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Document No. AMS-737-345-27256
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 27256 Document No: AMS-737-345-27256
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-737-345-27256
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 2 Wiring Diagram Manual 22-11-75 – Added Aircraft Maintenance Manual 22-11-01 – Added Issue 3 Aircraft Maintenance Manual 31-24-01 – Replaced Issue 4 Aircraft Maintenance Manual 23-71-00 - Changed Issue 5
Wiring Diagram Manual 25-00-18 – Added Illustrated Parts Catalogue 25-31-11-99Z – Added
Document No. AMS-737-345-27256
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.
®
RECORD OF REVISION
Issue DIN No. Date Issue DIN No. Date Initial DIN-2364 APR 01/11
2 DIN-2760 JAN 01/12 3 DIN-3364 NOV 01/12 4 DIN-3606 APR 01/13 5 DIN-3950 OCT 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-737-345-27256
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 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
BASIC ENGR
NUMBER
MFG SERIAL
NUMBER REGISTRY NUMBER
CUSTASSIGNED AIRPLANE
IDENT
B737-45D 404 PV284 PA696 P8005 27256
INTRO-00 Page 1 OCT 01/13
Document No. AMS-737-345-27256
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 31-24-24-99Z 1 APR 01/11 Highlights Chapter 33 Front Page Record of Revision and Approval 1 33-11-00-05Z 0 APR 01/11 Introduction 1 OCT 01/13 33-11-00-05Z 1 APR 01/11 Introduction 2 OCT 01/13 Chapter 34 Front Page List of Effective Pages 1 OCT 01/13 34-28-31-02Z 0 APR 01/11 List of Effective Pages 2 OCT 01/13 34-28-31-02Z 1 APR 01/11 Report/Feedback Sheet 34-62-21-04Z 0 APR 01/11 WDM Front Page 34-62-21-04Z 1 APR 01/11 WDM Contents 1 Chapter 35 Front Page WDM Contents 2 35-12-00-02Z 0 APR 01/11 Chapter 22 Front Page 35-12-00-02Z 1 APR 01/11 22-11-75 1 JAN 01/12 35-12-00-02Z 2 APR 01/11 Chapter 23 Front Page 35-12-00-20Z 0 APR 01/11 23-22-01 1 APR 01/11 35-12-00-20Z 1 APR 01/11 23-71-01 1 Sht 1 APR 01/11 AMM Front Page 23-71-01 1 Sht 2 APR 01/11 AMM Contents 1 Chapter 25 Front Page AMM Contents 2 25-00-18 115/116 OCT 01/13 Chapter 22 Front Page Chapter 31 Front Page 22-11-01 501 JAN 01/12 31-31-01 1 APR 01/11 22-11-01 502 JAN 01/12 Chapter 33 Front Page Chapter 23 Front Page 33-17-01 1 APR 01/11 23-71-00 501 APR 01/13 Chapter 34 Front Page 23-71-00 502 APR 01/13 34-22-11 1 APR 01/11 23-71-00 503 APR 01/13 34-22-21 1 APR 01/11 23-71-00 504 APR 01/13 34-49-04 1 APR 01/11 23-71-00 505 APR 01/13 34-53-12 1 APR 01/11 23-71-00 506 APR 01/13 34-53-22 1 APR 01/11 23-71-00 507 APR 01/13 34-61-11 1 APR 01/11 Chapter 25 Front Page IPC Front Page 25-11-11 201 APR 01/11 IPC Contents 1 25-11-11 202 APR 01/11 IPC Contents 2 25-11-11 203 APR 01/11 Chapter 23 Front Page 25-11-11 204 APR 01/11 23-71-13-01Z 0 APR 01/11 25-11-11 205 APR 01/11 23-71-13-01Z 1 APR 01/11 25-11-11 206 APR 01/11 Chapter 25 Front Page 25-11-11 207 APR 01/11 25-11-11-18Z 0 APR 01/11 25-11-11 208 APR 01/11 25-11-11-18Z 1 APR 01/11 25-11-11 209 APR 01/11 25-11-11-66Z 0 APR 01/11 25-11-11 210 APR 01/11 25-11-11-66Z 1 APR 01/11 25-11-11 211 APR 01/11 25-11-21-22Z 0 APR 01/11 25-11-11 212 APR 01/11 25-11-21-22Z 1 APR 01/11 Chapter 31 Front Page 25-31-11-99Z 0 OCT 01/13 31-24-01 1 APR 01/11 25-31-11-99Z 1 OCT 01/13 31-24-01 2 APR 01/11 Chapter 31 Front Page 31-24-01 3 APR 01/11 31-24-11-01Z 0 APR 01/11 31-24-01 4 APR 01/11 31-24-11-01Z 1 APR 01/11 31-24-01 5 APR 01/11 31-24-22-01Z 0 APR 01/11 31-24-01 6 APR 01/11 31-24-22-01Z 1 APR 01/11 31-24-01 7 APR 01/11 31-24-24-99Z 0 APR 01/11 31-24-01 8 APR 01/11
LEF-00 Page 1 OCT 01/13
Document No. AMS-737-345-27256
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
31-24-01 9 APR 01/11 34-49-03 502 APR 01/11 31-24-01 10 APR 01/11 34-62-01 501 APR 01/11 31-24-01 11 APR 01/11 34-62-01 502 APR 01/11 31-24-01 12 APR 01/11 34-62-01 503 APR 01/11 31-24-01 13 APR 01/11 31-24-01 14 APR 01/11 31-24-01 15 APR 01/11 31-24-01 16 APR 01/11 31-24-01 17 APR 01/11 31-24-01 18 APR 01/11 31-24-01 501 APR 01/11 31-24-01 502 APR 01/11 31-24-01 503 APR 01/11 31-24-01 504 APR 01/11 31-24-01 505 APR 01/11 31-24-01 506 APR 01/11 31-24-01 507 APR 01/11 31-24-01 508 APR 01/11 31-24-01 509 APR 01/11 31-24-01 510 APR 01/11 31-24-01 511 NOV 01/12 31-24-01 512 APR 01/11 31-24-01 513 APR 01/11 31-24-01 514 APR 01/11 31-24-01 515 APR 01/11 31-24-01 516 APR 01/11 31-24-01 517 APR 01/11 31-24-01 518 APR 01/11 31-24-01 519 APR 01/11 31-24-01 520 APR 01/11 31-24-01 521 APR 01/11 31-24-01 522 APR 01/11 31-24-01 523 APR 01/11 31-24-01 524 APR 01/11 31-24-01 525 APR 01/11 31-24-01 526 APR 01/11 31-24-01 527 APR 01/11 31-24-01 528 APR 01/11 31-24-01 529 APR 01/11 31-24-01 530 APR 01/11 31-24-01 531 APR 01/11 31-24-01 532 APR 01/11 31-24-01 533 APR 01/11 31-24-22 601 APR 01/11 31-24-22 602 APR 01/11 31-24-24 201 APR 01/11 31-24-24 202 APR 01/11 Chapter 34 Front Page 34-22-00 501 APR 01/11 34-22-00 502 APR 01/11 34-49-03 501 APR 01/11
LEF-00 Page 2 OCT 01/13
Document No. AMS-737-345-27256
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
22-11-75 – DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS
Chapter 23 COMMUNICATIONS
23-22-01 – SELCAL
23-71-01 – COCKPIT VOICE RECORDER
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-00-18 – SELL COMPONENT MAINTENANCE MANUAL P/N 1003C11A00000
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
34-49-04 – GROUND PROXIMITY WARNING
34-53-12 – ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-22 – ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-61-11 – FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS
Chapter 35 OXYGEN
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
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.
®
Chapter 49 AIRBORNE AUXILIARY POWER
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
PV284
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
22 STD OPT ILS DEVN WARN
25
BIT 1
26
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−R−3
A
12
34
53
FRN IRS XFR−A
DME BITE TESTAFDS 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−3
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
2
AUTO/MANUAL TUNE
ADATA BUS ANCDU−2
B
FWD LOC ANTENNA SELECT
LOCAL IRS XFR
D4317P
1
J
3
5
7
9
11
13
15
17
2
4
6
8
12
14
16
XA1
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
34−31−02
NOT USED
NOT USED
NOT USED
NOT USED
GDX22−DC
GDX22−DC
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
W011−013−20
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.
18 W011−800−20
739−20
37 SPD/ALT INTERVENTION
XB1
Z3
XC2
Z4
XD5
Z9
GD701−DC
GD701−DC
GD701−DC
T1015STA 314.5WL 182.5LBL 19.2
M923FLIGHT CONTROL COMPUTER "B"
W069−737−20
D1655A
2
18
19
22STD OPT ILS DEVN WARN
25
BIT 1
26
D1661A
D1661B
44
61
STD OPT ALT ALERT
CONFIG PINS
G/S SUPERFLAG
2
D1655B
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
FRN IRS XFR−A
AFDS 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−3
A
9
D1657B
8BDATA BUS FMC−1
A
26
D1659A
25BDATA BUS DAA−R−2
A
54DME HOLD
D1659B
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
2
AUTO/MANUAL TUNE
ADATA BUS ANCDU−2
B
FWD LOC ANTENNA SELECT
LOCAL IRS XFR
D4117P
32
J
34
36
38
40
42
44
46
48
33
34
37
39
43
45
47
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
NOT USED
NOT USED
NOT USED
NOT USED
GDX6−DC
GDX6−DC
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
W069−011−20
W069−009−20
31 41
49W069−800−20
739−20
37SPD/ALT INTERVENTION
34−55−41 53DME BITE TEST 34−55−51
W373−032−22
033−22
034−22
035−22
036−22
037−22
038−22
039−22
040−22
041−22
042−22
043−22
044−22
045−22
046−22
047−22
W373−049−22
048−22
W737−071−22
072−22
073−22
074−22
075−22
076−22
077−22
078−22
079−22
080−22
081−22
082−22
083−22
084−22
085−22
086−22
W737−088−22
087−22
062−20
W737−061−20
W737−063−20
XA1
XA5
XB1
Z3
XC2
Z4
XD5
Z9
GD701−DC
GD701−DC
GD701−DC
T1017STA 314.5WL 182.5LBL 19.2
062−20
W373−061−20
W373−063−20
CHAPTER
COMMUNICATIONS
B737-300/400/500 WIRING DIAGRAM MANUAL
PV284
SELCAL 23-22-01 INCORPORATES: 23-22-01 AERODEC MOD 0935
Page 1 Page 1
APR 01/11 APR 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
23-27-12
23-25-15
H12
4
4
4
HF-1 ANN LT
HF-1 ANN LT
HF-1 ANN LT
ANN LT CH 4
034-24
133-24
27
27
48
135-24
C7052-24
026-24
014-24
138-24
17
SM27
037-24 12 8305-24
017-24
23-27-11
1
4
56
7891011
12136
P D8963J
P D4287J
12
23-27-11
23-27-11
22-11011-85-42
8051-228050-22
8059-228056-22
8069-22
ELEX PWR-128V DC
FLT GND CALL
13C58 SELCAL
006-22
W089
J D4047P
STA 254DISC.
P18-2 ELECTRONI C LOAD CIRCUIT BREAKER PANEL
P18 LOAD CONTRO L CENTE R - LEFT
OVHD PANEL
CABIN ATTVHF-3 ACARS
LAMP TEST CONT
VHF-2 ANN LT
VHF-1 ANN LTVHF-3 ANN LT
671315
31
2
D141
STA 267DISC.
4
P D4212J
STA 254DISC.
23
P D4033J
W036562-24
STA 200 WL 209.30 RBL 9.06AURAL WRN UNIT MDL
P5
P8-53PANELOBS AUDIO SEL
68
D940
6
D4157J P
31-26-01W246-031-22
W329-011-24
CHIMESHI LO
M315
33-18-04
6
D131
6713152
13
D135
P8-6SEL PANELCAPT AUDIO
P8-7SEL PANELF/O AUDIO
P8
VHF-2 ANN LT
VHF-1 ANN LT
VHF-3 ANN LT
LAMP TEST CONT
FLT GND ANTCABIN ATT
VHF-3 ACARS
FLT GND CALLCABIN ATT
VHF-3 ACARSLAMP TEST CONTVHF-2 ANN LT
VHF-1 ANN LTVHF-3 ANN LT
2
3
1
PD4153J
19
SM26
618
SM24
17
1625
D4155J P
D4331J P
23-42-01
008-24
23-42-01
33-18-04
23-42-01
33-18-04
15137
SM25
P
P
D4285J
D4461J
ANN LT CH 1
ANN LT CH 3
D2555B
SM144 HI
LOCHASSIS GND
2
34
D2555C
28V DC2
D4151J P
W00722-250822-5508
GDX10-DC
D4703J P
17
16
25
A13
B13
A13B13
A13B13
D201B
D539B
D199B
SM30
SM31
SM136
SM138
23-27-1223-27-1223-27-1223-27-12
23-27-12
23-12-1123-12-31
M411 VHF COMM-3 XCVR
M149 VHF COMM-1 XCVR
HI
LO
HILO
OUTPUTAUDIOSELCAL
OUTPUTAUDIOSELCAL
M150 VHF COMM-2 XCVR
HILOOUTPUT
AUDIOSELCAL
R454WRN RELAYSELCAL AURAL
W175-
W327-
20
016-24W327-
W015
109-24
150-24054-24
055-24
W323-024-24
023-24
025-24W323-
W319- 031-24
032-24033-24W319-
072-24
071-24
073-24
136-24
076-24137-24
E2-1 ELECTRONI C SHELF
42
25
40
41
49
50
065-24
19383951
23-11-11
131-24
132-24
229-24R
230-24B
127-24
128-24
281-24R282-24B203-24R204-24B040-24
W189- 050-24
051-24
233-24R
234-24B
053-24
054-24
GD173-S201-24R202-24B231-24R232-24B
CIRCUI T INT OUT
W189-
RSV
227-24R
W191- 034-24
6153
A2
X1X2
A1
D2775
D2775
089-22
090-22088-22
SM29 097-22
23-12-21 SM137
228-24B
017-24042-24
297-24R298-24B
W191- 024-22
022-22
GD167-S
026-24032-24
034-24
201-24R202-24B219-24R220-24B
2
3
1J12
D2501A
K12
D2501AM1353
ELEX UNITREMOTE
107-24
4
56789
B4
B1A7
A3B3B8C8A2
A8
GND RESET CH 2ANN LT CH 2
CIRCUI T INT ININD LT INPUTHILOHI
8066-22
8065-22
8215-24R8216-24B8213-24R8214-24B
D4705J P
GDX10-DCA4
CH 4
8064-228054-22
LOGND RESET CH 5
CH 2
CH 5
E1-2 ELECTRONI C SHELF
M25 SELCAL DECODER
8057-24
8070-24
IHR42-7128
LO
GND RESET CH 1
GND RESET CH 3
HILOHILOGND RESET CH 4
D6
B7
A5
B5
A1
C1
B2C2A6B6D1
CH 3
CH 1
8218-24B
8072-24
8058-24
8207-24R8208-24B8203-24R8204-24B8073-24
1
2
3
4
5
6
7891011
GD173-S
GD167-S
GD173-S
ELECTRONI C PNLNOTES:
1
1 CAP AND STOW
B737-300/400/500 WIRING DIAGRAM MANUAL
PV284
COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0869
Page 1 Page 1 Sheet 1 Sheet 1
APR 01/11 APR 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
137
B737-300/400/500 WIRING DIAGRAM MANUAL
PV284
COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0869
Page 1 Page 1 Sheet 2 Sheet 2
APR 01/11 APR 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
137
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 WIRING DIAGRAM MANUAL
PV281
SELL COMPONENT MAINTENANCE MANUAL
P/N 1003C11A00000
25-00-18 INCORPORATES: 25-00-18 AERODEC MOD 1021 Page 115/116 Page 115/116
OCT 01/13 OCT 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 Pages 115/116 of Sell CMM 25-00-18 for P/No. 1003C11A00000
D
11H001A10 A
C
B
AAC POWER SUPPLY A115/200 VAC, 400 HZ
D101P.1
NOTE: FOR TERMINAL LUGS REFER TO FIGURE 102
FIGURE 108 − UNIT G1 −
1
3
AC NEUTRAL
CASE GROUND
B
C
AC NEUTRAL
2
1
3
D102P.2
BRT
PWR
DIM
C102
2A1
2B1
2C115 A
BOILER
A
B
C
F
G
D
E
D104P
1
2
4
5
3
D105P.4
L101
WORK LIGHTBRUCEBR9172−563
BOILERINVENTUM (DR40)
C103
211 A
WORK LIGHT
1
SHUTOFF
VALVE
3GD01
GD02
GD03
WATER TAPGD06
33
GD05
GD04
GD0911H027A6C 3
S101
2
1
3
5
4
6
BRT
DIM
OFF
S102
2
1
3
5
4
6
BRT
DIM
OFF
1
1
2
3
M101
BALLASTBRUCE03344−107
4
5
6
7
3
1
TB03TB04
GALLEYAREA LIGHTS
1
2
TB01TB02
1 1
3
GD12 SP01
SP02
3
1
WIRE SPEC:
BMS 13+31 AWG
BMS 13+58 AWG
P101
11H002A10 B
11H003A10 C
11H004A10 N
11H005A4 N
11H006A4 N
11H012A10 C
11H011A10 B
11H010A10 A
11H005A22
11H006A22
11H007A22
11H034A16A
11H035A16B
11H036A16C
11H046A16N
11H038A16N
11H039A10N 16
1611H040A10N
11H024A4N
A1
1
6
2
3
4
511H024A20N
11H023A20N
11H021A20C
11H044A20
11H041A20
11H042A20
11H043A20
11H045A20N
11H022A20C
11H016A20C
11H017A20N
11H010A22
11H019A22
11H013A10 C
11H031A16N
11H037A16N
11H023A20N
11H046A16N
11H038A16N
11H017A20N
11H046A16N
11H005A4N
11H0245A20N
11H027A4N
11H046A4N
11H026A4N
11H028A4N
C9001
A2A14 A
HOT JUG11H9004A10A 11H9001A20A 1
2
3
D9001J
HOT JUGJF003001DRIESSEN
1 11H9002A18NGD10 GD11
GD14
GD13
GD15
WTR FLTR
DRIP PAN
3 11H025A4N
11H014A4N
11H020A4N
11H015A4N
11H047A4N
11H048A4N
GD08 SINK
GD07 WORK PLATE
11H9003A18N
CHAPTER
INDICATING/ RECORDING
SYSTEM
B737-300/400/500 WIRING DIAGRAM MANUAL
PV284
DFDRS INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 0952
Page 1 Page 1
APR 01/11 APR 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
2.5C109 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
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
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
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
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
BACARS DATA IN
H3
H4
A
B
ACARS DATA OUT
23−27−12
ACQUISITION UNIT
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
31−31−0331−31−03
CHAPTER
LIGHTS
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV284
MAP, FLIGHT KIT AND READING LIGHTS 33-17-01 INCORPORATES: 33-17-01 AERODEC MOD 0968
Page 1 Page 1
APR 01/11 APR 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
6
6
GD596-AC 114-20W234-
GD316-AC 100-20W238-
32
1
32
1
D2492
A-E
5
SP722
807-24
D4036JP
20
PD4238J
7
004-24
004-22
SM4
SM3
GD100J-AC
W5007
002-24
E-A
3
D798
35
D796
4
CONTROL CABIN LIGHTING, FUEL SYSTEM AND MISCELLANEOUSP6-3
036-24
G-G
OBSERVERS READING LIGHT
WHT
XFR BUS-128V AC
W044
3 W238-24-53-312 1
804-24
W234-
W234-
D4060P
STA 259DISC.
W238-
C308
KIT LIGHTSFLIGHTMAP AND
073-24 SM91 533-24
844-24
2 13C309
STA 219, WL 224, RBL 36FIRST OFFICER S FLIGHT KIT LIGHT
XFR BUS-228V AC
24-53-41
BLK RW
L12READING LIGHTFIRST OBSERVERS
P6 LOAD CONTROL CENTER - RIGHT
DISC.
19
DISC.572ATS462ATS
W036W98-24 W234-014-24
W97-24
P5 OVERHEAD PANEL
SP188
SP186
GD610-AC=G =P
W
L9MAP LIGHTFIRST OFFICERS
-632W287PS 806PS004-205
D798
P23-1
GD190-ACG=P= R
W
L11
W238-
J
P21-1
SP606=P =G
W
L8MAP LIGHTCAPTAINS
G=P=GD1444-AC
D2458
G-A
L10STA 219, WL 224, LBL 36CAPTAIN S FLIGHT KIT LIGHT
RW
W234-C-P W234-C-G
W238-G-B
A-D-632W -632W
GD600-AC
070-24
W234-
STA 254, WL 265SECOND OBSERVERS READING LIGHT
G-P
4
F/O MAP LT DIMMER
W238-003-20
MAP LIGHT MODULE
D796
2
P10 FIRST OBSERVERS PANEL
W234-
011-22
CAPT MAP LT DIMMER
MAP LIGHT MODULE
010-20
(R505)
(R504)
E-D
W234-015-24
G=P=GD604-AC
RW
W234-B-P W234-B-G
L13
CHAPTER
NAVIGATION
B737-300/400/500 WIRING DIAGRAM MANUAL
PV284
EFIS POWER/PROGRAM PIN - LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 0864
Page 1 Page 1
APR 01/11 APR 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
PV284
EFIS POWER/PROGRAM PIN - RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 0864
Page 1 Page 1
APR 01/11 APR 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
PV284
GROUND PROXIMTY WARNING 34-49-04 INCORPORATES: 34-49-04 AERODEC MOD 0862
Page 1 Page 1
APR 01/11 APR 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
B15TERRAIN DISPLAY TYPE
D1153B
A3PPCOM (PROGRAMME PIN COMMON)
W021−501−24
W021−507−22
W9021−050−22
W021−518−24
GDX10−DC
SM1153
B10PPCNF2
A10PPCNF1
D1153A
W9021−047−22
W9021−048−22
W9021−076−22C10PPCNF3
W021−517−24
AIRCRAFT TYPE SELECT
D6PPCNF17 (PROGRAMME PIN PARITY)
B5PPCNF12 (WINDSHEAR CONTROL) W9021−069−22
C4PPCNF11 (AUDIO DECLUTTER / VOLUME)
W9021−054−22
W9021−053−22
W9021−049−22
W9021−052−22
SM505
34−49−03
D4PPCNF4
B4PPCNF5
A8PPCNF6
ALTITUDE CALLOUT MENU
D1153B
C2PPCNF9 (2 ILS / 2 LRRA / 3 LRRA)
B5PPCNF13 (TCF / TAD / SIM REPO)
D15GLIDESLOPE CANCEL OUTPUT
W9021−051−22 SP9009
C12DISCRETE OUTPUT 4 (WINDSHEAR CAUTION)
B12DISCRETE OUTPUT 6 (AUDIO ON)
D1153A
C2PPCNF14 (BANK ANGLE)
W9021−058−22
W9021−077−22 SM9025
W9021−061−22
W9021−060−22
W9021−059−22 SM9026
M652 ENHANCED GROUND PROXIMITY COMPUTER
E2−4 SHELF
34−49−03
W021−704−24
34−45−02
W021−8199−24 SM1151
W021−543−24
W021−506−24
34−49−03
A5PPCNF8 (AUDIO MENU) W9021−079−22 SM506
D14PPCNF7 (OPTIONAL GPS) W9021−055−22
B7DISCRETE OUTPUT 3 (PULL−UP WARNING) W021−511−2234−49−03
34−45−02
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV284
ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-12 INCORPORATES: 34-53-12 AERODEC MOD 0951
Page 1 Page 1
APR 01/11 APR 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
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−TNP 21150720PV284 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 1 0 0 00
1.NOTES:
FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D149B AND D2681
B737-300/400/500 AIRCRAFT WIRING MANUAL
PV284
ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-22 INCORPORATES: 34-53-22 AERODEC MOD 0951
Page 1 Page 1
APR 01/11 APR 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−TNP 21150720PV284 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 1 0 0 00
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
PV284
FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS
34-61-11 INCORPORATES: 34-61-11 AERODEC MOD 0853
Page 1 Page 1
APR 01/11 APR 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
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
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
23-71-13-01Z – 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
25-31-11-99Z – HOT CUP INSTL – GALLEY 1
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
31-24-11-01Z – FLIGHT RECORDER INSTL – AFT REMOVAL
31-24-22-01Z – EQUIP INSTL – ELECT. RACKS (DIGITAL FLIGHT DATA ACQUISITION UNIT ONLY)
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)
34-62-21-04Z – EQUIPMENT AND SOFTWARE INSTL – ELECT. RACKS (FMCS 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
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
COMMUNICATIONS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-71-13-01Z 23-71-13 MOD 0869 Fig 1Z APR 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 0869 Fig 1Z APR 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-0137 CVR SWITCH INSTALLATION 404404 RF
10 233A3211-1 • MODULE – COCKPIT VOICE RECORDER 1--20 TDH8127-3003 • RELAY 1--30 BACR13CF2AB • RELAY 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-11-11-18Z 25-11-11 MOD 0968 Fig 18Z APR 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 0968 Fig 18Z APR 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-0145 SECOND OBSERVER STATION INSTALLATION 404404 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 0968 Fig 66Z APR 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 0968 Fig 66Z APR 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-0145 SECOND OBSERVERS STATION INSTL 404404 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 0968 Fig 22Z APR 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 0968 Fig 22Z APR 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-0145 SECOND OBSERVER STATION INSTALLATION 404404 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
25-31-11-99Z 25-31-11 MOD-1021 Fig 99Z OCT 01/13 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-1021 Fig 99Z OCT 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-1021-001 INTRODUCTION OF DRIESSEN COMBO ASSY ON GALLEY G1A 404404 RF --1 AL253-1576 INSTALLATION OF DREISSEN COMBO ASSY (AERODEC DRAWING) 404404 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
--120 NAS1149D0363J • WASHER 8140 NAS43DD1-10FC • SPACER 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 NAS514P1032-18 • SCREW 4--240 AL253-1580-001 • ADAPTER PANEL 1--260 TC342A-X • CLIP 1
-- 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 APR 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 APR 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 404404 RF
10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-11-01Z 31-24-11 MOD 0876 Fig 1Z APR 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FLIGHT RECORDER INSTL – AFT REMOVAL FIGURE 1Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-11-01Z 31-24-11 MOD 0876 Fig 1Z APR 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-0035 FDAM/FDR REPLACEMENT 404404 RF
10 980-4700-042 • RECORDER – FLIGHT DATA 1 (ALT PART NOS.: 980-4700-001, 980-4700-003)
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-22-01Z 31-24-22 MOD 0876 Fig 1Z APR 01/11 Page 0
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EQUIPMENT INSTL – ELECT. RACKS (DIGITAL FLIGHT DATA ACQUISITION UNIT ONLY) FIGURE 1Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-22-01Z 31-24-22 MOD 0876 Fig 1Z APR 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-0035 FDAM/FDR REPLACEMENT 404404 RF
10 967-0212-002 • UNIT – DIGITAL FLIGHT DATA ACQUISITION 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
LIGHTS
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
33-11-00-05Z 33-11-00 MOD 0968 Fig 5Z APR 01/11 Page 0
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LIGHT INSTL – CONT CAB CREW Figure 5Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
33-11-00-05Z 33-11-00 MOD 0968 Fig 5Z APR 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-0145 SECOND OBSERVER’S STATION INSTL 404404 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 0868 Fig 2Z APR 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 0868 Fig 2Z APR 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-0033 IRS 2005 MAGNETIC VARIATION TABLE ACTIVATION 404404 RF
10 S242T101-117 • UNIT – INERTIAL REFERENCE 2 NOTE: EXISTING IRU PART NO. S242T101-107, WILL BECOME S242T101-117 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AD-34-0027 PER BOEING SERVICE LETTER 737-SL-34-177
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-62-21-04Z 34-62-21 MOD 0871 Fig 4Z APR 01/11 Page 0
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
EQUIPMENT AND SOFTWARE INSTL – ELECT RACKS (FMCS ONLY) FIGURE 4Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
34-62-21-04Z 34-62-21 MOD 0871 Fig 4Z APR 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-0036 INSTL OF 4 MCU FLIGHT MANAGEMENT COMPUTER 404404 RF
10 171497-05-01 • COMPUTER – FLIGHT MANAGEMENT (ALT NO: 176200-01-01) 1--20 66-14144-2 • SEAL TRAY 1--30 10-62225-1013 • OPS SOFTWARE (ALT NO: 549849-014) 1--40 443200-001 • MOD KIT – 8MCU TO 4MCU ADAPTER 1
-- ITEMS NOT ILLUSTRATED
CHAPTER
OXYGEN
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
35-12-00-02Z 35-12-00 MOD 0968 Fig 2Z APR 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 0968 Fig 2Z APR 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 0968 Fig 2Z APR 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-0145 SECOND OBSERVERS STATION INSTL 404404 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 0968 Fig 20Z APR 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 0968 Fig 20Z APR 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-0145 SECOND OBSERVERS STATION INSTL 404404 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-AGM1 • ANGLE ASSY 185 69-74512-AGM3 • 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--280 MC10-25-104 • OXYGEN MASK 1--290 MXP105 • MASK STOWAGE CUP 1--300 MXP210-00 • SMOKE GOGGLES 1--310 SFSW10F8DL26GY • SCREW 14
-- ITEMS NOT ILLUSTRATED
AIRCRAFT
MAINTENANCE
MANUAL
Contents
AMM-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
22-11-00– DIGITAL FLIGHT CONTROL SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 23 COMMUNICATIONS
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
31-24-01 – FLIGHT DATA RECORDER SYSTEM
PAGE BLOCK 1 – DESCRIPTION AND OPERATION
PAGE BLOCK 501 – ADJUSTMENT/TEST
31-24-22 – FLIGHT DATA ACQUISITION UNIT
PAGE BLOCK 601 – SERVICING
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
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.
®
34-49-03 – GROUND PROXIMITY WARNING SYSTEM
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
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
22-11-01404 Page 501 MOD 1093 JAN 01/12
Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
22-11-01404 Page 502 MOD 1093 JAN 01/12
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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 – CWS WARN NOT DISPLAYED
SOP – WINGS LVL NOT DISPLAYED
SOP – CWS OV/RD NOT DISPLAYED
SOP – PARITY OPEN 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
23-71-00AIRCRAFT WITH CVR SWITCH Page 501 MOD 0869 APR 01/13
Page produced by Aerospace Design and Engineering Consultants (AeroDECTM) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 502 MOD 0869 APR 01/13
Page produced by Aerospace Design and Engineering Consultants (AeroDECTM) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 503 MOD 0869 APR 01/13
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B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 504 MOD 0869 APR 01/13
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B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 505 MOD 0869 APR 01/13
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B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 506 MOD 0869 APR 01/13
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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.
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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
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CHAPTER
INDICATING/ RECORDING
SYSTEM
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E2-3
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(E2-3)
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FLIGHT DATA RECORDER SYSTEM – ADJUSTMENT/TEST 1. General
A. This procedure has one task, to carry of a System Test of the Flight Data Recorder System. The System Test refer to other task which do tests of the inputs to the Flight Data Recorder System.
B. Any other test associated with the Flight Data Recorder System in accordance with
31-24-01 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 – Flight Data Recorder System
A. General (1) The system test has procedures to do tests of the inputs to the flight data
recorder system. Tests can be accomplished out of sequence, and tests can also be accomplished independently.
(2) These tasks use the word SUBFRAME 0 to make a selection of a parameter which is on all four subframes. Some portable testers do not have a switch position for subframe 0. On these test sets, make a selection of subframes 1 thru 4 when the task uses subframe 0.
B. Location Zones
Zone Area 101 Control Cabin - Left 102 Control Cabin - Right
C. Prepare for Test
(1) References
Reference Title
24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)
(2) Tools/Equipment
Reference Description
981-6301-002 Data Signal Display Unit (DSDU) – Honeywell (A31007-32 Adapter Cable of -30 kit (without FDEP)) (A31007-35 Adapter Cable of -49 kit (with FDEP)) 2222786 Portable Tester - Teledyne (A31007-2 Adapter Cable of -1 kit) 2229738-X Portable Tester - Teledyne (A31007-60 Adapter Cable of -59 kit)
964-0446-001 Handheld Download Unit (HHDLU) - Honeywell
(704-2554-001 Adapter Cable)
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(3) Location Zones
Zone Area
101 Control Cabin - Left 102 Control Cabin - Right
(4) Preparation Procedure
(a) Supply electrical power (AMM 24-22-00) (b) Make sure the engines are off, the airplane is in ground mode, and the
following circuit breakers on the P18 panel are open: FLT REC AC (C109) FLT REC DC (C468)
(c) Do this step only if using tester 1 through 3 listed above. Remove the
shorting plug from the system test plug on the P18 panel and connect the tester using the appropriate adapter cable.
NOTE: Only testers 1 through 3 listed above can be connected to this
system test plug.
(d) When tester 1 (Honeywell DSDU) is used, set the switches to the following positions:
Switch Position
POWER ON WORD As given in test SUBFRAME As given in test INPUT ARINC INPUT DATA DATA PARAMETER SYNC B OCTAL DISPLAY 12 BIT
(e) When tester 2 or 3 (TELEDYNE) is used, set the switches to the following
positions:
Switch Position
DATA 12 bit for 12 bit signals 10 bit for 10 bit signals or discretes
READOUT ACFT UPDATE AUTO SUBFRAME As given in test WORD As given in test
(f) Do this step if using tester 4 listed above (Honeywell HHDLU).
1) Attach the HHDLU interface cable to the test connector at the front side of the Solid State Flight Data Recorder (SSFDR).
NOTE: To get access to the SSFDR, open the aft lowered ceiling panel
No. 2 (AMM 25-21-71/401). The HHDLU is used on the Honeywell SSFDR only.
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2) Once power is applied to the flight recorder, press and release the power button next to the input connector on the HHDLU. The HHDLU display will be inactive for approximately 30 seconds while the unit initializes. The Main Menu will then be displayed.
Note: The following steps can be performed with or without a memory
cartridge installed in the HHDLU.
3) On the HHDLU, press and release the DSDU key. The DSDU menu will be displayed. After initial synchronization, WORD 1 in base octal will be displayed on all three display lines. Press and release WRD 1. The word configuration menu will be displayed.
NOTE: In the following tests, the top line of the HHDLU display will
contain WRDI data, unless otherwise stated the test results refer to the top line of the display only. Data displayed in the lower lines can be ignored (WRDZ and WRD3).
4) The following steps will be necessary in subsequent procedures in order
to select a particular Subframe, Word and Numerical Base.
5) To cancel a modified character, press and release the EXIT key instead of the SEL key.
6) To carry out SUBFRAME SELECT, do the following procedure:
a) Press and release the SF key. The SUBFRAME SELECT menu will be displayed.
b) Press and release the left or right arrow keys until desired subframe number is displayed. The display scrolls down or up through subframes 1, 2, 3, 4 and ALL.
c) Press and release the SEL key. The HHDLU will accept the subframe selected and the word configuration menu will be displayed.
d) Press and release the WORD, BASE or EXIT key, as required. The WORD SELECT, BASE SELECT or DSDU menu will be displayed.
7) To carry out WORD SELECT, do the following procedure:
a) Press and release the WORD key. The WORD SELECT menu will be displayed.
b) Press and release the left or right arrow keys until the desired word is displayed. The HHDLU display scrolls down or up through the available words.
c) Press and release the SEL key. The HHDLU accept the word selected and the word configuration menu is displayed.
d) Press and release either the BASE or EXIT key, as required. The BASE SELECT or DSDU menu will be displayed.
8) To carry out BASE SELECTION, do the following procedure:
a) Press and release the BASE key. The BASE SELECT menu will be displayed.
b) Press and release either the BIN, OCT, DEC or HEX key to select binary, octal, decimal or hexadecimal base, as required. Asterisks (*) indicate current base selected. The word configuration menu will be displayed.
c) Press and release the EXIT key. The DSDU menu will be displayed.
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(g) Several of the parameters to be tested are recorded in superframe format. This is a format that is used to store parameter data that changes infrequently. A superframe counter, recorder in WORD 64, SUBFRAME 1, BITS 1-4 is used for timing purposes to store and subsequently recover the parameter data. When using the HHDLU to display superframe data, use the second line of the HHDLU display (WRD 2) to display the superframe counter. When the counter value (binary value plus 1) matches the expected superframe cycle the next update of parameter data is valid.
(h) Put the Test - Normal Switch on the Flight Recorder Test Module to the
Test Position.
D. Procedure
(1) Supply electrical power (PAGEBLOCK 24-22-00/201).
(2) Make sure the engines are off.
(3) Sync Word Test
(a) On the tester, set the SUBFRAME to 1 and the WORD to 1. Make sure the tester display shows 1107.
(b) Repeat for each SUBFRAME and verify the correct values as shown below:
Subframe 2 - 2670 Subframe 3 - 5107 Subframe 4 - 6670
(4) Relative Time (Frame Count) Test
(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 64. Verify displayed
values increases by 1 count at 4-second intervals.
(5) Clock Signal (GMT) Test
(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 17.
(b) Set the captain's clock to 13 hours and 42 minutes.
(c) Set the GMT knob on the clock to the run position.
(d) Immediately make sure the tester display is 3324 or 3325.
(e) Set the clock to its usual condition.
(6) DADC Bus Signal Test
(a) References Reference Description AMM 34-12-01/501 Air Data System
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(b) In this test it is necessary to put the DADC into the TEST mode. You can use one of three methods depending on the type of DADC installed on the airplane.
1) Airplanes with a test select switch on the DADC; Put the Test select
switch to the function position and push and hold the Test button.
2) Airplanes with a Test - History switch on the DADC; Put the Test - History switch to the Test position.
3) Airplanes with a Self-Test switch on the DADC; Put the Self- Test switch
to the Test position.
(c) Make sure the Air Data Computer System is serviceable (AMM 34-12-01/501)
(d) On the Tester, Set the SUBFRAME to 0 and the WORD to 33.
(e) Put the DADC No. 1 into Test Mode.
(f) Make sure the tester display is 4663 to 4775.
(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 8.
(h) Make sure the tester display is 6560 to 7027.
(7) EFIS Bus Signals Test
(a) References Reference Description
AMM 34-22-00/501 EFIS AMM 34-28-01/201 Inertial Reference System
(b) Make sure the EFIS system is serviceable (AMM 34-22-00/501)
(c) Make sure the IRS system is serviceable (AMM 34-28-01/201)
(d) Make sure the SYS DSPL switch on the IRS display is in the L position
(e) Make sure the EFIS transfer switch is in the NORM position.
(f) Make sure the IRS transfer switch is in the NORM position.
(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 28.
(h) On the IRS display unit, push and hold the DSPL SEL switch in the test
position for more than 10 seconds.
(i) Make sure the tester display is 0224 to 0303.
(j) Put the SYS DSPL switch on the IRS display in the R position.
(k) Put the EFIS transfer switch to the BOTH-ON 2 (or BOTH-ON-R) position
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(l) On the IRS display unit, push and hold the DSPL SEL switch in the test position for more than 10 seconds.
(m) Make sure the tester display is 0224 to 0303.
(n) Put the EFIS transfer switch to its usual position.
(8) Accelerometer Signals Test
(a) Special Tools and Equipment
Reference Description
# Inclinometer
(b) References Reference Description
AMM 31-24-81/401 Flight Recorder System Accelerometer
(c) Loosen the accelerometer but do not disconnect the electrical connector, AMM 31-24-81/401
(d) Use the inclinometer to put the accelerometer in to the positions shown in
the table below.
(e) Set the tester to the applicable words and subframe and make sure the display agrees with the values shown in the table below.
(f) Carefully install the accelerometer to its usual position (AMM 31-24-81/401)
WORD SUBFRAME ACCEL POSITION TESTER DISPLAY
VERTICAL ACCEL 02, 10, 18, 26, 34, 42, 50, 58 0
NORMAL 3520 – 3636 INVERTED 1746 – 2064
LATERAL ACCEL
11, 27, 43, 59 0 NORMAL 4024 – 4217
LEFT FACE UP 0150 – 0337 LONGITUDINAL ACCEL
9, 25, 41, 57 0 NORMAL 4024 – 4217
FORWARD FACE UP 7704 – 7777
(9) ATC Event (Radio Keying) signals Test
(a) References Reference Description
AMM 23-11-01/501 HF Communication System AMM 23-11-00/501 VHF Communication System
WARNING: MAKE SURE THAT PERSONNEL STAY A MINIMUM OF 6 FEET AWAY FROM
THE VERTICAL STABILIZER WHEN THE HF SYSTEM TRANSMITS. RF ENERGY FROM THE HF COMMUNICATION ANTENNA CAN CAUSE INJURY TO PERSONNEL.
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(b) Make sure the HF Communication system is serviceable (AMM 23-11-01/501)
(c) Make sure the VHF Communication system is serviceable (AMM 23- 11-00/501)
(d) Tune all transceivers to approved frequencies.
(e) On the captain's audio selector panel, push the VHF-1 switch.
(f) On the Tester, Set the SUBFRAME to 0 and the WORD to 07.
(g) Make sure bit 3 is a 1 (or light is on).
(h) Push the captain's PTT button and make sure bit 3 goes to a 0 (or light goes off)
(i) On the captain's audio selector panel, push the VHF-2 switch.
(j) On the Tester, Set the SUBFRAME to 0 and the WORD to 08.
(k) Make sure bit 3 is a 1 (or light is on).
(l) Push the captain's PTT button and make sure bit 3 goes to a 0 (or light
goes off).
(m) On the captain's audio selector panel, pus the HF-1 switch.
(n) On the Tester, Set the SUBFRAME to 0 and the WORD to 04.
(o) Make sure bit 2 is a 1 (or light is on).
(p) Push the captain's PTT button and make sure bit 2 goes to a 0 (or light goes off).
(q) Use the first officer's audio selector panel and first officer's PTT button
and repeat test.
(10) EIS Bus signals Test (a) References
Reference Description
AMM 31-42-00/501 EIS System
NOTE: If the input signal of the actual N1 is 10% RPM or more on one of the two engines the BITE test will not function.
(b) On the Tester, Set the SUBFRAME to 0 and the WORD to 04.
(c) Push and hold the primary EIS BITE button.
(d) Let the display become stable and make sure it shows N1 of 106%.
(e) Make sure the tester display is 6374 to 6603.
(f) Release the primary EIS BITE button.
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(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 36.
(h) Push and hold the BITE button on the primary EIS.
(i) Let the display become stable and make sure it shows N1 of 106%.
(j) Make sure the tester display is 6374 to 6603.
(k) Release the primary EIS BITE button.
(l) On the Tester, Set the SUBFRAME to 1, WORD to 49, and SUPERFRAME CYCLE to 3.
(m) Push and hold the BITE button on the secondary EIS.
(n) Let the display become stable and make sure the left oil pressure shows 13
psi.
(o) Make sure the tester display is 0013 to 0017.
(p) Release the secondary EIS BITE button.
(q) On the Tester, Set the SUBFRAME to 1, WORD to 49, and SUPERFRAME Cycle to 2.
(r) Push and hold the BITE button on the secondary EIS.
(s) Let the display become stable and make sure the right oil pressure shows
13 psi.
(t) Make sure the tester display is 0013 to 0017.
(u) Release the secondary EIS BITE button.
(11) FCC Bus Signals Test (a) References
Reference Description
AMM 22-11-01/501 Digital Flight Control System AMM 27-51-00/201 Trailing Edge Flaps
(b) Make sure the Autopilot system is serviceable (AMM 22-11-01/501).
(c) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 16.
CAUTION: WHEN YOU CHANGE DIRECTIONS WITH THE ELECTRICAL FLAP DRIVE KEEP
THE SWITCH IN THE SAME POSITION FOR 30 SECONDS. YOU CAN CAUSE DAMAGE TO THE ELECTRICAL FLAP DRIVE IF YOU DO NOT KEEP THE SWITCH IN THE SAME POSITION FOR 30 SECONDS
(d) Use the electrical flap drive to put the trailing edge flaps in the 2°
position (AMM 27-51-00/201)
NOTE: The position refers to the middle of the white band.
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(e) Make sure the tester display is 0000 to 0557.
(f) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 16.
(g) Use the electrical flap drive to put the trailing edge flaps in the 25° position.
(h) Make sure the tester display is 4060 to 4637.
(12) Control Column Position Signal Test
(a) References
Reference Description
AMM 29-00-00/201 Hydraulic Power
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATOR S, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Supply hydraulic power A and B (AMM 29-00-00/201).
(c) Make sure the control column is in the neutral position and install a rig
pin in the captain's control column.
(d) On the Tester, set the SUBFRAME to 0 and the WORD to 13 and 45 (in turn).
(e) Make sure the tester display is 7640 to 0137 (nominal 0000).
(f) Remove the rig pin from the captain's control column and move the column to the full forward position (against the stop).
NOTE: Do not use too much force on the control column or you may not
see correct values.
(g) Make sure the tester display is 6420 to 6716.
(h) Move the column to the full aft position (against the stop).
(i) Make sure the tester display is 1142 to 1440.
(j) Move the control column to the usual position.
(k) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201
(13) Control Wheel Position Signal Test
(a) Special Tools and Equipment
Reference Description
11MIT5-74110-51 Universal Protractor (or equivalent)
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(b) References
Reference Description
AMM 27-11-00/201 Aileron and Aileron Trim Control
(c) Install the protractor to the control wheel.
(d) Make sure the control wheel is in the neutral position and install a rig pin in the captain's control wheel.
(e) On the Tester, Set the SUBFRAME to 0 and the WORD to 21 and 53 (in turn).
(f) Make sure the tester display is 7745 to 0033 (nominal 0000).
(g) Remove the rig pin and turn the control wheel counter clockwise to 50°.
(h) Make sure the tester display is 6461 to 6563.
(i) Turn the control wheel clockwise to 50°.
(j) Make sure the tester display is 1215 to 1317.
(k) Move the control wheel to the usual position.
(l) Remove the protractor from the control wheel.
(14) Rudder Pedal Position signal Test
(a) References
Reference Description
AMM 27-21-00/501 Rudder and Rudder Trim Control System.
(b) Use the rudder pedal crank to move the captain's rudder pedal to the zero position and install a rig pin in the captain's rudder pedal.
(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 29 and 61 (in turn).
(d) Make sure the tester display is 7557 to 0221 (nominal 0000).
(e) Remove the rig pin and push the captain's right rudder pedal forward to the
stop.
(f) Make sure the tester display is 1356 to 2011.
(g) Push the captain's left rudder pedal forward to the stop.
(h) Make sure the tester display is 5765 to 6422.
(i) Move the rudder pedals to the usual position.
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(15) Elevator Position Signal Test (a) References
Reference Description
AMM 29-00-00/201 Hydraulic Power AMM 27-31-00/201 Elevator and Tab Control AMM 27-31-00/501 Elevator and Tab Control AMM 31-24-51/401 Elevator Position Transmitter
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Make sure the elevator system is serviceable (AMM 27-31-00/201).
(c) Set the ''B'' dimension on the stabiliser jackscrew to 41.57 ± 0.05 inches.
AMM 27-31-00/501.
(d) Open the STAB TRIM circuit breaker on the P6 panel.
(e) Make sure the mach trim actuator is in the null position.
(f) Supply hydraulic power A and B (AMM 29-00-00/201).
(g) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table:
(h) Set the elevators to the positions shown in the following table and make
sure the values agree with the tester display.
WORD SUBFRAME POSITION TESTER DISPLAY LEFT ELEVATOR
14 0 At Index Mark 7731 – 0051 10” Above Index 7217 – 7336 10” Below Index 0473 – 0635
RIGHT ELEVATOR 46 0
At Index Mark 7726 – 0046 10” Below Index 7144 – 7304 10” Above Index 0441 – 0560
(i) Remove hydraulic power A and B if it is no longer necessary
(AMM 29-00-00/201
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(16) Aileron Position signal Test
(a) References
Reference Description
AMM 27-11-00/201 Aileron and Aileron Trim Control AMM 31-24-31/401 Aileron Position Transmitter
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Supply power to the aileron system (AMM 27-11-00/501)
(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the
following table.
(d) Set the ailerons to the positions shown in the following table and make sure the values agree with the tester display.
WORD SUBFRAME POSITION TESTER DISPLAY
LEFT AILERON
22 0
At Index Mark (point A aligned with point B)
7736 – 0042
4” Above Index 0475 – 0612 4” Below Index 7166 – 7302
RIGHT AILERON
54 0
At Index Mark (point A aligned with point B) 7736 – 0042
4” Above Index 7166 – 7302 4” Below Index 0475 – 0612
(e) Remove power to the aileron system if it is no longer necessary
(AMM 27-11-00/201)
(17) Rudder Position Signal Test (a) References
Reference Description
AMM 27-21-00/201 Rudder and Rudder Trim Control AMM 31-24-41/401 Rudder Position Transmitter
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Make sure the rudder control system is serviceable (AMM 27-21-00/201).
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(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.
(d) Set the rudder to the positions shown in the following table and make sure
the values agree with the tester display.
WORD SUBFRAME POSITION TESTER DISPLAY RUDDER
30 & 62 0 At Index Mark 7756 – 0021
16” Left of Index 7274 – 7365 16” Right of Index 0421 – 0511
(e) Remove power to the rudder control system if it is no longer necessary
AMM 27-21-00/201.
(18) Stabilizer Position Signal Test (a) References
Reference Description
AMM 27-41-00/501 Horizontal Stabilizer Trim Control System AMM 29-00-00/201 Hydraulic Power
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Supply hydraulic power A and B (AMM 29-00-00/201).
(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the
following table.
(d) Set the Horizontal Stabilizer to the positions shown in the following table and make sure the values agree with the tester display.
WORD SUBFRAME POSITION TESTER DISPLAY
STABILIZER
44 0
41.57” Dimension B (3 units trim) 7705 – 0074
27.16” Dimension B (13 units trim) 0440 – 0660
(e) Remove hydraulic power A and B if it is no longer necessary
(AMM 29-00-00/201)
(19) Stabilizer Trim (A/P) Control Signal Test (a) References
Reference Description
AMM 27-41-00/501 Horizontal Stabilizer Trim Control System
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(b) On the Tester, Set the SUBFRAME to 0 and the WORD to 05.
(c) Put the dip engage switch A to the CMD position.
(d) Make sure bit 2 is a 0 (or light is off).
(e) Make sure all the STAB TRIM circuit breakers on the P18 panel are closed.
(f) Pull the control column aft until the stabilizer trim operates (AMM 27-41- 00/501).
(g) Make sure bit 2 changes to a 1 (or light comes on).
(h) Put the control column in the neutral position and make sure bit 2 goes to
0 (or light goes off).
(20) Stabiliser Trim (Manual) switch Signal Test
(a) On the Tester, Set the SUBFRAME to 0 and the WORD to 05.
(b) Make sure the trim switches on the control wheel are in the neutral position.
(c) Make sure bit 1 is a 0 (or light is off).
(d) Set the trim switch on the captain's control wheel to the TRIM NOSE UP
position.
(e) Make sure bit 1 changes to a 1 (or light comes on).
(f) Set the trim switch on the captain's control wheel to the neutral position.
(g) Make sure bit 1 changes to a 0 (or light is off).
(h) Set the trim switch on the captain's control wheel to the TRIM NOSE DN position.
(i) Make sure bit 1 changes to a 1 (or light comes on).
(j) Set the trim switch on the captain's control wheel to the neutral position.
(k) Make sure bit 1 changes to a 0 (or light is off).
(l) Use the first officer's control wheel switches and repeat the test
(21) Alternate Flaps Signals Test
(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 56.
(b) Make sure the alternate 'flaps master arming switch on the P5-3 panel is in
the off position.
(c) Make sure bit 6 is a 0 (or the light is off).
(d) Set the alternate flaps master arming switch to the ARMED position.
(e) Make sure bit 6 changes to a 1 (or the light comes on).
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(22) Leading Edge Flap Position Signal Test (a) References
Reference Description
AMM 27-81-00/201 Leading Edge Flap and Slat
(b) Make sure the flap system is serviceable (AMM 27-81-00/201).
CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.
(c) On the Tester, Set the SUBFRAME and WORD to the locations shown in the
following table.
(d) Move the flaps to get the conditions shown in the following table and make sure the values agree with the tester display.
FLAP NUMBER WORD SUBFRAME FLAP LIGHT
FLAP LIGHT CONDITION
BIT NUMBER
TESTER DISPLAY
1 23 1 & 3
IN TRANSIT OFF 2
1 (LIGHT ON) IN TRANSIT ON 0 (LIGHT OFF)
35 2 & 4 FULL EXTEND OFF
12 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
2 23 2 & 4
IN TRANSIT OFF 2
1 (LIGHT ON) IN TRANSIT ON 0 (LIGHT OFF)
35 2 & 4 FULL EXTEND OFF
11 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
3 23 1 & 3
IN TRANSIT OFF 1
1 (LIGHT ON) IN TRANSIT ON 0 (LIGHT OFF)
35 2 & 4 FULL EXTEND OFF
10 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
4 23 2 & 4
IN TRANSIT OFF 1
1 (LIGHT ON) IN TRANSIT ON 0 (LIGHT OFF)
35 2 & 4 FULL EXTEND OFF
9 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
(23) Leading Edge Slat Position Signal Test (a) References
Reference Description
AMM 27-81-00/201 Leading Edge Flap and Slat AMM 29-00-00/201 Hydraulic Power
(b) Make sure the slat system is serviceable (AMM 27-81-00/201).
(c) Supply hydraulic power A and B (AMM 29-00-00/201).
CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED
POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.
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(d) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.
(e) Move the slats to get the conditions shown in the following table and make
sure the values agree with the tester display
FLAP NUMBER
WORD SUBFRAME FLAP LIGHT FLAP LIGHT CONDITION
BIT NUMBER
TESTER DISPLAY
1
35 2 & 4 IN TRANSIT OFF
8 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 1 & 3 MID EXTEND OFF
3 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
31 1 & 3 FULL EXTEND OFF
2 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
2
35 2 & 4 IN TRANSIT OFF
7 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 2 & 4 MID EXTEND OFF
3 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
31 2 & 4 FULL EXTEND OFF
2 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
3
35 2 & 4 IN TRANSIT OFF
6 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 1 & 3 MID EXTEND OFF
2 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
31 1 & 3 FULL EXTEND OFF
1 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
4
35 2 & 4 IN TRANSIT OFF
5 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 2 & 4 MID EXTEND OFF
2 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
31 2 & 4 FULL EXTEND OFF
4 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
5
35 2 & 4 IN TRANSIT OFF
4 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 1 & 3 MID EXTEND OFF
1 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
56 2 & 4 FULL EXTEND OFF
11 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
6
35 2 & 4 IN TRANSIT OFF
3 1 (LIGHT ON)
IN TRANSIT ON 0 (LIGHT OFF)
24 2 & 4 MID EXTEND OFF
1 1 (LIGHT ON)
MID EXTEND ON 0 (LIGHT OFF)
56 2 & 4 FULL EXTEND OFF
12 1 (LIGHT ON)
FULL EXTEND ON 0 (LIGHT OFF)
(F) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201) .
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(24) Thrust Reverser Position Signal Test
(a) References
Reference Description
AMM 78-31-00/501 Thrust Reverser System AMM 29-00-00/201 Hydraulic Power
CAUTION: PUT A SAFETY OBSERVER NEAR THE THRUST REVERSER WHEN YOU DO
THIS TEST. THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS WHEN IT MOVES.
(b) Pull the safety pins from each thrust reverser isolation valve at the
forward air conditioning bay AMM 78-31-00/201.
(c) Make sure the thrust reverser circuit breakers are closed.
(d) With the two thrust reverser handles fully down, energize the A and B Hydraulic systems AMM 29-00-00/201.
(e) On the Tester, Set the SUBFRAME and WORD to the locations shown in the
following table.
(f) Move the thrust reversers to get the conditions shown in the following table and make sure the values agree with the tester display .
ENGINE NUMBER
WORD SUBFRAME T/R POSITION BIT NUMBER
TESTER DISPLAY
1 56 0
T/R L SLV STOWED 3
1 (LIGHT ON) T/R L SLV NOT STOWED 0 (LIGHT OFF)
56 0 T/R L SLV STOWED
4 1 (LIGHT ON)
T/R L SLV NOT STOWED 0 (LIGHT OFF)
2 39 0
T/R L SLV STOWED 4
1 (LIGHT ON) T/R L SLV NOT STOWED 0 (LIGHT OFF)
39 0 T/R L SLV STOWED
3 1 (LIGHT ON)
T/R L SLV NOT STOWED 0 (LIGHT OFF)
1 56 0
T/R L SLV STOWED 1
0 (LIGHT OFF) T/R L SLV NOT STOWED 1 (LIGHT ON)
56 0 T/R L SLV STOWED
2 0 (LIGHT OFF)
T/R L SLV NOT STOWED 1 (LIGHT ON)
2 39 0
T/R L SLV STOWED 2
0 (LIGHT OFF) T/R L SLV NOT STOWED 1 (LIGHT ON)
39 0 T/R L SLV STOWED
1 0 (LIGHT OFF)
T/R L SLV NOT STOWED 1 (LIGHT ON)
(g) Put the thrust reversers in the locked position.
(h) Return the safety pins to the thrust reverser isolation values.
(i) Remove hydraulic power A and B if it is no longer necessary (AMM 29-00-00/201).
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(25) Speed Brake Handle Signal Test (a) References
Reference Description
AMM 27-62-00/501 Speed Brake Control System
(b) On the Tester, Set the SUBFRAME and WORD to the locations shown in the following table.
(c) Set the speed brake handle to the positions shown in the following table
and make sure the values agree with the tester display.
WORD SUBFRAME POSITION TESTER DISPLAY SPEED BRAKE HANDLE
20 0 DOWN 7751 – 0027 ARMED 7674 – 7751 INFLIGHT 7036 – 7113
(d) Put the speed brake handle in its usual position.
(26) Autothrottle Bus Signals Test
(a) Make sure the engines are off.
(b) Put the No. 1 throttle lever to the full forward position.
(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 07.
(d) Make sure the tester display is 2000 to 2707.
(e) Put the No. 2 throttle lever to the full aft (idle) position.
(f) On the Tester, Set the SUBFRAME to 0 and the WORD to 39.
(g) Make sure the tester display is 7525 to 0253 (nominal 0000).
(h) Put the No. 1 and No. 2 throttle lever's to the usual position.
(27) FMC Bus Signals Test
(a) References
Reference Description
AMM 28-41-02/501 Fuel Quantity Indicating System AMM 34-62-00/501 Flight Management Computer System
(b) Make sure the following systems are serviceable:
1) Flight Management Computer System (AMM 34-62-00/501) 2) DAA No. 1 3) Fuel Quantity Indicator System (AMM 28-41-02/501)
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(c) Use the FMC CDU to get access to the PREF INIT 1/1 page: 1) Push the INIT REF key on the CDU. 2) Make sure the CDU shows the POS INIT page. 3) Push the line-select key 6L (<index). 4) Make sure the CDU shows the INIT REF INDEX 1/1 page. 5) Push the line-select key 3L (<PERF). 6) Make sure the CDU shows the PERF NIT 1/1 page.
(d) Enter the following information into the CDU.
1) Make sure a number shows below the FUEL annunciation (next to line-select key 2L).
2) Use the keys on the FMC CDU to enter a gross weight of 46.8K KG (102,960 lbs).
3) Make sure 46.8K shows on the CDU scratch pad. 4) Push the line-select key 1L. 5) Make sure the CDU shows the gross weight adjacent to the line- select
key 1L. 6) Push the line-select key 6R (TAKEOFF>). 7) Make sure the CDU shows the TAKEOFF REF 1/1 page.
(e) On the Tester, Set the SUBFRAME to 3, WORD to 49, and SUPERFRAME CYCLE
to 15.
(f) Make sure the tester display is 2371 to 2425.
NOTE: Value will only be visible when the is cycled on CDU.
(g) On the Tester, Set the SUBFRAME to 0, and the WORD to 63.
(h) Push the line -select key next to the FIXED OUTPUTS prompt on the FMCS BITE page of the CDU.
(i) Make sure the tester display is 0322 to 0455.
(28) Autothrottle Disengage Switch Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and WORD to 48.
(b) Make sure bit 1 is a 1 (or light is on).
(c) Push the A/T disengage switch on the thrust lever for engine No. 1
(d) Make sure bit exchanges to a 0 (or light goes off).
(e) Release the A/T disengage switch.
(29) Yaw Damper Engage Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and WORD to 59.
(b) Engage Yaw Damper switch on P5-3.
(c) Make sure bit 1 is a 1 (or light is on).
(d) Disengage Yaw Damper switch. 1
(e) Make sure bit 1 changes to a 0 (or light goes off).
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(30) Marker Beacon Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and the WORD to 12.
(b) Make sure bit 1 is a 0 (or light is off).
(c) Push the SELF-TEST button on the marker beacon receiver and make sure bit 1 on the tester changes to a 1 (or light comes on) in conjunction with the marker beacon lights on the P1 and P3 panels.
NOTE: The Self-Test button on the marker beacon receiver causes the
marker beacon lights to come on in order (i.e. Outer, Middle, and Airways). All three of these inputs relate to WORD 12, discrete bit 1.
On some marker beacon receivers the Self-Test button does not exist.If this is the case perform the system test IAW MM 34-35-00 and ensure that bit 1 on the tester changes to a 1 (or light comes on) in conjunction with the marker beacon lights.
(31) Master Caution Annunciator Signals Test
(a) Set the IRS Transfer switch to the NORM position.
(b) Close the IRS-1 AC breaker on the P18-2 panel.
(c) Make sure the IRS master caution light is off.
(d) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(e) Make sure bit 2 is a 1 (or light is on).
(f) Open the IRS AC circuit breaker.
(g) Make sure the IRS master caution light comes on.
(h) Make sure bit 2 is a 0 (or light is off).
(32) A/P Warning (Captain) Signals Test
(a) Open the following circuit breakers on the P6-2 panel:
1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC
(b) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(c) Get the FMC MAINT PAGE on the CDU.
(d) Push the line select key next to the DFCS BITE prompt and make sure the
captains A/P warning light in on.
(e) Make sure bit 4 is a 0 (or light is off).
(f) Push the INIT REF key on the FMC CDU and make sure the captain's A/P warning light is off.
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(g) Make sure bit 4 is a 1 (or light is on).
(h) Close the following circuit breakers on the P6-2 panel: 1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC
(33) A/P Warning (First Officer) Signals Test
(a) Open the following circuit breakers on the P6-2 panel:
1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC
(b) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(c) Get the FMC MAINT PAGE on the CDU.
(d) Push the line select key next to the DFCS BITE prompt and make sure the
first officer's A/P warning light in on.
(e) Make sure bit 4 is a 0 (or light is off).
(f) Push the INIT REF key on the FMC CDU and make sure the first officer's A/P warning light is off.
(g) Make sure bit 4 is a 1 (or light is on).
(h) Close the following circuit breakers on the P6-2 panel:
1) AFCS-B MACH TRIM DC 2) AFCS-B SENSOR EXC AC 3) AFCS-B ENGA INTLK 4) AFCS-B MACH TRIM AC 5) AFCS-B FCC DC
(34) Autothrottle Warning Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(b) Make sure the autothrottle is engaged and the autothrottle warning lights
are off.
(c) Make sure bit 8 is a 1 (or light is on).
(d) Push the A/T disengage switch on the thrust lever for engine No. 1 and make sure the autothrottle warning lights flash.
(e) Make sure bit 8 changes to a 0 (or light go off).
(f) Release the A/T disengage switch
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(35) Fire Warning (Wheel Well) Signals Test
(a) Open the following circuit breakers on the P6-2 panel: 1) FIRE PROTECTION DETECTION APU 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2
(b) Ensure the following circuit breaker on the P6-2 are closed:
1) OVHT WHL WELL WING BODY
(c) On the Tester, set the SUBFRAME to 0 and the WORD to 38.
(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the wheel well light comes on.
(e) Make sure bit 12 is a 1 (or light is on).
(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the wheel well light
goes off.
(g) Make sure bit 12 is a 0 (or light is off).
(h) Close the following circuit breakers on the P6-2 panel: 1) FIRE PROTECTION DETECTION APU 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2
(36) Fire Warning (APU) Siqnals Test
(a) Open the following circuit breakers on the P6-2 panel:
1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION ENG 1 3. FIRE PROTECTION DETECTION ENG 2
(b) Ensure the following circuit breakers on the P6-2 panel are closed:
1) FIRE PROTECTION DETECTION APU
(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the APU fire light comes on.
(e) Make sure bit 11 is a 1 (or light is on).
(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the APU fire light
goes off.
(g) Make sure bit 11 is a 0 (or light is off).
(h) Close the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION ENG 1 3) FIRE PROTECTION DETECTION ENG 2
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(37) Fire Warning (Engine No. 1) Signals Test
(a) Open the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 2
(b) Ensure the following circuit breakers on the P6-2 panel are closed:
1) FIRE PROTECTION DETECTION ENG 1
(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(d) Put the FAULT/INOP-OVHT/FIRE switch in the OVHT/FIRE position and make sure the ENG #1 light comes on.
(e) Make sure bit 6 is a 1 (or light is on).
(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the ENG #1 fire light
goes off.
(g) Make sure bit 6 is a 0 (or light is off).
(h) Close the following circuit breakers on the P6-2 panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 1
(38) Fire Warning (Engine No. 2) Signals Test
(a) Open the following circuit breakers on the P6-2 panel:
1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 1
(b) Ensure the following circuit breakers on the P6-2 panel are closed:
1) FIRE PROTECTION DETECTION ENG 2
(c) On the Tester, Set the SUBFRAME to 0 and the WORD to 38.
(d) Put the FAULT/INOP--OVHT/FIRE switch in the OVHT/FIRE position and make sure the ENG #2 light comes on.
(e) Make sure bit 7 is a 1 (or light is on).
(f) Release the FAULT/INOP-OVHT/FIRE switch and make sure the ENG #2 are light
goes off.
(g) Make sure bit 7 is a 0 (or light is off).
(h) Close the following circuit breakers on the put panel: 1) OVHT WHL WELL WING BODY 2) FIRE PROTECTION DETECTION APU 3) FIRE PROTECTION DETECTION ENG 2
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(39) Landing Gear Position signals Test
(a) Make sure the airplane is on the ground, all three gears are down and locked and the landing gear doors are open.
(b) Install locks on all landing gear.
(c) Make sure hydraulic power is off.
(d) Make sure the LEFT, RIGHT and NOSE GEAR green lights on the P2 panel are
on.
(e) Make sure the LEFT, RIGHT and NOSE GEAR red lights on the P2 panel are off.
(f) On the Tester, Set the SUBFRAME and WORD to the locations shown in the
following table.
(g) On one gear at a time install a copper shield between the downlock sensor and the actuator of the proximity switch shown in the following table and make sure the values agree with the tester display.
LANDING GEAR
WORD SUBFRAME GEAR LIGHT LIGHT CONDITION
BIT NUMBER
TESTER DISPLAY
LEFT 35 1
GREEN ON 1
0 (LIGHT OFF) GREEN OFF 1 (LIGHT ON)
38 0 RED ON
5 0 (LIGHT OFF)
RED OFF 1 (LIGHT ON)
RIGHT 35 1
GREEN ON 2
0 (LIGHT OFF) GREEN OFF 1 (LIGHT ON)
38 0 RED ON
10 0 (LIGHT OFF)
RED OFF 1 (LIGHT ON)
NOSE 35 3
GREEN ON 2
0 (LIGHT OFF) GREEN OFF 1 (LIGHT ON)
38 0 RED ON
9 0 (LIGHT OFF)
RED OFF 1 (LIGHT ON)
(40) Air/Ground Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and the WORD to 36.
(b) Make sure bit 1 is a 0 (or light off).
(c) Push the GND SENSING TEST switch on the landing gear accessory unit on the E11 shelf.
(d) Make sure bit 1 is a 1 (or light goes on).
(e) Release the GND SENSING TEST switch.
(f) On the Tester, Set the SUBFRAME to 0 and the WORD to 61.
(g) Make sure bit 2 is a 0 (or light off).
(h) Push the NOSE SENSING TEST switch on the landing gear accessory.
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(i) Make sure bit 2 is a 1 (or light goes on).
(41) DSWC Bus Signal Test
(a) Special Tools and Equipment
Reference Description
# Angle-of-Attack vane angle protractor
(b) Put the A and B PITOT STATIC HEAT switches on the pilot's overhead panel to the off position.
NOTE: This removes the heater power from the angle-of-airflow (alpha) vane.
WARNING: DO NOT TOUCH THE ALPHA VANES UNTIL THEY ARE COOL. HOT ALPHA
VANES CAN BURN YOU.
(c) Turn the left vane slowly to make sure it moves freely.
(d) Attach a portable airflow sensor calibrator to the left vane.
(e) Make sure the A SNSR EXC AC circuit breaker on the P18-1 circuit panel is closed.
(f) Use the protractor to put the vane in a 11° a trailing edge up position.
(g) On the Tester, Set the SUBFRAME to 0 and the WORD to 19 and 51 (in turn).
(h) Make sure the tester display is 104X to 112X.
NOTE: X represents any alphanumeric character.
(i) Remove the portable airflow sensor calibrator from the left vane
(42) DAA Bus Signals Test
(a) Set the captain's VHF NAV control panel on the P8 control stand to the MAN
position.
(b) Tune the control panel to 108.25 MHz.
(c) On the Tester, Set the SUBFRAME to 2 and the WORD to 52.
(d) Make sure the tester display is 5XXX.
NOTE: XXX represents any alphanumeric character.
(e) On the Tester, Set the SUBFRAME to 2 and the WORD to 49.
(f) Make sure the tester display is 0404.
(g) Set the First Officer's VHF NAV control panel on the P8 control stand to the MAN position.
(h) Tune the control panel to 109.50 MHz.
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(i) On the Tester, Set the SUBFRAME to 4 and the WORD to 52.
(j) Make sure the tester display is 0XXX.
NOTE: XXX represents any alphanumeric character.
(k) On the Tester, Set the SUBFRAME to 4 and the WORD to 49.
(l) Make sure the tester display is 0452.
(43) Hydraulic System Low Pressure Signal Test (a) References
Reference Description
AMM 29-00-00/201 Hydraulic Power
CAUTION: MAKE SURE THE THRUST REVERSER COWLS (C-DUCTS) ARE IN THE CLOSED POSITION BEFORE YOU DO THIS TEST. YOU CAN CAUSE DAMAGE TO THE FLAPS AND COWLS IF THE COWLS ARE OPEN WHEN THE FLAPS ARE EXTENDED.
(b) Close the following circuit breakers on the put panel:
1) MASTER DIM SECTION 1 (C00313) 2) MASTER DIM SECTION 5 (C00317) 3) MASTER DIM SECTION 6 (C00318)
(c) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 3.
(d) Make sure the system A-ENG 1 LOW PRESSURE annunciator on the P5 forward
overhead panel is on.
(e) Make sure bit 2 is a 0 (or light is off).
(f) Open the SECTION 6 MASTER DIM circuit breaker.
(g) Disconnect the D2684 connector from the S796 system A engine pump low pressure switch.
(h) Close the SECTION 6 MASTER DIM circuit breaker.
(i) Make sure bit 2 is a 1 (or light goes on).
(j) Make sure the system A-ENG 1 LOW PRESSURE annunciator is off.
(k) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 3.
(l) Make sure the system B-ENG 2 LOW PRESSURE annunciator on the P5 forward
overhead panel is on.
(m) Make sure bit 2 is a 0 (or light is off).
(n) Open the SECTION 5 MASTER DIM circuit breaker.
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(o) Disconnect the D2686 connector from the S797 system B engine pump low pressure switch.
(p) Close the SECTION 5 MASTER DIM circuit breaker.
(q) Make sure bit 2 is a 1 (or light goes on).
(r) Open the SECTION 1, 5, and 6 MASTER DIM circuit breakers.
(s) Make sure the system A-ENG 1 LOW PRESSURE annunciator is off.
(t) Connect the electrical connectors to system A and B engine pump low
censure switches.
(u) Close the SECTION 1, 5, and 6 MASTER DIM circuit breakers.
(v) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 3.
(w) Make sure the system B-ELEC 1 LOW PRESSURE annunciator is on.
(x) Make sure bit 1 is a 0 (or light is off).
WARNING: TO AVOID INJURY TO PERSONNEL, STAY CLEAR OF THE LEADING EDGE SLAT is WHICH CAN MOVE AUTOMATICALLY (UNLESS OTHERWISE INHIBITED) DURING MAINTENANCE WHEN EITHER HYDRAULIC SYSTEM IS PRESSURIZED AND THE TRAILING EDGE FLAPS ARE IN POSITION 1, 2, OR 5 AND THE NOSE OR MAIN LANDING GEAR AIR/GROUND RELAYS SENSE AN AIRBORNE CONDITION.
(y) Set the system B-ELEC 1 switch to the on position.
(z) Make sure the system B electrical pump is on.
(aa) Make sure the system ELEC-1 LOW PRESSURE annunciator is off.
(ab) Make sure bit 1 is a 1 (or light goes on).
(ac) Set the system B-ELEC 1 switch to the off position.
(ad) Make sure the system ELEC-1 LOW PRESSURE annunciator comes On.
(ae) Make sure bit 1 is a 0 (or light is off).
(af) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 3.
(ag) Set the system A-ELEC 2 switch to the on position.
(ah) Make sure the system A electrical pump is on.
(ai) Make sure the system ELEC-2 LOW PRESSURE annunciator is off.
(aj) Make sure bit 1 is a 1 (or light goes on).
(ak)Set the system A-ELEC 2 switch to the off position.
(al)Make sure the system ELEC-2 LOW PRESSURE annunciator comes On.
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(am) Make sure bit 1 is a 0 (or light is off).
(an) Open the following circuit breakers: 1) NORMAL STANDBY HYDRAULIC PUMP (C847) ON P6-11 2) ALTERNATE STANDBY HYDRAULIC PUMP (C848) ON P6-12
(ao) Set the FLT CONTROL A switch on the P5-3 panel to the STBY RUD position.
(ap) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 36.
(aq) Make sure bit 2 is a 0 (or light is off).
(ar) Close the NORMAL and ALTERNATE STANDBY HYDRAULIC PUMP circuit breakers.
(as) Make sure bit 2 is a 1 (or light is on).
(at) Set the FLT CONTROL A switch to the off position.
(au) Remove hydraulic power if it is no longer necessary (AMM 29-00-00/201).
(av) Open the NORMAL and ALTERNATE STANDBY HYDRAULIC PUMP circuit breakers.
(44) IRU Bus Signals Test
(a) References
Reference Description
AMM 34-28-01/50 Inertial Reference System
(b) Open the following circuit breakers on the P18-2 panel: 1) FMCS CMPTR (C1017).
(c) Wait at least 60 seconds before continuing to next step.
(d) Make sure the EFIS transfer switch is in the NORM position.
(e) Make sure the IRS transfer switch is in the NORM position.
(f) Make sure the two IRUS are in NAV mode (AMM 34-28-01/501).
(g) Make sure the SYS DSPL switch is in the L position.
(h) On the Tester, Set the SUBFRAME to 1 and the WORD to 52.
(i) On the IRS display unit, turn and hold the DSPL SEL knob to the TEST
position.
(j) Make sure the tester display is 2760 to 3237.
(k) Turn the SYS DSPL switch is in the R position.
(l) On the IRS display unit, turn and hold the DSPL SEL knob to the TEST position.
(m) Make sure the tester display is 2760 to 3237.
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(45) Fuel Cutoff Signals Test
(a) Open the following circuit breaker on the P6-2 panel: 1) ENG 1 R IGN 2) ENG 1 L IGN 3) ENG 2 R IGN 4) ENG 2 L IGN
(b) Make sure pneumatic power is NOT available to the two engines.
(c) Make sure the fire handles are in the NORMAL ignition.
(d) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and the WORD to 56.
(e) Make sure the engine No. 1 start lever is in the CUTOFF position.
(f) Make sure bit 5 is a 1 (or light is on).
(g) Put the engine No. 1 start lever switch in the START position.
(h) Make sure bit 5 is a 0 (or light goes off).
(i) Put the engine No. 1 start lever switch in the CUTOFF position.
(j) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and the WORD to 56.
(k) Make sure the engine No. 2 start lever is in the CUTOFF position.
(l) Make sure bit 5 is a 1 (or light is on).
(m) Put the engine No. 2 start lever switch in the START position.
(n) Make sure bit 5 is a 0 (or light goes off).
(o) Put the engine No. 2 start lever switch in the CUTOFF position.
(p) Close the following circuit breaker on the put panel:
1) ENG 1 R IGN 2) ENG 1 L IGN l 1 3) ENG 2 R IGN 4) ENG 2 L IGN
(46) Stick Shaker Signals Test
(a) On the Tester, Set the SUBFRAME to 0 and WORD to 16.
(b) Make sure bit 2 is a 0 (or light is off).
(c) Push the STALL WARNING TEST NO.1 button on the stall warning module.
(d) Make sure bit 2 is a 1 (or light goes on).
(e) Release the STALL WARNING TEST NO.1 button.
(f) Make sure bit 2 is a 0 (or light goes off).
(g) Push the STALL WARNING TEST NO. 2 button on the stall warning module.
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(h) Make sure bit 2 is a 1 (or light goes on).
(i) Release the STALL WARNING TEST NO. 2 button.
(47) EFIS Transfer Switch Signals Test
(a) Make sure the EFIS transfer switch on the P5 overhead panel is in the NORMAL position.
(b) On the Tester, Set the SUBFRAME to 1 and WORD to 36.
(c) Make sure bit 2 is a 0 (or light is off).
(d) Set the EFIS transfer switch to the BOTH-ON-2 position.
(e) Make sure bit 2 is a 1 (or light goes on).
(f) Set the EFIS transfer switch to NORMAL.
(48) IRS Transfer Switch Signals Test
(a) Make sure the IRS transfer switch on the P5 overhead panel is in the
NORMAL position.
(b) On the Tester, Set the SUBFRAME to 3 and WORD to 36.
(c) Make sure bit 2 is a 0 (or light is off).
(d) Set the IRS transfer switch to the BOTH-ON-2 (or BOTH-ON-R) position.
(e) Make sure bit 2 is a 1 (or light goes on).
(f) Set the IRS transfer switch to NORMAL.
(49) GPWC Bus Signal Test
(a) On the Tester, Set the SUBFRAME to 0 and WORD to 61.
(b) Push the ground proximity warn TEST switch.
(c) Make sure bit 1 changes to a 1 (or light comes on) when the PULL-UP light is on.
(d) Make sure bit 1 changes to a 0 (or light goes off) when the PULL-UP light
goes off.
(50) TCAS Bus Signal Test
(a) On the Tester, Set the SUBFRAME to 1 and the WORD to 56.
(b) Make sure the AIR/GND RELAY & LTS circuit breaker is closed.
(c) Make sure bit 12 is a 0 (or light is on.
(d) Momentarily put the Mode S/TCAS mode switch on the TCAS/ATC control panel, in the TEST position.
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(e) Make sure bit 12 changes to a 1 (or light goes on).
(51) Cabin Altitude >10k ft Bus Signal Test
(a) Remove the connector D776 from the cabin pressure switch S128 at STA 192, WL 207, BL 0.
(b) On the Tester, Set the SUBFRAME to 3 and the WORD to 35.
(c) Ground pin A of the electrical connector D776.
(d) Make sure bit 1 is a 0 (or light is off).
(e) Remove the ground on pin A of the electrical connector D776.
(f) Make sure bit 1 changes to a 1 (or light comes on).
(g) Put the connector D776 to its usual condition.
(52) Brake Pressure Signal Test
(a) References
Reference Description
AMM 32-41-00/501 Hydraulic Brake System AMM 29-00-00/201 Hydraulic Power
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Put chocks around the airplane wheels.
(c) Release the parking brake.
(d) Supply hydraulic power to system B (AMM 29-00-00/201).
(e) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and WORD to 24.
(f) Push the captain's left brake pedal fully against the stop.
(g) Find the PSI value in the table that best agrees with the hydraulic
pressure display and make sure the tester display agrees with the value.
(h) Release the captain's left brake pedal.
(i) On the Tester, Set the SUBFRAME to 2 and 4 (in turn) and WORD to 24.
(j) Push the captain's right brake pedal fully against the stop.
(k) Find the PSI value in the table that best agrees with the hydraulic pressure display and make sure the tester display agrees with the value.
(l) Release the captain's right brake pedal.
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(m) Remove hydraulic power to system B.
(n) Pump the brake pedal to fully deplete the accumulator.
(o) Supply hydraulic power to system A.
(p) Push the captain's right brake pedal fully against the stop.
(q) Find the PSI value in the table that best agrees with the hydraulic pressure display and make sure the tester display agrees with the value.
(r) Release the captain's right brake pedal.
(s) On the Tester, Set the SUBFRAME to 1 and 3 (in turn) and WORD to 24.
(t) Push the captain's left brake pedal fully against the stop.
(u) Find the PSI value in the table that best agrees with the hydraulic
pressure display and make sure the tester display agrees with the value.
(v) Release the captain's left brake pedal.
BRAKE PRESSURE TEST DISPLAY 2400 55XX – 60XX 2500 57XX – 62XX 2600 60XX – 64XX 2700 62XX – 66XX 2800 64XX – 70XX 2900 66XX – 72XX 3000 70XX – 73XX 3100 72XX – 75XX 3200 73XX – 77XX 3300 75XX – 77XX
NOTE: XXX represents any alphanumeric character.
(w) Remove hydraulic power if it is no longer necessary (AMM 29-00-00/201).
(53) Main/Attn Brake Select Signals Test (a) References
Reference Description
AMM 29-00-00/201 Hydraulic Power
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(b) Make sure the parking brake is not set.
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(c) Supply hydraulic power to system B (AMM 29-00-00/201).
(d) Make sure hydraulic power to system A and STANDBY is of.
(e) On the Tester, Set the SUBFRAME to 4 and WORD to 56.
(f) Make sure bit 6 is a 1 (or light is on).
(g) Remove hydraulic power to system B.
(h) Supply hydraulic power to system A.
(i) Pump the captain's brake pedal to remove the pressure from the main brake lines.
(j) Make sure bit 6 is a 0 (or light goes off).
(k) Remove hydraulic power if it is no longer necessary (AMM 29-00- 00/201 .
E. Put the Airplane in its Usual Condition
(1) References
Reference Description
AMM 24-22-00/201 Manual Control
(2) Put the Test - Normal Switch on the Flight Recorder Test Module to the Normal Position.
(3) Put the power switch on the tester to the OFF position (if applicable).
(4) Disconnect the tester from the flight data recording system.
(5) Remove electrical power if it is no longer necessary (AMM 24-22- 00/201 .
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FLIGHT DATA ACQUISITION UNIT - SERVICING
1. General
A. This procedure contains:
1) A DFDAU Database Load Procedure 2. Install Database Into the DFDAU
A. References
Reference Title
20-15-11 P/B 201 ON-AIRPLANE SOFTWARE INSTALLATION – MAINTENANCE PRACTICES 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
C. DFDAU Database Load Procedure
NOTE: The proper DFDAU database must be loaded prior to performing any ground
tests. The following steps define the procedure for loading of the database if the proper database was not verified above. The data loader indications are based on a Honeywell PDL. Differing indications may be observed with alternate data loaders. The load disks have been created to verify the proper configuration of the Aircraft Type discretes and to confirm the aircraft is in "ground" mode (determined by a logic zero at the DFDAU binary port B37, LTP3H), prior to loading. Confirm the proper configuration of these discretes if difficulty loading is encountered.
1) Open the following Circuit breakers on the P18 panel:
FLT REC AC (C109) FLT REC DC (C468)
2) Connect data loader to the DFDAU using FDAMS DFDAU PDL Interface cable
assembly.
3) On front panel of the FDAMS DFDAU PDL Interface cable assembly, set the toggle switch to DFDAU position and turn the rotary selector switch to the DFDAU MANDATORY EE ENABLE position.
4) Close the following Circuit breakers on the P18 panel:
FLT REC AC (C109) FLT REC DC (C468)
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5) Insert diskette, part number 998-2512-503 or approved alternate per Honeywell Component Part List, dwg. no. 756-0134-102, into data loader.
a) RDY and PROG light will illuminate during the load process.
b) RDY light will blink at approximately 3 second intervals.
c) Time to load the diskette is approximately 15 minutes, but vary with data
loader type.
d) Remove diskette when the COMP light on data loader illuminates.
6) Open the following Circuit breakers on the P18 panel:
FLT REC AC (C109) FLT REC DC (C468)
7) Turn the rotary selector switch on the FDAMS DFDAU PDL Interface cable to the
DFDAU NON-MANDATORY EE ENABLE position.
8) Close the following Circuit breakers on the P18 panel:
FLT REC AC (C109) FLT REC DC (C468)
9) Insert diskette, part number 998-2513-503 or approved alternate 503 or
approved alternate per Honeywell Component Part List, dwg. no. 756-0134-102, into data loader.
a) RDY and PROG light will illuminate during the load process.
b) RDY light will blink at approximately 3 second intervals.
c) Time to load the diskette is approximately 8 minutes, but varies with data
loader type.
d) Remove the diskette when COMP light on data loader illuminates.
10) Open the following Circuit breakers on the P18 panel:
FLT REC AC (C109) FLT REC DC (C468)
11) Disconnect the FDAMS DFDAU PDL Interface cable assembly and data loader from
the DFDAU.
12) Repeat Section D (above) to verify the proper database was loaded.
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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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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
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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
7A391B0 87BE000 E080000
Note: Make sure EHSI displays HDG up in the NAV, MAP and PLAN mode.
(Refer to pages 519, 522 and 523 of the applicable AMM)
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-0862.
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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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.
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