AIRCRAFT MANUAL SUPPLEMENT · ipc-contents page. 1. chapter 11 placard & markings chapter 21 air...

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 25105 Document No: AMS-737-345-25105

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.


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


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 811 PW241 PA612 25105

INTRO-00 Page 1 JAN 01/16


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-1590 Introduction of EFIS Pin Programming Changes AeroDEC MOD-1597 Introduction of EGPWS Altitude Callout Menu 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

Mitchellh

Typewritten Text

M. Hills

danj

Typewritten Text

D. Jackson

WIRING

DIAGRAM

MANUAL

Contents

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

34-61-11 – FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS

Chapter 35 OXYGEN

Chapter 36 PNEUMATIC

Chapter 38 WATER/WASTE

Chapter 49 AIRBORNE AUXILIARY POWER

Chapter 52 DOORS

WDM-CONTENTS Page 2


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


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 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 34-61-11 1 JAN 01/16

CHAPTER

23 COMMUNICATIONS

B737-300/400/500 WIRING DIAGRAM MANUAL

PW241

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.

CHAPTER

25 EQUIPMENT/

FURNISHINGS


PW241

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


CHAPTER

31 INDICATING/ RECORDING

SYSTEM


PW241

DFDRS INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 0952

Page 1 Page 1


CHAPTER

34 NAVIGATION


PW241

EFIS POWER/PROGRAM PINS – LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 1590

Page 1 Page 1



PW241

EFIS POWER/PROGRAM PINS – RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 1590

Page 1 Page 1



PW241

GROUND PROXIMITY WARNING 34-49-03 INCORPORATES: 34-49-03 AERODEC MOD 1597

Page 1 Page 1



PW241

FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS

34-61-11 INCORPORATES: 34-61-11 AERODEC MOD 1581

Page 1 Page 1


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


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


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 PW241 MOD-0054 0002 24 34-49-03 SHT 1 M652 D1153B A8 E2-4 SM957 PW241 MOD-0054

ILLUSTRATED

PARTS

CATALOGUE

Contents

IPC-CONTENTS Page 1





23-28-11-99Z – EQUIPMENT INSTL – SELCAL SYSTEM (PLACARDS ONLY)



25-31-11-99Z – HOTCUP INSTL – GALLEY G1



Chapter 28 FUEL




31-24-24-99Z – EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY)


Chapter 33 LIGHTS


Chapter 35 OXYGEN




IPC-CONTENTS Page 2

Chapter 52 DOORS

Chapter 53 FUSELAGE



Chapter 56 WINDOWS

Chapter 57 WINGS



Chapter 74 IGNITION

Chapter 75 AIR


Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

IPC-LEF Page 1



IPC Front Page IPC Contents 1 IPC Contents 2 IPC-List of Effective Pages 1 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

CHAPTER

23 COMMUNICATIONS

B737-300/400/500 ILLUSTRATED PARTS CATALOGUE

23-28-11-99Z 23-28-11 AERODEC MOD-0969 Fig 99Z JAN 01/16 Page 0


NOT ILLUSTRATED

EQUIPMENT INSTL – SELCAL SYSTEM (PLACARDS ONLY) FIGURE 99Z




FIG ITEM PART NUMBER NOMENCLATURE EFF

CODE UNITS PER

ASSY 1234567

99Z --1 MEO-0969-001 DEACTIVATION OF SELCAL SYSTEM 811811 RF --1 AL113-0950 INOP PLACARDS (AERODEC DRAWING) 811811 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

CHAPTER

25 EQUIPMENT/

FURNISHINGS




HOT CUP INSTL – GALLEY G1 FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 MEO-1580-001 INTRODUCTION OF DRIESSEN COMBO ASSEMBLY 811811 RF --1 AL253-2521 INSTL OF DRIESSEN HOT JUG ASSY (AERODEC DRAWING) 811811 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


CHAPTER


SYSTEM




EQUIP INSTL – P18 (MINI QUICK ACCESS RECORDER ONLY) FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 MEO-0952-001 INSTALLATION OF A MINI QUICK ACCESS RECORDER 811811 RF

10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1 --20 AL313-1455-007 • KIT 1


AIRCRAFT

MAINTENANCE

MANUAL

Contents

AMM-CONTENTS Page 1







25-32-00 – DRIESSEN COMBO / COMBINATION WATER BOILER HOT CUP

PAGE BLOCK 501 – ADJUSTMENT/TEST



Chapter 28 FUEL




31-24-24– QUICK ACCESS RECORDER

PAGE BLOCK 201 – MAINTENANCE PRACTICES


Chapter 33 LIGHTS


34-22-00 – EFIS DISPLAY MODES TEST


34-42-03 – GROUND PROXIMITY WARNING SYSTEM


34-62-01 – FLIGHT MANAGEMENT COMPUTER SYSTEM – PIN VERIFICATION TEST


Chapter 35 OXYGEN




AMM-CONTENTS Page 2

Chapter 52 DOORS

Chapter 53 FUSELAGE



Chapter 56 WINDOWS

Chapter 57 WINGS



Chapter 74 IGNITION

Chapter 75 AIR


Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

AMM-LEF Page 1



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

CHAPTER

25 EQUIPMENT/

FURNISHINGS

B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL

EFFECTIVITY

25-32-00 AIRPLANES WITH DRIESSEN COMBO Page 501 AERODEC MOD-1580 JAN 01/16


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).

CHAPTER


SYSTEM


EFFECTIVITY

31-24-24 AIRPLANES WITH AVIONICA MINI QAR Page 201 AERODEC MOD-0952 JAN 01/16


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.


EFFECTIVITY

31-24-24 AIRPLANES WITH AVIONICA MINI QAR Page 202 AERODEC MOD-0952 JAN 01/16


12) Select “OK”. Make sure the message appears “miniQAR Successfully Erased”

13) Select “OK”. Make sure the message appears “Return to Service Complete. You may now disconnect the miniQAR”

14) Disconnect the USB connector of the PTI cable P/N 605-177 from the USB Port of

the PC or RSU tablet first.

15) Disconnect the DB9 connector of the PTI cable PN 605-0177 from the UUT DB9

connector.

16) End of test. The miniQAR can now be returned to service.

CHAPTER

34 NAVIGATION


EFFECTIVITY

34-22-00 811 Page 501 AERODEC MOD-1590 JAN 01/16


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.


EFFECTIVITY



(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


shown on the EHSI.

(d) EXP VOR/ILS

NOTE: To show the VOR mode, a VOR frequency (108.00) must be set on the


shown on the EHSI.

To show the ILS mode, an ILS frequency (108.10) must be set on the


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.


EFFECTIVITY

34-42-03 AIRPLANES WITH ENHANCED GROUND PROXIMITY WARNING Page 501 AERODEC MOD-1597 JAN 01/16


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"


EFFECTIVITY

34-42-03 AIRPLANES WITH ENHANCED GROUND PROXIMITY WARNING 2 AERODEC MOD-1597 JAN 01/16





“CURRENT FAULTS” “NO FAULTS” “PRESS TO CONTINUE”




“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 ---------------------------


EFFECTIVITY



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.


EFFECTIVITY



(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.


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


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


EFFECTIVITY



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.

AIRCRAFT MANUAL SUPPLEMENT · ipc-contents page. 1. chapter 11 placard & markings chapter 21 air...

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