AIRCRAFT MANUAL
SUPPLEMENT To comply with EASA Regulation CS-25.1529 and CS-25 Appendix H and FAA Regulation CFR 14 25.1529 and to support the continued airworthiness of:
B737-4Q8 – MSN 25109 Document No: AMS-737-345-25109
Intro Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace 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 on behalf of 365 Aerospace Limited, UK. 365 Aerospace 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 Highlights of any future amendments will be described here.
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace 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 Date Issue Date Initial JAN 01/16
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 CFR 14 25.1529.
RRA-00 Page 1
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace 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 on behalf of 365 Aerospace Ltd and is in accordance with Air Transport Association of America
Specification No. 100, Specification for Manufacturers Technical Data. The data contained within is related to certain changes/modifications/alterations that are in addition to the associated airplane’s type design.
NOTE: THIS MANUAL IS PREPARED SPECIFICALLY TO COVER THE AIRPLANE LISTED IN THE "INTRODUCTION"
SECTION, FOR THE OWNER/OPERATOR NAMED ON THE TITLE PAGE.
THIS MANUAL IS NOT SUITABLE FOR USE, INCLUDING WITHOUT LIMITATION, GENERAL INSTRUCTIONS OR TRAINING, FOR ANY AIRPLANES NOT LISTED HEREIN.
B. The convention for the use of this publication is in the same convention (ATA 100) as the associated manufacturers AMM,
WDM, and IPC. Therefore, this publication is a SUPPLEMENT to the associated AMM, WDM, and IPC, and instructions on how to use this manual are equivalent to the instructions on how to use the manufacturers AMM, WDM and IPC.
C. This Manual Supplement has been raised to give historic design information pertaining to the following related aircraft
manuals: WDM – Wiring Diagram Manual WL – Wire List IPC – Illustrated Parts Catalogue AMM – Aircraft Maintenance Manual
D. For information on the approval of the technical content of this document, please refer to the Change/Mod/Alteration listing E. Aircraft Effectivity Information:
MODEL/ TYPE
CUST EFFECT CODE
CUST EFFECT CODE
(IPC ONLY)
VARIABLE ENGR
NUMBER
ENGINE SET
NUMBER LINE
NUMBER
MFG SERIAL
NUMBER REGISTRY NUMBER
CUST ASSIGNED AIRPLANE
IDENT
737-4Q8 665 PW245 PA668 25109
INTRO-00 Page 1 JAN 01/16
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace 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
2. Change/Modification/Alteration Listing
A. DOA Mod/STC information – Table 2.1
Mod/STC Ref: Title:
B. Owner/Operator/Supplier Mod/STC Information – Table 2.2
Mod/STC Ref: Title: Supplier:
MOD-0952 Instl of a Mini Quick Access Recorder AeroDEC MOD-0969 Deactivation of a SELCAL System AeroDEC MOD-1580 Instl of Driessen Combo Assy AeroDEC MOD-1581 Flight Management Computer (FMC) Pin Programming Changes AeroDEC MOD-1588 Installation of Airframe & Engine Lease Plates AeroDEC MOD-1590 Introduction of EFIS Pin Programming Changes AeroDEC MOD-1597 Introduction of EGPWS Altitude Callout Menu AeroDEC MOD-1598 Mode S ATC Address Code Pin Programming Change B737-400 (CL) AeroDEC
3. Approval
A. With reference to any Mod/STC indicated in Table 2.1 above, the technical content of the supplement information associated
with any listed Mod/STC above is approved under the authority of DOA No. EASA.21J.575. B. With reference to any Mod/STC indicated in Table 2.2 above, the technical content of the supplement information associated
with any listed Mod/STC above is approved under the authority of the named Owner/Operator/Supplier of the document. The Owner/Operator/Supplier of the document has given the compiler of this supplement rights to use their information in order to produce this manual supplement.
C. The Checking process will include a verification of technical consistency with the associated Mod/STC and Compliance
documentation which may relate to effectivity, description, effects on airworthiness and environmental protection especially when limitations are changed or affected.
Checked: Print Name:
Approved: Print Name:
INTRO-00 Page 2 JAN 01/16
WDM-CONTENTS Page 1
Produced by 365 Aerospace 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
23-22-01 – SELCAL
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-32-21 – HOTCUP WIRING – GALLEY G1
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
Chapter 34 NAVIGATION
34-22-11 – EFIS POWER – PROGRAM PINS - LEFT
34-22-21 – EFIS POWER – PROGRAM PINS - RIGHT
34-49-03 – 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 365 Aerospace 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
WDM-LEF Page 1
Produced by 365 Aerospace 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
WDM Front Page WDM Contents 1 WDM Contents 2 WDM-List of Effective Pages 1 Chapter 23 Front Page 23-22-01 1 JAN 01/16 Chapter 25 Front Page 25-32-21 1 JAN 01/16 Chapter 31 Front Page 31-31-01 1 JAN 01/16 Chapter 34 Front Page 34-22-11 1 JAN 01/16 34-22-21 1 JAN 01/16 34-49-03 1 JAN 01/16 34-53-12 1 JAN 01/16 34-53-22 1 JAN 01/16 34-61-11 1 JAN 01/16
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
SELCAL 23-22-01 INCORPORATES: 23-22-01 AERODEC MOD 0969
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
HOT CUP WIRING – GALLEY G1 25-32-21 INCORPORATES: 25-32-21 AERODEC MOD 1580
Page 1 TO BE READ IN CONJUNCTION WITH DRIESSEN GALLEY G1 COMPONENT Page 1 MAINTENANCE MANUAL 25-32-21
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
DFDRS INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 0952
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
EFIS POWER/PROGRAM PINS – LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 1590
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
EFIS POWER/PROGRAM PINS – RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 1590
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
GROUND PROXIMITY WARNING 34-49-03 INCORPORATES: 34-49-03 AERODEC MOD 1597
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-12 INCORPORATES: 34-53-12 AERODEC MOD 1598
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING
34-53-22 INCORPORATES: 34-53-22 AERODEC MOD 1598
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
B737-300/400/500 WIRING DIAGRAM MANUAL
PW245
FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS
34-61-11 INCORPORATES: 34-61-11 AERODEC MOD 1581
Page 1 Page 1
JAN 01/16 JAN 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
Produced by 365 Aerospace Limited, UK, who own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
WIRE
LIST
INDEX
B737-300/400/500 WIRING DIAGRAM MANUAL
WIRE LIST Section INDEX Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
SECTION PAGE NO. DATE SECTION PAGE NO. DATE
W9021 1 JAN 01/16
B737-300/400/500 WIRING DIAGRAM MANUAL
91-21-11
INCORPORATES: WIRE LIST Section W9021 AERODEC MOD‐1597 Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information. JAN 01/16
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9021
0001 24 34-49-03 SHT 1 M652 D1153B B4 E2-4 SM505 PW245 MOD-0054 0002 24 34-49-03 SHT 1 M652 D1153B A8 E2-4 SM957 PW245 MOD-0054
IPC-CONTENTS Page 1
Chapter 11 PLACARD & MARKINGS
11-20-10-99Z – PLACARD INSTL – NOTICE OF MORTGAGE-OWNERSHIP-LEASE
11-20-11-99Z – PLACARD INSTL – CAB. INTR 737-400
Chapter 21 AIR CONDITIONING
Chapter 22 AUTO FLIGHT
Chapter 23 COMMUNICATIONS
23-28-11-99Z – EQUIPMENT INSTL – SELCAL SYSTEM (PLACARDS ONLY)
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-31-11-99Z – HOTCUP INSTL – GALLEY G1
Chapter 26 FIRE PROTECTION
Chapter 27 FLIGHT CONTROLS
Chapter 28 FUEL
Chapter 29 HYDRAULIC POWER
Chapter 30 ICE AND RAIN PROTECTION
Chapter 31 INDICATING/RECORDING SYSTEMS
31-24-24-99Z – EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY)
Chapter 32 LANDING GEAR
Chapter 33 LIGHTS
Chapter 34 NAVIGATION
Chapter 35 OXYGEN
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
Chapter 49 AIRBORNE AUXILIARY POWER
IPC-CONTENTS Page 2
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
IPC-LEF Page 1
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
IPC Front Page IPC Contents 1 IPC Contents 2 IPC-List of Effective Pages 1 Chapter 11 Front Page 11-20-10-99Z 0 JAN 01/16 11-20-10-99Z 1 JAN 01/16 11-20-11-99Z 0 JAN 01/16 11-20-11-99Z 1 JAN 01/16 Chapter 23 Front Page 23-28-11-99Z 0 JAN 01/16 23-28-11-99Z 1 JAN 01/16 Chapter 25 Front Page 25-31-11-99Z 0 JAN 01/16 25-31-11-99Z 1 JAN 01/16 Chapter 31 Front Page 31-24-24-99Z 0 JAN 01/16 31-24-24-99Z 1 JAN 01/16
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
11-20-10-99Z 11-20-10 AERODEC MOD-1588 Fig 99Z JAN 01/16 Page 0
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
PLACARD INSTL – NOTICE OF MORTGAGE/OWNERSHIP/LEASE (REGISTRATION PLACARDS ONLY) FIGURE 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
11-20-10-99Z 11-20-10 AERODEC MOD-1588 Fig 99Z JAN 01/16 Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-1588-001 INSTL OF AIRFRAME AND ENGINE LEASE PLATES 665665 RF --1 AL112-2530 INSTL OF AIRFRAME AND ENGINE LEASE PLATES (AERODEC DRAWING) 665665 RF
30 AL112-2530-003 • ENGINE LEASE PLATE – NO.1 1 40 AL112-2530-004 • ENGINE LEASE PLATE – NO.2 1 60 BACB30GZ8-4 • BOLT 4 70 HL77-8 • COLLAR 4 80 BMS5-95 • SEALANT A/R 90 AS3485-10 • NUT 4
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
11-20-11-99Z 11-20-11 AERODEC MOD-1588 Fig 99Z JAN 01/16 Page 0
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
PLACARD INSTL – CAB. INTR 737-400 (REGISTRATION PLACARDS ONLY) FIGURE 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
11-20-11-99Z 11-20-11 AERODEC MOD-1588 Fig 99Z JAN 01/16 Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-1588-001 INSTL OF AIRFRAME AND ENGINE LEASE PLATES 665665 RF --1 AL112-2530 INSTL OF AIRFRAME AND ENGINE LEASE PLATES (AERODEC DRAWING) 665665 RF --1 AL112-2544 INSTL OF REGISTRATION PLACARD (AERODEC DRAWING) 665665 RF
10 AL112-2544-002 • REGISTRATION PLACARD 1 20 AL112-2530-002 • AIRCRAFT LEASE PLATE 1
--50 NAS1398D4-2 • RIVET 8 --80 BMS5-95 • SEALANT A/R
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-28-11-99Z 23-28-11 AERODEC MOD-0969 Fig 99Z JAN 01/16 Page 0
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
NOT ILLUSTRATED
EQUIPMENT INSTL – SELCAL SYSTEM (PLACARDS ONLY) FIGURE 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
23-28-11-99Z 23-28-11 AERODEC MOD-0969 Fig 99Z JAN 01/16 Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-0969-001 DEACTIVATION OF SELCAL SYSTEM 665665 RF --1 AL113-0950 INOP PLACARDS (AERODEC DRAWING) 665665 RF
--10 AL113-0950-003 • PLACARD - INOP 1
** TO BE INSTALLED AT SELCAL CB POSITION ON P18-2 **
--20 AL113-0950-003 • PLACARD - INOP 1 ** TO BE INSTALLED ON SELCAL CONTROL PANEL **
--20 AL113-0950-011 • PLACARD - INOP 1 ** TO BE INSTALLED ON SELCAL DECODER MOUNTING TRAY **
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-99Z 25-31-11 AERODEC MOD-1580 Fig 99Z JAN 01/16 Page 0
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
HOT CUP INSTL – GALLEY G1 FIGURE 99Z
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
25-31-11-99Z 25-31-11 AERODEC MOD-1580 Fig 99Z JAN 01/16 Page 1
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
FIG ITEM PART NUMBER NOMENCLATURE EFF
CODE UNITS PER
ASSY 1234567
99Z --1 MEO-1580-001 INTRODUCTION OF DRIESSEN COMBO ASSEMBLY 665665 RF --1 AL253-2521 INSTL OF DRIESSEN HOT JUG ASSY (AERODEC DRAWING) 665665 RF
30 JF003001 • COMBO ASSY 1 40 34-00318 • BRACKET 1 50 AL253-2528-001 • BRACKET 1 60 9-028-13 • SCREW 2 70 NAS514P1032-6 • SCREW 2 80 NAS1149D0332J • WASHER 4 90 NAS603-6 • SCREW 4
100 AL253-2527-202 • SPACER – ADAPTER PANEL 4 120 NAS514P632-12 • SCREW 4 130 NAS1149D0616J • WASHER 4 140 MS35649-262 • NUT 4 150 AC16707 • CONNECTOR 1 160 AL113-0248-001 • PLACARD – USER INSTRUCTIONS 1 170 AN935-6 • WASHER 4 180 NAS514P428-22 • SCREW 4 190 AL253-2527-101 • ADAPTER PANEL 1 200 NAS43DD1-10FC • SPACER 4 210 TC342A-X • CLIP 1
-- ITEMS NOT ILLUSTRATED
B737-300/400/500 ILLUSTRATED PARTS CATALOGUE
31-24-24-99Z 31-24-24 AERODEC MOD-0952 Fig 99Z JAN 01/16 Page 0
Page produced by 365 Aerospace 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 AERODEC MOD-0952 Fig 99Z JAN 01/16 Page 1
Page produced by 365 Aerospace 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 665665 RF
10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1 --20 AL313-1455-007 • KIT 1
-- ITEMS NOT ILLUSTRATED
AMM-CONTENTS Page 1
Chapter 11 PLACARD & MARKINGS
Chapter 21 AIR CONDITIONING
Chapter 22 AUTO FLIGHT
Chapter 23 COMMUNICATIONS
Chapter 24 ELECTRICAL POWER
Chapter 25 EQUIPMENT/FURNISHINGS
25-32-00 – DRIESSEN COMBO / COMBINATION WATER HOT CUP
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 26 FIRE PROTECTION
Chapter 27 FLIGHT CONTROLS
Chapter 28 FUEL
Chapter 29 HYDRAULIC POWER
Chapter 30 ICE AND RAIN PROTECTION
Chapter 31 INDICATING/RECORDING SYSTEMS
31-24-24– QUICK ACCESS RECORDER
PAGE BLOCK 201 – MAINTENANCE PRACTICES
Chapter 32 LANDING GEAR
Chapter 33 LIGHTS
Chapter 34 NAVIGATION
34-22-00 – EFIS DISPLAY MODES TEST
PAGE BLOCK 501 – ADJUSTMENT/TEST
34-42-03 – GROUND PROXIMITY WARNING SYSTEM
PAGE BLOCK 501 – ADJUSTMENT/TEST
34-62-01 – FLIGHT MANAGEMENT COMPUTER SYSTEM – PIN VERIFICATION TEST
PAGE BLOCK 501 – ADJUSTMENT/TEST
Chapter 35 OXYGEN
Chapter 36 PNEUMATIC
Chapter 38 WATER/WASTE
Chapter 49 AIRBORNE AUXILIARY POWER
AMM-CONTENTS Page 2
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
AMM-LEF Page 1
LIST OF EFFECTIVE PAGES
Description Page No. Date Description Page No. Date
AMM Front Page AMM Contents 1 AMM Contents 2 AMM-List of Effective Pages 1 Chapter 25 Front Page 25-32-00 501 JAN 01/16 Chapter 31 Front Page 31-24-24 201 JAN 01/16 31-24-24 202 JAN 01/16 Chapter 34 Front Page 34-22-00 501 JAN 01/16 34-22-00 502 JAN 01/16 34-42-03 501 JAN 01/16 34-42-03 502 JAN 01/16 34-62-01 501 JAN 01/16 34-62-01 502 JAN 01/16 34-62-01 503 JAN 01/16
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
25-32-00 AIRPLANES WITH DRIESSEN COMBO Page 501 AERODEC MOD-1580 JAN 01/16
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
DRIESSEN COMBO / COMBINATION WATER BOILER HOT CUP – ADJUSTMENT/TEST
1. General
A. This procedure has one task, to carry out an Operational Test of the Driessen Combo (Combination Water Boiler Hot Cup).
2. Operational Test
A. Procedure
1) Make sure that power is supplied to the aircraft (AMM Chapter 24).
2) On the unit, check to see if the orange "empty" LED, on the control panel, glows faintly. This indicates that the power is on and that the COMBO is ready to use.
3) Place an empty kettle in the combo holder and set both retainers in the
upright position.
4) Switch the COMBO on by pressing the "ON" switch. The "on" LED will light up green.
5) After a while the "hot" LED will start burning red, telling that the heating
plate of the combo holder is warmer than ±45°C (113°F).
6) Disengage one of the retainers and check to see if the COMBO stops heating. The green "on" LED stops burning. The red "hot" LED keeps burning as long as the hot plate is hot. Check both retainers one after the other.
7) Switch the COMBO on by pressing the "ON" switch. After several minutes the
orange "empty" LED starts blinking and the green "on" LED stops burning. This tells you that the kettle is empty and the heating process is stopped.
8) After the COMBO is sufficiently cooled down, the heating process can be
started again by pressing the "ON" switch. 9) Remove power from the aircraft if it is no longer required (AMM Chapter 24).
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-24-24 AIRPLANES WITH AVIONICA MINI QAR Page 201 AERODEC MOD-0952 JAN 01/16
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-24-24 AIRPLANES WITH AVIONICA MINI QAR Page 202 AERODEC MOD-0952 JAN 01/16
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
34-22-00 665 Page 501 AERODEC MOD-1590 JAN 01/16
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
ELECTRONIC FLIGHT INSTRUMENT SYSTEM – ADJUSTMENT/TEST
1. General
A. This procedure has one task, to carry an EFIS Display Modes Test.
B. Any other test associated with the Electronic Flight Instrument 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.
2. Operational Test (AMM TASK 34-22-00-715-001-001)
A. General
(1) Prepare testing conditions in accordance with 34-22-00 Page Block 501, AMM
TASK 34-22-00-715-001-001, of the associated manual.
Note: For aircraft with AeroDEC Modification MOD-1590, when carrying out the
EFIS Display Modes Test, please make sure that the following test is
applied. All other tests within 34-22-00 Page Block 501 are not
affected by this modification, and can therefore be carried out in
accordance with the applicable AMM.
À. EFIS Display Modes Test
(1) Make sure the EFI transfer switch is in the NORMAL position.
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.
(3) Push the INIT/REF key on the FMCS CDU.
(4) Push the line select key (LSK) 6L (<INDEX) on the FMCS CDU.
(5) Push the LSK 6R (MAINT>).
(a) Make sure the FMCS CDU display shows the MAINT BITE INDEX 1/1 page.
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(6) Push the LSK 5L (<EFIS).
(a) Make sure the FMCS CDU display shows the EFIS BITE TEST page.
(7) Push the LSK 3L (<SELF TEST).
(8) Make sure the hex code lines on the bottom right of the two EADIs show as
follows:
FA391B0
87BE008
E080000
(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
(10) For each mode on the left EFIS control panel, make sure the applicable test
patterns (Figure 502 and Figure 503) show on the left display units.
(11) For each mode on the right EFIS control panel, make sure the applicable test
patterns (Figure 502 and Figure 503) show on the right display units.
(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.
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
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34-42-03 AIRPLANES WITH ENHANCED GROUND PROXIMITY WARNING Page 501 AERODEC MOD-1597 JAN 01/16
Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST
1. General
A. This section carries out an operational test of the Enhanced Ground Proximity
Warning System (EGPWS).
B. Any other test associated with the Enhanced Ground Proximity Warning System (EGPWS)
in accordance with 34-42-03 Page Block 501 of the associated manual, are not
affected by the AeroDEC modification Listed below, and can therefore be accomplished
as instructed
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) Prepare the aircraft for Operational Test in accordance with the associated
AMM 34-42-03 Page Block 501
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"
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
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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 (PAGE BLOCK 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
B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL
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Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.
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 ENABLE
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.