE THE REMOTE TEST SET ANTENNA CLOSER THAN 15 INCHES (0.40
METERS) TO THE AIRCRAFT ANTENNA WITH THE TEST SET ON. THIS WILL CAUSE DAMAGE TO THE TEST SET.
(1) Put the test set antenna approximately 30 feet from the ATC antenna for the related system.
Note: The test set antenna must be within the line of sight of the ATC antenna.
S 845-051
(2) Put the test set antenna in position towards the aircraft antenna.
S 845-052 (3) Connect the coax cable from the remote test set antenna to the test set.
S 865-053
(4) Close these circuit breakers:
(a) P18 Load Control Center - Left 1) ATC 1
(b) P6 Load Control Center - Right
1) ATC 2
S 715-154 (5) Do the ATC Operational Test.
S 865-054
(6) Set the PWR switch on the test set to the ON position.
Note: The test set is a source of interference for radio and L-band radar equipment operating on the airplane and located near the test set. Turn the test set off as soon as the test is completed or when you must perform other radio checks on the airplane.
S 865-055
(7) Push the SETUP key to enter the SETUP menu.
Note: For information regarding the battery test, timing and recharging refer to the operation section of the test set operators manual.
S 865-155
(8) Push the SELF TEST key on the test set.
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S 865-156 (9) Push the RUN/STOP key to start the self test.
(a) Make sure the test set display shows PASSED.
S 865-157
(10) Push the SETUP key to enter the SETUP menu.
S 865-056 (11) Enter 30 feet in the RANGE field for the TOP and BOTTOM antenna.
S 865-158
(12) Enter 17 feet for the HEIGHT field for the TOP antenna and 3 feet for the BOTTOM antenna.
S 865-159 (13) Choose the bottom antenna on the SELECTED field.
(a) Use the SLEW keys to change the values. (b) Use the SELECT keys to change the items.
(c) Use the SELECT keys to select the antenna which you must test.
S 865-267
(14) Enter the gain listed on the test set antenna into the GAIN_1030 and GAIN_1090 field.
S 865-231 (15) Enter the cable loss listed on the cable in the LOSS field.
S 865-160
(16) Open these circuit breaker.
(a) P6 Circuit breaker Panel
1) AIR/GND RLY and LTS 2) NOSE GEAR AIR/GND
S 865-161
(17) Set the captain's and first officer's altimeter to1013.25mb
F. ATC System Test
S 865-162
CAUTION: DO NOT USE CODES 7500, 7600-7677, AND 7700-7777. THESE ARE EMERGENCY CODES.
(1) Set the code switches on the ATC control panel to a desired ATC ID code.
(2) Using the FMC MCDU Select FMC, press the RTE Key and enter a Flight ID Code into the Flt No. field.
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Note: The Flight ID code to be entered can be any combination of letters or numbers and up to eight
characters in length. As the same keypad keys are used to enter alpha/numeric characters, you may have to press the keypad keys numerous times to enter your selected numbers/letters. Typical Flight ID – ABC123
S 865-163
(3) Set the transponder select switch on the ATC control panel to the left or No. 1 system.
S 865-168 (4) Set the altitude reporting switch on the ATC control panel to ALT ON.
S865-057
(5) Push the AUTO TEST key on the test set.
(6) Using the Pitot-Static test set compare altitude readings to the altitude reported in the replies to the IFR ATC-601 test set at altitudes from ground level to 40,000 feet at 5,000 feet intervals. The reported altitude should be within 100ft of the captains indicated altitude.
(7) On the ATC control panel, select Altitude Reporting ‘OFF’. Ensure that no altitude is displayed on the IFR
ATC-601 test set. (8) On the ATC control panel, select the ‘ALT ON’ mode of operation.
S 865-187
(9) Use the RUN/STOP key to start or stop individual test.
S865-170 (10) Use the SELECT key to select each individual test.
(11) On the ATC Control panel, momentarily press the IDENT pushbutton. Ensure that the IFR ATC-601 test set
displays the IDENT indication for 15 to 20 seconds S 735-058
(12) Do a check of the REPLY DELAY TEST.
(a) Make sure the reply delay is 3.00us (±0.50us) for ATCRBS mode.
S 735-059 (13) Do a check of the REPLY JITTER TEST.
(a) Make sure the reply jitter is < 0.06us for all call. (b) Make sure the reply jitter is < 0.1us for ATCRBS modes.
S 735-060
(14) Do a check of the ATCRBS REPLY TEST.
(a) Make sure the spacing of the F1 to F2 pulse is 20.3us (±0.10us)
(b) Make sure the duration of the F1, F2 pulse is 0.45us (±0.10us).
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S 735-061 (15) Do a check of the SLS LEVEL TEST.
(a) Make sure the reply is received when the SLS pulse is -9dB and no reply is received when the SLS
pulse is 0dB.
Note: Run the SLS level test in less than 95 feet (28.96 meters) of the UUT antenna.
S 735-062 (16) Do a check of the ATC ONLY ALL-CALL TEST.
(a) Make sure the mode S transponder did not reply to the interrogation (PASSED TEST).
S 735-063
(17) Do a check of the MODE S ALL CALL TEST.
(a) Make sure the test set shows PASSED and the airplane's mode S address.
S 735-064 (18) Do a check of the INVALID MODE S ADDRESS TEST.
(a) Make sure the mode S transponder did not reply (PASSED TEST). S 735-065
(19) Do a check of the SPR ON/OFF TEST.
(a) Make sure a reply is receive when SPR is ON and no reply is receive when SPR is OFF.
S 735-066 (20) Do a check of the MODE S UF0 TEST.
(a) Make sure (Down-link format) DF=0, AC=(airplane's altitude) and ADDRESS=(airplane's mode S
address) (WDM 34-53-12).
Note: Make sure the reported altitude is within ±125 feet of the local field elevation altitude shown on captain's and first officer's altimeter (applicable for all altitude reporting check).
S 735-067
(21) Do a check of the MODE S UF4 TEST.
(a) Make sure DF=4, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).
S 735-068 (22) Do a check of the MODE S UF5 TEST.
(a) Make sure DF=5, ID=(selected ATC ID code on the ATC control panel) and ADDRESS=(airplane's
mode S address).
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S 735-069 (23) Do a check of the MODE S UF11 TEST.
(a) Make sure DF=11 and AA = Aircraft Address
S 735-070
(24) Do a check of the MODE S UF16 TEST. (a) Make sure DF=16, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).
Note: No reply to the UF16 test is not a failure of the ATC system.
S 735-071
(25) Do a check of the MODE S UF20 TEST.
(a) Make sure DF=20, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).
Note: No reply to the UF20 test is not a failure of the ATC system.
S 735-072 (26) Do a check of the MODE S UF21 TEST.
(a) Make sure DF=21, ID=(selected ATC ID code on the ATC control panel) and ADDRESS=(airplane's
mode S address). Note: No reply to the UF21 test is not a failure of the ATC system.
S 735-073
(27) Do a check of the SQUITTER TEST.
(a) Make sure the squitter's period is between 0.8 to 1.2 seconds.
S 735-074 (28) Do a check of the FREQUENCY TEST.
(a) Make sure the reply frequency of the transponder is 1090 MHz ±1MHz.
(29) Do a check of the FLIGHT ID BDS 2.0 TEST
(a) Make sure the down-link format DF = 20, and the Flight ID field = selected Flight ID code on FMC CDU.
(30) Do a check of the MODE S UELM TEST (uplink extended length message). Ensure that the display shows passed.
(31) Do a check of the MODE S DELM TEST (downlink extended length message). Ensure that the display
shows passed.
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S 735-075 (32) Do a check of the DIVERSITY TEST.
(a) Make sure the power level difference is > 20dB between 'ON' antenna squitters and 'OFF' antenna
squitters.
Note: To make sure the dynamic range is 20dB, a diversity test must be run at a distance of less than 50 feet (15.2 meters) from the airplane antenna.
S 735-076
(33) Do a check of the MTL DIFFERENCE TEST.
(a) Make sure the Minimum Threshold Level (MTL) difference between mode A and mode C is <1.0dBm. (34) Do a check of the SELECTED VERTICAL INTENT REPORT BDS 4.0 Parts 1 and 2.
(a) On the Mode Control Panel (MCP) select an altitude of 30,000ft and if the MCP will allow it, VNAV Mode to ‘ON’ and APPR Mode to ‘OFF’.
(b) Ensure that the display shows Passed and that the MCP/FCU SEL ALT = 30,000ft, and the AA =
Aircraft Address. (c) Ensure that FMS SEL ALT = N/A, SOURCE INFO = NO and TARGET ALT = UNKNOWN.
(d) Ensure that BARO PRES SET = 1013.25mb abd that VNAV MODE, APPR MODE, ALT MODE are either ACTIVE or N/ACTIVE, dependant on selection on MCP.
(35) Do a check of the DATA LINK CAPABILITY REPORT BDS 1,0 PART 1 (a) Ensure that the display shows PASSED, SUBNET VER VBR = 000 and XPDR LEVEL = 2-4.
(b) Ensure that the display shows SPECIFUIC SER CAP REP FIELD = YES, DTE = NO, UELM SEG CAP = NO UELM and CONT FLAG = NO.
(c) Ensure that the display shows DELM SEG CAP = NO DELM, AIRCRAFT ID CAP = YES, SI CAP =
YES and SQUITTER CAP = YES (36) Do a check of Track and Turn Report BDS 5,0
(a) Ensure that the display shows PASSED, AA = Aircraft Address, ROLL ANGLE = 0.0 (±2.0) degrees and GND SPEED = 0 (±2.0) kts.
(b) Ensure that the display shows T_TRACK ANGLE = N/A and RATE = N/A.
(37) Do a check of the HEADING & SPEED REPORT BDS 6,0
(a) Set the Pitot-static test set to simulate an indicated airspeed of 250kts and a rate of climb of 1000 fpm. (b) Ensure that the display shows PASSED, AA = Aircraft Address, IND AIR SPEED = Flight Deck
indicated airspeed (±10%), BARA ALT RATE = Flight Deck indicated vertical speed, MAG HDG = Current Aircraft Heading (±2.0 degrees) and I_V_VEL = Current A/C Rate of Climb (±200 ft/min)
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(c) Release all Pitot-Static pressure from the Pitot-Static system.
S 715-184
(38) Do the system test again for the right or No. 2 ATC system and use the right or No. 2 air data source.
Note: On the test set, select the TOP ATC antenna.
G. Put the Airplane Back to Its Usual Condition
S 845-185 (1) Remove the ATC ramp test set and antenna shield.
S 865-186
(2) Close these circuit breaker.
(a) P6 Circuit Breaker Panel: 1) AIR/GND and LTS 2) NOSE GEAR AIR/GND
S 865-256
(3) Remove the electrical power if it is not necessary (Ref 24-22-00/201).
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FLIGHT MANAGEMENT COMPUTER SYSTEM – ADJUSTMENT/TEST 1. General
A. This procedure has one task, to carry a Program Pin Verification of the Flight Management Computer System. The Program Pin Verification is part of the System Test – Analogue Discretes.
B. Any other test associated with the Flight Management Computer System in
accordance with 34-62-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
2. System Test - FMCS
A. General
(1) The system test fully examines the FMCS. The system test procedure includes the tests shown below: (a) Operational Test (par. 2) (b) Analog Discretes. (c) Performance Code/Performance Factors - Verification/Adjustment
Note: For all other tests, other than the Program Pin Verification (detailed
below), please refer to the associated AMM.
B. References
Reference Title
24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER) 34-28-01 P/B 201 INERTIAL REFERENCE SYSTEM - MAINTENANCE PRACTICES
C. Location Zones
Zone Area
101 Control Cabin - Left 102 Control Cabin - Right
D. Analog Discretes
(1) Do the prepare for test (34-62-01 – associated AMM): "Operational Test -
FMCS" if it is necessary.
(2) Make sure that the CDU display shows the FMCS BITE 1/1 page.
(3) If the CDU does not show the FMCS BITE 1/1 page, do these steps: (a) Push the INIT REF key on the CDU front panel to show the POS INIT or
PERF INIT page. (b) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page. (c) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page. (d) Push the LSK adjacent to <FMCS to show the FMCS BITE 1/1 page.
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(4) Do the Program Pin Verification: (a) Push the PREV PAGE key on CDU to show the FMCS ANALOG DISC 2/4 page.
(b) Make sure the outputs on the CDU display are the same as the outputs
shown below:
Table 514
ASSUMED TEMP ENABLE
CAA FLT RULES DISABLE
CAA FLT RULES ENABLE
KILOGRAM OPTION DISABLE
MAG/TRUE MAG
OMEGA OFF
ALL AIRCRAFT PRE SB 737-34-1593 SRCE/DEST IDENT LEFT
ALL AIRCRAFT POST SB 737-34-1593 SRCE/DEST IDENT RIGHT
ALL AIRCRAFT ASPIRATED TAT DISABLE
FRQ SCAN DME DISABLE
FRQ SCAN DME ENABLE
°C/°F DEFAULT °C
EFIS INSTALLED ON
ALL AIRCRAFT; AIRPLANES WITH SOFTWARE U7.0 AND ON
NOTE: OMEGA is removed and PERF CODE 1 is added.
ALL AIRCRAFT POST SB 737-34-1593
NOTE: The SOURCE/DEST IDENT line will show RIGHT when you do a test of
the right FMC.
ALL AIRCRAFT
(c) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 3/4 page.
(d) Make sure the outputs on the CDU display are the same as the outputs
shown below: Table 515
VMO/MMO 340/.82
MAINT TEST DISABLE
ALL AIRCRAFT POST SB 737-34-1593 FMC SOURCE SEL *[1] NORMAL
ALL AIRCRAFT
*[1] The FMC SOURCE SEL line will read BOTH-ON-L when the FMC SOURCE SELECT switch is in the BOTH ON L position and BOTH-ON-R in the BOTH ON R position
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NOTE: AIRPLANES WITH SOFTWARE UPDATE 7.X, 8.X or 10.X; MAINT TEST is removed.
NOTE: AIRPLANES WITH SOFTWARE UPDATE 10.X;
VMO/MMO is removed.
(e) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 4/4 page.
(f) Make sure the outputs on the CDU display are the same as the outputs
shown below:
Table 516
VOR INHIBIT DISABLE
FLIGHT NUMBER DISABLE
TOGA RW POS UPD ENABLE
TAKEOFF PROFILE DISABLE
FAA/CAA QRH SPD DISABLE
FAA/CAA QRH SPD ENABLE
TAKEOFF SPEEDS DISABLE
NAVAID SUPPRESS DISABLE
SEL CRS INHIBIT DISABLE
ACARS INSTALLED OFF
(5) Push the line select key (LSK) adjacent to <INDEX (6L) to show FMCS BITE 1/1 page.
(6) Refer to the associated AMM to continue testing, or put aircraft back to to
its usual condition.
CHAPTER
AIRBORNE AUXILIARY
POWER
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ELAPSED TIME INDICATOR - REMOVAL/INSTALLATION
1. General
A. This procedure contains the removal and installation tasks for the elapsed time indicator.
B. The elapsed time indicator is installed on the left side of the oil cooler.
2. Elapsed Time Indicator Removal (Figure 401)
A. Location Zones
Zone Area
101 Control Cabin - Left 205 Electronic Compartment 703 APU Compartment
B. Access Panels
Number Name/Location
1201 Electronic Equipment Access Door 3804 APU Cowl Door - Left
C. Procedure
(1) Open this access panel:
Number Name/Location
1201 Electronic Equipment Access Door
(2) Set the switch and the circuit breaker:
(a) Set the APU master switch on the P5 forward overhead panel to the OFF
position and attach a DO-NOT-OPERATE tag.
(b) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) E3-3 Electrical Shelf, APU Control Unit
(3) Open the APU cowl door:
(a) Open the latches for the APU cowl door.
(b) Open this access panel:
Number Name/Location
3804 APU Cowl Door - Left
(c) Connect the door support rods.
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(4) Remove the lower shroud:
(a) Hold the lower shroud and open the shroud latches.
(b) Remove the lower shroud.
(5) Remove the elapsed time indicator:
(a) Disconnect the electrical connector from the indicator.
(b) Loosen the clamp that attaches the indicator to the bracket on the oil cooler.
1) Remove the indicator and the shockmount.
(c) Remove the screws and washers that attach the indicator to the
shockmount.
------------------------- END OF TASK ---------------------------
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Elapsed Time Indicator Installation Figure 401
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3. Elapsed Time Indicator Installation (Figure 401)
A. Location Zones
Zone Area
101 Control Cabin - Left 205 Electronic Compartment 703 APU Compartment
B. Access Panels
Number Name/Location
1201 Electronic Equipment Access Door 3804 APU Cowl Door - Left
C. Procedure
(1) Install the elapsed time indicator:
(a) Put the indicator in the shockmount and install the screws and washers.
(b) Put the assembled indicator in the shockmount bracket.
1) Tighten the clamp that attaches the indicator.
(c) Connect the electrical connector to the indicator.
CAUTION: KEEP A MINIMUM CLEARANCE OF 0.18 INCHES (5 MM) BETWEEN THE
ENGINE, FIRE DETECTOR, CLAMPS, AND LOWER SHROUD. BE CAREFUL WHEN YOU MOVE THE LOWER SHROUD. DAMAGE TO THE SHROUD CAN OCCUR.
(2) Install the lower shroud:
(a) Hold the lower shroud against the upper shroud.
(b) Close the shroud latches.
(3) Close the APU cowl door:
(a) Disconnect the door support rods.
(b) Put the door support rods in the clips on the APU cowl door.
(c) Close this access panel:
Number Name/Location
3804 APU Cowl Door - Left
(d) Close the latches for the APU cowl door.
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(4) Set the circuit breaker and the switch:
(a) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) E3-3 Electrical Shelf, APU Control Unit
(b) Remove the DO-NOT-OPERATE tag from the APU master switch on the P5
forward overhead panel.
(5) Close this access panel: Number Name/Location
1201 Electronic Equipment Access Door
------------------------- END OF TASK ---------------------------