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. ®
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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:
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.
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
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
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®
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
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®
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
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®
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
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
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
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®
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
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
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.
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
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
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
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®
34-49-03 – GROUND PROXIMITY WARNING SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
34-62-01 – FLIGHT MANAGEMENT COMPUTER SYSTEM – PROGRAM PIN VERIFICATION
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.
H. AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Voice Recorder AUTO/ON Switch Test
(1) TEST WITHOUT ENGINES RUNNING
NOTE: Additional relays are added to tum the CVR "on" when either engine is running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.
(a) Close all applicable circuit breakers to the CVR system.
(b) At the P5 overhead panel, at the cockpit voice recorder (CVR) control panel,
connect a 600 ohm headset to the CVR monitor jack.
(c) Make sure the CVR AUTO/ON switch is in the AUTO position.
(d) Make sure ambient cockpit audio is not heard over the headset. The CVR is OFF.
(e) On the CVR P5 control panel; AIRPLANES WITH VOICE RECORDER CONTROL PANEL
WITH METER; Make sure that the voice recorder control panel meter needle does not move while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light does not come on while you push the TEST switch.
(f) Make sure the CVR AUTO/ON switch is in the ON position.
(g) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(h) On the P5 control panel and make sure that; AIRPLANES WITH VOICE RECORDER
CONTROL PANEL WITH METER; Make sure that the voice recorder control panel meter needle moves and stays in the green area while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light comes on while you push the TEST switch.
(i) At the P18-2 panel, open circuit breaker (C9500) VOICE RECORDER RELAY.
(j) Make sure the CVR Auto/On switch automatically switches to the AUTO position.
(k) Make sure you cannot hear flight deck conversation in the headset. The CVR
is OFF.
(l) Close circuit breaker (C9500) VOICE RECORDER RELAY.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
23-71-00AIRCRAFT WITH CVR SWITCH Page 507 MOD 0869 APR 01/13
NOTE: Additional relays are added to tum the CVR "on" when either engine is
running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.
(a) Make sure the CVR AUTO/ON switch is in the AUTO position.
(b) Start No. 1 Engine Per AMM 71-00-00/201, ensure the No. 1 Eng N2 Gauge is
>46.33%.
(c) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(d) Shut down No.1 Eng Per AMM 71-00-00/201.
(e) Wait six minutes.
NOTE: The CVR switch circuit relay R9500 will tum the CVR off after five minutes.
(f) Make sure you cannot hear flight deck conversation in the headset. The CVR
is OFF.
(g) Start No. 2 Engine Per AMM 71-00-00/201, ensure the No. 2 Eng N2 Gauge is >46.33%.
(h) Make sure you hear flight deck conversation in the headset. The CVR is ON.
(i) Shut down No.2 Eng Per AMM 71-00-00/201.
(j) Wait six minutes.
NOTE: The CVR switch circuit relay R9500 will turn the CVR off after five
minutes.
(k) Make sure you cannot hear flight deck conversation in the headset. The CVR is OFF.
I. Put the Airplane Back to the Usual Condition S 085-015 (1) Remove the headphone from the control panel.
S 865-036
(2) AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Set the voice recorder AUTO/ON switch to the AUTO position. S 865-016 (3) Remove electrical power if it is not necessary (AMM 24-22-00/201)
CHAPTER
EQUIPMENT/
FURNISHINGS
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
25-11-11AIRPLANES WITH SECOND OBSERVER’S SEAT Page 201 MOD 0968 APR 01/11
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)
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-24-01AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU AND HONEYWELL FDR Page 502 MOD 0876 APR 01/11
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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-24-01AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU AND HONEYWELL FDR Page 504 MOD 0876 APR 01/11
(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:
(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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(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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(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
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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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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(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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(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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(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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(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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(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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(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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(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) 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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(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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
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(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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31-24-01AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU AND HONEYWELL FDR Page 533 MOD 0876 APR 01/11
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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31-24-22AIRPLANES WITH HONEYWELL (ALLIED SIGNAL) DFDAU Page 602 MOD 0876 APR 01/11
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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31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 202 MOD 0952 APR 01/11
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.
(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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34-49-03AIRPLANES WITH ENHANCED GROUND PROMXITY WARNING Page 501 MOD 0862 APR 01/11
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:
(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 ---------------------------
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.
(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