AIRCRAFT MANUAL SUPPLEMENT · MOD-1040 SELCAL Code Change AERODEC MOD-1041 Mode S Code Change AERODEC MOD-1042 Introduction of Mini QAR AERODEC MOD-1043 Installation of a Hot Jug

AIRCRAFT MANUAL SUPPLEMENT To support Instructions for Continued Airworthiness in accordance with Regulations EASA CS-25.1529/FAR 14 CFR-25.1529, Appendix H.

B757 – MSN 25622 Document No: AMS-757-25622

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 Issue 2 Wiring Diagram Manual 34-22-16, 34-22-26 Changed 34-22-36 Added

Issue 3 Aircraft Maintenance Manual 31-31-00-PB1, 31-31-01-PB201 31-31-01-PB501 Added Note: Issue 1 thru 3 supplied by AERODEC

Issue 4 onwards supplied by 365 Aerospace Ltd. Issue 4 Document re-written as a 365 Aerospace document Supplemental information added throughout to include 365 Aerospace Mod-0006


RECORD OF REVISION

Issue Date Issue Date Initial (1) FEB 01/12

2 MAR 01/12 3 APR 01/12

Issue 1 thru 3 supplied by AERODEC

Issue 4 onwards supplied by 365 Aerospace Ltd. 4 APR 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 14 CFR 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

EL – Equipment List

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

757-28A 239 NB239 NW815 N0230 25622

INTRO-00 Page 1 APR 01/16


INTRODUCTION

2. Change/Modification/Alteration Listing

A. DOA Mod/STC information – Table 2.1

Mod/STC Ref: Title:

MOD-0006 Installation of a Controller Pilot Data Link Communications (CPDLC) System MOD-0123 Change for the Introduction of Bose A20 Headsets

B. Owner/Operator/Supplier Mod/STC Information – Table 2.2

Mod/STC Ref: Title: Supplier:

MOD-1038 EFIS Strapping Change AERODEC MOD-1039 EGPWS Callout Change AERODEC MOD-1040 SELCAL Code Change AERODEC MOD-1041 Mode S Code Change AERODEC MOD-1042 Introduction of Mini QAR AERODEC MOD-1043 Installation of a Hot Jug in the Galley AERODEC MOD-1044 Installation of SSFDR 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 APR 01/16

Mitchellh

Typewritten Text

M. Hills

danj

Typewritten Text

D. Jackson

WIRING

DIAGRAM

MANUAL

Contents

WDM-CONTENTS Page 1

Chapter 11 PLACARD & MARKINGS

Chapter 21 AIR CONDITIONING

Chapter 22 AUTO FLIGHT

Chapter 23 COMMUNICATIONS

23-12-31 – VHF COMMUNICATION - CENTRE

23-21-12 – SELCAL CODING

23-22-11 – AIRCRAFT COMMUNICATIONS ADDRESSING & REPORTING (ACARS) DLINK & POWER

23-71-11 – VOICE RECORDER

Chapter 24 ELECTRICAL POWER

Chapter 25 EQUIPMENT/FURNISHINGS

25-32-34 – GALLEY G1A WIRING

Chapter 26 FIRE PROTECTION

Chapter 27 FLIGHT CONTROLS

Chapter 28 FUEL

28-41-11 – FUEL QUANTITY INDICATION

Chapter 29 HYDRAULIC POWER

Chapter 30 ICE AND RAIN PROTECTION

Chapter 31 INDICATING/RECORDING SYSTEMS

31-31-01 – FDRS – INTERCONNECT GROUP 1

31-31-41 – FLIGHT DATA RECORDER SYSTEM – DIGITAL

31-33-01 – PRINTER INTERFACE

31-51-33 – AURAL WARNING – BELL CHIME

Chapter 32 LANDING GEAR

32-44-11 – PARKING BRAKE SYSTEM

Chapter 33 LIGHTS

Chapter 34 NAVIGATION

34-22-16 – EFIS POWER/LIGHTING/PROGRAMM PINS - LEFT

34-22-26 – EFIS POWER/LIGHTING/PROGRAMM PINS - RIGHT

34-22-36 – EFIS POWER/LIGHTING/PROGRAMM PINS - CENTER

34-46-11 – GROUND PROXIMITY WARNING SYSTEM PROGRAM PINS

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

34-61-15 – LEFT FMC/EFIS/DATA LOADER GENERAL – OUTPUTS

WDM-CONTENTS Page 2

Chapter 35 OXYGEN

Chapter 36 PNEUMATIC

Chapter 38 WATER/WASTE

Chapter 49 AIRBORNE AUXILIARY POWER

Chapter 52 DOORS

52-71-11 – DOOR WARNING INDICATION – LEFT AND ACCESS

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 23 Front Page 23-12-31 1 APR 01/16 23-21-12 1 APR 01/16 23-22-11 1 SHT 1 APR 01/16 23-22-11 1 SHT 2 APR 01/16 23-22-11 1 SHT 3 APR 01/16 23-22-11 1 SHT 4 APR 01/16 23-71-11 1 APR 01/16 Chapter 25 Front Page 25-32-34 1 APR 01/16 Chapter 28 Front Page 28-41-11 1 APR 01/16 Chapter 31 Front Page 31-31-01 1 APR 01/16 31-31-41 1 APR 01/16 31-33-01 1 APR 01/16 31-51-33 1 APR 01/16 Chapter 32 Front Page 32-44-11 1 APR 01/16 Chapter 34 Front Page 34-22-16 1 APR 01/16 34-22-26 1 APR 01/16 34-22-36 1 APR 01/16 34-46-11 1 SHT 1 APR 01/16 34-46-11 1 SHT 2 APR 01/16 34-53-12 1 APR 01/16 34-53-22 1 APR 01/16 34-61-15 1 APR 01/16 Chapter 52 Front Page 52-71-11 1 APR 01/16

CHAPTER

23 COMMUNICATIONS

B757 WIRING DIAGRAM MANUAL

NB239

VHF COMMUNICATIONS - CENTRE 23-12-31 INCORPORATES: 23-12-31 365 AEROSPACE MOD 0006

Page 1 Page 1

APR 01/16 APR 01/16 Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.


NB239

SELCAL CODING 23-21-12 INCORPORATES: 23-21-12 AERODEC MOD 1040

Page 1 Page 1



NB239

AIRCRAFT COMMUNICATIONS ADDRESSING & REPORTING (ACARS) DLINK & POWER

23-22-11 INCORPORATES: 23-22-11 365 AEROSPACE MOD 0006

Page 1 Page 1 Sheet 1 Sheet 1



NB239






NB239






NB239






NB239

VOICE RECORDER 23-71-11 INCORPORATES: 23-71-11 365 AEROSPACE MOD 0006 Page 1 Page 1

APR 01/16 APR 01/16

Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

CHAPTER

25 EQUIPMENT/

FURNISHINGS


NB239

GALLEY G1A WIRING 25-32-34 INCORPORATES: 25-32-34 AERODEC MOD 1043

Page (See Note) Page (See Note)



NB239

GALLEY G1A WIRING 25-32-34 INCORPORATES: 25-32-34 AERODEC MOD 1043

Page (See Note) Page (See Note)


CHAPTER

FUEL


NB239

FUEL QUANTITY INDICATION 28-41-11 INCORPORATES: 28-41-11 365 AEROSPACE MOD 0006 Page 1 Page 1

APR 01/16 APR 01/16


CHAPTER

31 INDICATING/ RECORDING

SYSTEM


NB239

FDRS – INTERCONNECT GROUP 1 31-31-01 INCORPORATES: 31-31-01 AERODEC MOD 1042

Page 1 Page 1



NB239

FLIGHT DATA RECORDER SYSTEM - DIGITAL INTERFACE GROUP 1 31-31-41 INCORPORATES: 31-31-41 365 AEROSPACE MOD 0006

Page 1 Page 1



NB239

PRINTER INTERFACE 31-33-01 INCORPORATES: 31-33-01 365 AEROSPACE MOD 0006

Page 1 Page 1



NB239

AURAL WARNING – BELL CHIME 31-51-33 INCORPORATES: 31-51-33 365 AEROSPACE MOD 0006 Page 1 Page 1

APR 01/16 APR 01/16


CHAPTER

LANDING GEAR


NB239

PARKING BRAKE SYSTEM 32-44-11 INCORPORATES: 32-44-11 365 AEROSPACE MOD 0006 Page 1 Page 1

APR 01/16 APR 01/16


CHAPTER

34 NAVIGATION


NB239

EFIS POWER/LIGHTING/ PROGRAM PINS - LEFT

34-22-16 INCORPORATES: 34-22-16 AERODEC MOD 1038

Page 1 Page 1



NB239

EFIS POWER/LIGHTING/ PROGRAM PINS - RIGHT


Page 1 Page 1



NB239

EFIS POWER/LIGHTING/ PROGRAM PINS - CENTER


Page 1 Page 1



NB239

GROUND PROXIMITY WARNING SYSTEM PROGRAM PINS 34-46-11 INCORPORATES: 34-46-11 AERODEC MOD 1039




NB239

GROUND PROXIMITY WARNING SYSTEM PROGRAM PINS 34-46-11 INCORPORATES: 34-46-11 AERODEC MOD 1039




NB239

ATC NO 1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1



NB239

ATC NO 2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1



NB239

LEFT FMC/EFIS/DATA LOADER GENERAL - OUTPUTS 34-61-15 INCORPORATES: 34-61-15 365 AEROSPACE MOD 0006

Page 1 Page 1


CHAPTER

DOORS


NB239

DOOR WARNING INDICATION – LEFT AND ACCESS 52-71-11 INCORPORATES: 52-71-11 365 AEROSPACE MOD 0006

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.

EQUIPMENT

LIST

INDEX


INCORPORATES: EQUIPMENT LIST Section INDEX 365 Aerospace MOD-0006 Page 1

Page produced by 365 Aerospace Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information. APR 01/16

SECTION PAGE NO. DATE SECTION PAGE NO. DATE

M09000 1 APR 01/16


INCORPORATES: EQUIPMENT LIST Section M09000 365 Aerospace MOD-0006 Page 1


Equip Part Number Used on Dwg Qty Diagram Effectivity Part Description Vendor Location

M09000 14114-1-02 (MOD 3) 2-59475-702 1 23-22-11 NB239 UNIT – DLINK+ ACARS EMTEQ P8 AFT PILOT CONTROL STAND M09001 12854-4 1 23-22-11 NB239 UNIT – PERSONALITY MODULE P8 AFT PILOT CONTROL STAND M09002 81194 365-25-0003 1 23-12-31 NB239 ANTENNA - GPS 365 AEROSPACE LTD STA 690 RBL 5.00 M09003 8055515-4503 2-59475-704 1 23-22-11 NB239 PRINTER – DATA (PTA-45B) EMTEQ P8 AFT PILOT CONTROL STAND M09004 84327-50-200B 365-25-0005 1 23-12-31 NB239 SENSOR – GPS/WAAS 365 AEROSPACE LTD E4-4 SHELF

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


INCORPORATES: WIRE LIST Section INDEX 365 Aerospace MOD-0006 Page 1


SECTION PAGE NO. DATE SECTION PAGE NO. DATE

W0069 1 APR 01/16 W0110 1 APR 01/16 W0124 1 APR 01/16 W1161 1 APR 01/16 W1163 1 APR 01/16 W1171 1 APR 01/16 W1260 1 APR 01/16 W1275 1 APR 01/16 W1280 1 APR 01/16 W1433 1 APR 01/16 W1447 1 APR 01/16 W1451 1 APR 01/16 W2069 1 APR 01/16 W2653 1 APR 01/16 W4228 1 APR 01/16 W4471 1 APR 01/16 W9001 1 APR 01/16 W9002 1 APR 01/16 W9003 1 APR 01/16 W9004 1-3 APR 01/16 W9008 1 APR 01/16


91-21-11

INCORPORATES: WIRE LIST Section W0069 365 Aerospace MOD-0006 Page 1


Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W0069 286N0069 FLIGHT RECORDER CONTROL, P61 9200B 24 23-22-11 SHT 4 P61 D40003P 38 P61 D9007J 1 NB239 MOD-0006 9200WB 24 23-22-11 SHT 4 P61 D40003P 39 P61 D9007J 2 NB239 MOD-0006 9200O 24 23-22-11 SHT 4 P61 D40003P 35 P61 D9007J 3 NB239 MOD-0006 9200WO 24 23-22-11 SHT 4 P61 D40003P 36 P61 D9007J 6 NB239 MOD-0006 9200Z 24 23-22-11 SHT 4 P61 D40003P 40 NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W0110 286N0110 P11-1 MODULE WIRING – LEFT BUSSES 0900 12 23-22-11 SHT 1 P11-1 C539 B P11-1 C9000 B NB239 MOD-0006 0901 16 31-33-01 P11-1 C592 B P11-1 C9001 B NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W0124 286N0124 P11-1 MODULE WIRING – LEFT – STBY – LOAD SIDE 0110 16 23-12-31. P11-1 C546 L P11-1 C9002 L NB239 MOD-0006 9000 16 23-22-11 SHT 1 P11-1 C9000 L P11-1 D40616J 7 NB239 MOD-0006 9001 22 31-33-01 P11-1 C9001 L P11-1 D40616J 2 NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1161 286N1161 E4-4 INTEGRATION 001CX BA5903 23-12-31. E4-4 D847C 1 E4-4 CAPPED AND STOWED NB239 MOD-0006 0029 24 23-12-31. E4-4 D847B C13 E4-4 CAPPED AND STOWED NB239 MOD-0006 0030 24 23-12-31. E4-4 D847B D13 E4-4 CAPPED AND STOWED NB239 MOD-0006 0031 24 23-12-31. E4-4 D847B B14 E4-4 D41529P 2 NB239 MOD-0006 0033 24 23-12-31. E4-4 D847B D1 E4-4 CAPPED AND STOWED NB239 MOD-0006 0036 16 23-12-31. E4-4 D847C 4 E4-4 CAPPED AND STOWED NB239 MOD-0006 0038 22 23-12-31. E4-4 D847B D3 E4-4 CAPPED AND STOWED NB239 MOD-0006 0039 24 23-12-31. E4-4 D847B A3 E4-4 CAPPED AND STOWED NB239 MOD-0006 0040 24 23-12-31. E4-4 D847B B3 E4-4 CAPPED AND STOWED NB239 MOD-0006 0041 24 23-12-31. E4-4 D847B C3 E4-4 CAPPED AND STOWED NB239 MOD-0006 0042 24 23-12-31. E4-4 D847B C1 E4-4 CAPPED AND STOWED NB239 MOD-0006 2041R 24 23-12-31. E4-4 D847B A1 E4-4 CAPPED AND STOWED NB239 MOD-0006 2041B 24 23-12-31. E4-4 D847B B1 E4-4 CAPPED AND STOWED NB239 MOD-0006 2042R 24 23-12-31. E4-4 D847B A15 E4-4 CAPPED AND STOWED NB239 MOD-0006 2042B 24 23-12-31. E4-4 D847B B15 E4-4 CAPPED AND STOWED NB239 MOD-0006 2043R 24 23-12-31. E4-4 D847B A13 E4-4 CAPPED AND STOWED NB239 MOD-0006 2043B 24 23-12-31. E4-4 D847B B13 E4-4 CAPPED AND STOWED NB239 MOD-0006 5018R 24 23-12-31. E4-4 D847B A7 E4-4 D9008-P1 13 NB239 MOD-0006 5018B 24 23-12-31. E4-4 D847B B7 E4-4 D9008-P1 14 NB239 MOD-0006 9001 22 23-12-31. E4-4 D847B D5 E4-4 CAPPED AND STOWED NB239 MOD-0006 9002 20 23-12-31. E4-4 SM35 E4-4 D9008-P1 1 NB239 MOD-0006 9003 20 23-12-31. E4-4 D9008-P1 2 E4-4 GD1765-DC NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1163 286N1163 E4-3 SHELF 9001 24 23-71-11 E4-3 DE9201J 52 E4-3 D41551J 20 NB239 MOD-0006 9002R 24 23-71-11 E4-3 DE9201J 53 E4-3 D41551J 21 NB239 MOD-0006 9002B 24 23-71-11 E4-3 DE9201J 54 E4-3 D41551J 22 NB239 MOD-0006 9002Z 24 23-71-11 E4-3 DE9201J 55 E4-3 D41551J 23 NB239 MOD-0006 9003R 24 23-71-11 E4-3 DE9201J 49 E4-3 D41551J 29 NB239 MOD-0006 9003B 24 23-71-11 E4-3 DE9201J 50 E4-3 D41551J 30 NB239 MOD-0006 9003Z 24 23-71-11 E4-3 DE9201J 51 E4-3 D41551J 31 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1171 286N1171 E2-1 INTEGRATION BUNDLE 0900 20 23-22-11 SHT 2 E2-1 D41391J 29 E2-1 GD1814-ST NB239 MOD-0006 0901 20 23-22-11 SHT 2 E2-1 D41391J 28 E2-1 GD1816-ST NB239 MOD-0006 0902 20 23-22-11 SHT 2 E2-1 D41391J 15 E2-1 GD1811-ST NB239 MOD-0006 5152B 24 23-22-11 SHT 2 E3-3 TB201 Z103 E3-3 TB201 Z106 NB239 MOD-0006 5152R 24 23-22-11 SHT 2 E3-3 TB201 Z104 E3-3 TB201 Z107 NB239 MOD-0006 9001R 24 23-71-11 E2-1 D41420J 20 E2-1 TB201 YC100 NB239 MOD-0006 9001B 24 23-71-11 E2-1 D41420J 21 E2-1 TB201 YC99 NB239 MOD-0006 9001Z 24 23-71-11 E2-1 D41420J 22 E2-1 GD1813 ST NB239 MOD-0006 9200R 24 23-22-11 SHT 2 E2-1 D41391J 18 E2-1 TB201 Z107 NB239 MOD-0006 9200B 24 23-22-11 SHT 2 E2-1 D41391J 13 E2-1 TB201 Z106 NB239 MOD-0006 9200Z 24 23-22-11 SHT 2 E2-1 D41391J 53 E2-1 NB239 MOD-0006 9201R 24 23-22-11 SHT 2 E2-1 D41391J 8 E2-1 TB201 Z122 NB239 MOD-0006 9201B 24 23-22-11 SHT 2 E2-1 D41391J 7 E2-1 TB201 Z121 NB239 MOD-0006 9201Z 24 23-22-11 SHT 2 E2-1 D41391J 9 E2-1 NB239 MOD-0006 9202R 24 23-22-11 SHT 2 E2-1 D41391J 43 E2-1 TB201 Z94 NB239 MOD-0006 9202B 24 23-22-11 SHT 2 E2-1 D41391J 44 E2-1 TB201 Z93 NB239 MOD-0006 9202Z 24 23-22-11 SHT 2 E2-1 D41391J 45 E2-1 NB239 MOD-0006 JPR-Z103 24 23-22-11 SHT 2 E2-1 TB201 Z103 E2-1 TB201 Z106 NB239 MOD-0006 JPR-Z104 24 23-22-11 SHT 2 E2-1 TB201 Z104 E2-1 TB201 Z107 NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1260 286N1260 INTERNAL P36- PLATES (A,B,D,E,F) 9001 20 32-44-11 P36 D2768 1 P36 GD1671-DC NB239 MOD-0006 9002 20 32-44-11 P36 D2768 2 P36 D40914J 2 NB239 MOD-0006 9003 20 23-12-31. P36 D40914P 2 P8 D9002 K- NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1275 286N1275 E4-2 SHELF –(N2) 9001 24 23-12-31 P8 D9002 Y- E4-2 D41628P 53 NB239 MOD-0006 9002 24 52-71-11 E4-2 D41628J 53 E4-2 TB207 YC80 NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1280 286N1280 E3-4 SHELF HARNESS 9001 24 31-51-33 E3-4 D42012J 13 E3-4 D41311J 19 NB239 MOD-0006 9002R 24 23-22-11 SHT 4 E3-4 D41445J 18 E3-4 TB182 YA3 NB239 MOD-0006 9002B 24 23-22-11 SHT 4 E3-4 D41445J 19 E3-4 TB182 YA5 NB239 MOD-0006 9002Z 24 23-22-11 SHT 4 E3-4 D41445J 17 E3-4 TB182 YA1 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1433 286N1433 E3-3 SHELF BUNDLE 0901 20 23-22-11 SHT 4 E3-3 D40670P 41 E3-3 GD1944-ST NB239 MOD-0006 0902 20 23-22-11 SHT 4 E3-3 D40670P 44 E3-3 GD1944-ST NB239 MOD-0006 5020R 24 23-22-11 SHT 4 E3-3 D11D C14 E3-3 TB181 YA120 NB239 MOD-0006 5020B 24 23-22-11 SHT 4 E3-3 D11D D14 E3-3 TB181 YC120 NB239 MOD-0006 5020Z 24 23-22-11 SHT 4 E3-3 TB181 YA121 NB239 MOD-0006 9200R 24 23-22-11 SHT 4 E3-3 D40670P 42 E3-3 TB181 YC120 NB239 MOD-0006 9200B 24 23-22-11 SHT 4 E3-3 D40670P 43 E3-3 TB181 YA120 NB239 MOD-0006 9200Z 24 23-22-11 SHT 4 E3-3 D40670P 41 NB239 MOD-0006 9201R 24 23-22-11 SHT 4 E3-3 D11D C14 E3-3 TB181 YC120 NB239 MOD-0006 9201B 24 23-22-11 SHT 4 E3-3 D11D D14 E3-3 TB181 YA120 NB239 MOD-0006 9201Z 24 23-22-11 SHT 4 E3-3 TB181 YA121 NB239 MOD-0006 9300R 24 23-22-11 SHT 4 E3-3 D40670P 45 E3-3 D11D H3 NB239 MOD-0006 9300B 24 23-22-11 SHT 4 E3-3 D40670P 46 E3-3 D11D H4 NB239 MOD-0006 9300Z 24 23-22-11 SHT 4 E3-3 D40670P 44 E3-3 GD1944-ST NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1447 286N1447 E2-1 SHELF TO E4-3 SHELF 9001R 24 23-71-11 E2-1 D41420P 20 E4-3 DE9201P 49 NB239 MOD-0006 9001B 24 23-71-11 E2-1 D41420P 21 E4-3 DE9201P 50 NB239 MOD-0006 9001Z 24 23-71-11 E2-1 D41420P 22 E4-3 DE9201P 51 NB239 MOD-0006


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Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W1451 286N1451 P-51 WIRE BUNDLE 0253 24 31-51-33 P51 D41059J 30 P51 SP9113 NB239 MOD-0006 9001 24 31-51-33 P51 D41481J 8 P51 SP9113 NB239 MOD-0006 9002 24 31-51-33 P51 D41059J 30 P51 SP9113 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W2069 286N2069 VHF-C CONTROL, P8 TO E4-4 0001 20 23-12-31. P8 D891 1 P8 CAPPED AND STOWED NB239 MOD-0006 0002 20 23-12-31. P8 D891 2 P8 CAPPED AND STOWED NB239 MOD-0006 0003 18 23-12-31. P8 D891 13 P8 CAPPED AND STOWED NB239 MOD-0006 0005 24 23-12-31. P8 D891 5 P8 CAPPED AND STOWED NB239 MOD-0006 0006 24 23-12-31. P8 D891 6 P8 CAPPED AND STOWED NB239 MOD-0006 0007 24 23-12-31. P8 D891 7 P8 CAPPED AND STOWED NB239 MOD-0006 0008 24 23-12-31. P8 D891 8 P8 CAPPED AND STOWED NB239 MOD-0006 0009 24 23-12-31. P8 D891 9 P8 CAPPED AND STOWED NB239 MOD-0006 0010 20 23-12-31. P8 D891 14 P8 CAPPED AND STOWED NB239 MOD-0006 5001R 24 23-12-31. P8 D891 17 P8 D9002 E- NB239 MOD-0006 5001B 24 23-12-31. P8 D891 18 P8 D9002 D- NB239 MOD-0006 5001Z 24 23-12-31. P8 D891 19 P8 D9002 S- NB239 MOD-0006 9001 22 23-12-31. P8 D891 4 P8 CAPPED AND STOWED NB239 MOD-0006 9002 24 23-12-31. P8 D9002 j E4-4 D41529J 2 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W2653 286N2653 VOICE RECORDER TO E/E RACK 9001 24 23-71-11 E4-3 D41551P 20 STA1615

WL290 BL5 CAP AND STOW IN VICINITY OF M201

NB239 MOD-0006 9002R 24 23-71-11 E4-3 D41551P 21 STA1615


NB239 MOD-0006 9002B 24 23-71-11 E4-3 D41551P 22 STA1615


NB239 MOD-0006 9002Z 24 23-71-11 E4-3 D41551P 23 STA1615


NB239 MOD-0006 9003 24 23-71-11 STA1615 GD180 DC STA1615


NB239 MOD-0006 WL290 BL5 9004R 24 23-71-11 E4-3 D41551P 29 STA1615


NB239 MOD-0006 9004B 24 23-71-11 E4-3 D41551P 30 STA1615


NB239 MOD-0006 9004Z 24 23-71-11 E4-3 D41551P 31 STA1615


NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W4228 286N4228 E/E SHELF DISC TO LEFT WING BODY DISC 9001 24 31-51-33 P8 D9002 G E3-4 D42012P 13 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W4471 286N4471 E/E RACK, INTERRACK LEFT 9001 24 31-51-33 E3-4 D41311P 19 P51 D41481P 8 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9001 9000 16 23-22-11 SHT 4 P8 D9001 A P11-1 D40616P 7 NB239 MOD-0006 9001 16 23-22-11 SHT 4 P8 D9001 B P8 GD2303-DC NB239 MOD-0006 9002 20 23-22-11 SHT 4 P8 D9001 G P8 TB58 Z3 NB239 MOD-0006 9003 20 23-22-11 SHT 4 P8 D9001 H P8 GD2303-AC NB239 MOD-0006 9004 16 23-22-11 SHT 4 P8 D9001 J P8 GD2303-DC NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9002 9100R 24 23-22-11 SHT 2 P8 D9002 U E2-1 D41391P 30 NB239 MOD-0006 9100B 24 23-22-11 SHT 2 P8 D9002 V E2-1 D41391P 31 NB239 MOD-0006 9100Z 24 23-22-11 SHT 2 P8 D9002 A- E2-1 D41391P 29 NB239 MOD-0006 9101R 24 23-22-11 SHT 2 P8 D9002 W E2-1 D41391P 23 NB239 MOD-0006 9101B 24 23-22-11 SHT 2 P8 D9002 X E2-1 D41391P 24 NB239 MOD-0006 9101Z 24 23-22-11 SHT 2 P8 D9002 I- E2-1 D41391P 28 NB239 MOD-0006 9102B 24 23-22-11 SHT 4 P8 D9002 D P61 D40003P 38 NB239 MOD-0006 9102WB 24 23-22-11 SHT 4 P8 D9002 E P61 D40003P 39 NB239 MOD-0006 9102O 24 23-22-11 SHT 4 P8 D9002 B P61 D40003P 35 NB239 MOD-0006 9102WO 24 23-22-11 SHT 4 P8 D9002 C P61 D40003P 36 NB239 MOD-0006 9102Z 24 23-22-11 SHT 4 P8 D9002 F P61 D40003P 40 NB239 MOD-0006 9103R 24 23-22-11 SHT 4 P8 D9002 S E3-3 D40670P 42 NB239 MOD-0006 9103B 24 23-22-11 SHT 4 P8 D9002 T E3-3 D40670P 43 NB239 MOD-0006 9103Z 24 23-22-11 SHT 4 P8 D9002 N E3-3 D40670P 41 NB239 MOD-0006 9104R 24 31-33-01 P8 D9006 V P8 D9002 AA NB239 MOD-0006 9104B 24 31-33-01 P8 D9006 W P8 D9002 BB NB239 MOD-0006 9104Z 24 31-33-01 P8 D9002 Z- NB239 MOD-0006 9105R 24 31-33-01 P8 D9006 E P8 D9002 CC NB239 MOD-0006 9105B 24 31-33-01 P8 D9006 F P8 D9002 DD NB239 MOD-0006 9105Z 24 31-33-01 P8 D9002 Z- NB239 MOD-0006 9106R 24 23-22-11 SHT 2 P8 D9002 Y E2-1 D41391P 43 NB239 MOD-0006 9106B 24 23-22-11 SHT 2 P8 D9002 Z E2-1 D41391P 44 NB239 MOD-0006 9106Z 24 23-22-11 SHT 2 P8 D9002 P- E2-1 D41391P 15 NB239 MOD-0006 9107R 24 23-22-11 SHT 4 P8 D9002 EE E3-4 D41445P 18 NB239 MOD-0006 9107B 24 23-22-11 SHT 4 P8 D9002 FF E3-4 D41445P 19 NB239 MOD-0006 9107Z 24 23-22-11 SHT 4 P8 D9002 GG E3-4 D41445P 17 NB239 MOD-0006 9108A 24 23-22-11 SHT 4 FLIGHT DECK D9002 J P10 D40901P 17 NB239 MOD-0006 9108B 24 23-22-11 SHT 4 FLIGHT DECK D40901J 17 FLIGHT DECK SP9108 NB239 MOD-0006 9108C 24 23-22-11 SHT 4 FLIGHT DECK D40677P 16 FLIGHT DECK SP9108 NB239 MOD-0006 9108D 24 23-22-11 SHT 3 FLIGHT DECK D40677J 16 FLIGHT DECK R9004 NB239 MOD-0006 9108F 24 23-22-11 SHT 4 FLIGHT DECK D41170P 16 FLIGHT DECK SP9108 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9002 (Continued…) 9108G 24 23-22-11 SHT 3 FLIGHT DECK D41170J 16 FLIGHT DECK D40249P 6 NB239 MOD-0006 9108H 24 23-22-11 SHT 3 FLIGHT DECK D40249J 6 FLIGHT DECK R9008 NB239 MOD-0006 9109A 24 23-22-11 SHT 4 FLIGHT DECK D9002 H P10 D40901P 28 NB239 MOD-0006 9109B 24 23-22-11 SHT 4 FLIGHT DECK D40901J 28 FLIGHT DECK SP9109 NB239 MOD-0006 9109C 24 23-22-11 SHT 3 FLIGHT DECK D40677P 21 FLIGHT DECK SP9109 NB239 MOD-0006 9109D 24 23-22-11 SHT 3 FLIGHT DECK D40677J 21 FLIGHT DECK R9001 NB239 MOD-0006 9109F 24 23-22-11 SHT 4 FLIGHT DECK D41170P 21 FLIGHT DECK SP9109 NB239 MOD-0006 9109G 24 23-22-11 SHT 3 FLIGHT DECK D41170J 21 FLIGHT DECK D40249P 7 NB239 MOD-0006 9109H 24 23-22-11 SHT 3 FLIGHT DECK D40249J 7 FLIGHT DECK R9005 NB239 MOD-0006 9110A 24 23-22-11 SHT 4 FLIGHT DECK D9002 N- P10 D40901P 29 NB239 MOD-0006 9110B 24 23-22-11 SHT 4 FLIGHT DECK D40901J 29 E5-1 SHELF D41325P 15 NB239 MOD-0006 9110C 24 23-22-11 SHT 4 E5-1 SHELF D41325J 15 M10331 D3312B D8 NB239 MOD-0006 9110D 24 23-22-11 SHT 4 E5-1 SHELF SP9114 M10331 D3312B D8 NB239 MOD-0006 9111R 24 23-22-11 SHT 4 P8 D9002 B- E4-3 DE9201P 30 NB239 MOD-0006 9111B 24 23-22-11 SHT 4 P8 D9002 C- E4-3 DE9201P 31 NB239 MOD-0006 9111Z 24 23-22-11 SHT 4 P8 D9002 KK E4-3 DE9201P 32 NB239 MOD-0006 9112R 24 23-22-11 SHT 4 P8 D9002 V- E4-3 DE9201P 33 NB239 MOD-0006 9112B 24 23-22-11 SHT 4 P8 D9002 W- E4-3 DE9201P 34 NB239 MOD-0006 9112Z 24 23-22-11 SHT 4 P8 D9002 X- E4-3 DE9201P 35 NB239 MOD-0006 9118R 24 23-71-11 SHT 1 FLIGHT DECK D9002 P E4-3 SHELF DE9201P 53 NB239 MOD-0006 9118B 24 23-71-11 SHT 1 FLIGHT DECK D9002 R E4-3 SHELF DE9201P 54 NB239 MOD-0006 9118Z 24 23-71-11 SHT 1 FLIGHT DECK D9002 A E4-3 SHELF DE9201P 55 NB239 MOD-0006 9119 24 23-71-11 SHT 1 E4-3 SHELF DE9201P 52 FLIGHT DECK D40901J 16 NB239 MOD-0006 9120A 24 23-22-11 SHT 4 FLIGHT DECK D40901P 16 FLIGHT DECK D40901P 23 NB239 MOD-0006 9120B 24 23-22-11 SHT 4 FLIGHT DECK D40901J 23 FLIGHT DECK D40677P 15 NB239 MOD-0006 9120C 24 23-22-11 SHT 3 FLIGHT DECK D40677J 15 FLIGHT DECK R9010 NB239 MOD-0006 9121A 24 23-22-11 SHT 3 FLIGHT DECK R9010 FLIGHT DECK SM9010 NB239 MOD-0006 9121B 24 23-22-11 SHT 3 FLIGHT DECK D9100 G FLIGHT DECK SM9010 NB239 MOD-0006 9121C 24 23-22-11 SHT 3 FLIGHT DECK R9009 FLIGHT DECK SM9010 NB239 MOD-0006 9122A 24 23-22-11 SHT 3 FLIGHT DECK R9009 FLIGHT DECK SM9002 NB239 MOD-0006 9122B 24 23-22-11 SHT 3 FLIGHT DECK R9002 FLIGHT DECK SM9002 NB239 MOD-0006 9122C 24 23-22-11 SHT 3 FLIGHT DECK R9003 FLIGHT DECK SM9002 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9002 (Continued…) 9122D 24 23-22-11 SHT 3 FLIGHT DECK TB64 Z18 FLIGHT DECK SM9002 NB239 MOD-0006 9123A 24 23-22-11 SHT 3 FLIGHT DECK TB64 Z17 FLIGHT DECK SM9001 NB239 MOD-0006 9123B 24 23-22-11 SHT 3 FLIGHT DECK SM9001 FLIGHT DECK SM9009 NB239 MOD-0006 9123C 24 23-22-11 SHT 3 FLIGHT DECK SM9001 FLIGHT DECK SM9003 NB239 MOD-0006 9123D 24 23-22-11 SHT 3 FLIGHT DECK D9100 D FLIGHT DECK SM9009 NB239 MOD-0006 9123E 24 23-22-11 SHT 3 FLIGHT DECK D9100 A FLIGHT DECK SM9009 NB239 MOD-0006 9123F 24 23-22-11 SHT 3 FLIGHT DECK D9100 B FLIGHT DECK SM9009 NB239 MOD-0006 9123G 24 23-22-11 SHT 3 FLIGHT DECK D9100 C FLIGHT DECK SM9009 NB239 MOD-0006 9123H 24 23-22-11 SHT 3 FLIGHT DECK D9101 D FLIGHT DECK SM9003 NB239 MOD-0006 9123J 24 23-22-11 SHT 3 FLIGHT DECK D9101 C FLIGHT DECK SM9003 NB239 MOD-0006 9123K 24 23-22-11 SHT 3 FLIGHT DECK D9101 B FLIGHT DECK SM9003 NB239 MOD-0006 9123L 24 23-22-11 SHT 3 FLIGHT DECK D9101 A FLIGHT DECK SM9003 NB239 MOD-0006 9124A 24 23-22-11 SHT 3 FLIGHT DECK R9001 FLIGHT DECK SM9004 NB239 MOD-0006 9124B 24 23-22-11 SHT 3 FLIGHT DECK R9002 FLIGHT DECK SM9004 NB239 MOD-0006 9124C 24 23-22-11 SHT 3 FLIGHT DECK D9101 G FLIGHT DECK SM9004 NB239 MOD-0006 9125A 24 23-22-11 SHT 3 FLIGHT DECK R9003 FLIGHT DECK SM9005 NB239 MOD-0006 9125B 24 23-22-11 SHT 3 FLIGHT DECK R9004 FLIGHT DECK SM9005 NB239 MOD-0006 9125C 24 23-22-11 SHT 3 FLIGHT DECK D9101 F FLIGHT DECK SM9005 NB239 MOD-0006 9126A 24 23-22-11 SHT 3 FLIGHT DECK SM2 FLIGHT DECK SM9006 NB239 MOD-0006 9126B 24 23-22-11 SHT 3 FLIGHT DECK D9102 D FLIGHT DECK SM9006 NB239 MOD-0006 9126C 24 23-22-11 SHT 3 FLIGHT DECK D9102 C FLIGHT DECK SM9006 NB239 MOD-0006 9126D 24 23-22-11 SHT 3 FLIGHT DECK D9102 B FLIGHT DECK SM9006 NB239 MOD-0006 9126E 24 23-22-11 SHT 3 FLIGHT DECK D9102 A FLIGHT DECK SM9006 NB239 MOD-0006 9127A 24 23-22-11 SHT 3 FLIGHT DECK R9005 FLIGHT DECK SM9007 NB239 MOD-0006 9127B 24 23-22-11 SHT 3 FLIGHT DECK R9006 FLIGHT DECK SM9007 NB239 MOD-0006 9127C 24 23-22-11 SHT 3 FLIGHT DECK D9102 G FLIGHT DECK SM9007 NB239 MOD-0006 9127D 24 23-22-11 SHT 3 FLIGHT DECK R9006 FLIGHT DECK SM1 NB239 MOD-0006 9128A 24 23-22-11 SHT 3 FLIGHT DECK R9008 FLIGHT DECK SM9008 NB239 MOD-0006 9128B 24 23-22-11 SHT 3 FLIGHT DECK R9007 FLIGHT DECK SM9008 NB239 MOD-0006 9128C 24 23-22-11 SHT 3 FLIGHT DECK D9102 F FLIGHT DECK SM9008 NB239 MOD-0006 9128D 24 23-22-11 SHT 3 FLIGHT DECK R9007 FLIGHT DECK SM1 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9003 9000 CX1 23-22-11 SHT 1 P8 D9003 1 P8 D169 A1 NB239 MOD-0006 9000X CX1 23-22-11 SHT 1 P8 D9003 C1 P8 D169 C1 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9004 9201 22 31-33-01 P8 D40616P 2 P8 D9006 R NB239 MOD-0006 9202 20 31-33-01 P8 D9006 N P8 GD2303-AC NB239 MOD-0006 9203 20 31-33-01 P8 D9006 L P8 GD2303-ST NB239 MOD-0006 9204 20 31-33-01 P8 D9006 M P8 GD2303-AC NB239 MOD-0006 9205 20 31-33-01 P8 D9006 E- P8 TB58 Z3 NB239 MOD-0006


91-21-11



Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9008 9001 CX1 23-12-31. E4-4 D9008-P2 =A STA 690 D9005 A1 NB239 MOD-0006 9001Z CX1 23-12-31. E4-4 D9008-P2 =C STA 690 D9005 C1 NB239 MOD-0006

ILLUSTRATED

PARTS

CATALOGUE

Contents

IPC-CONTENTS Page 1


11-31-04-01Z – PLACARD INSTL – SELCAL AND REGISTRATION




23-22-06-99Z – PANEL INSTL – P8 ELECTRONIC (DLINK+ ACARS UNIT ONLY)

23-22-90-99Z – ETHERNET RECEPTACLE INSTL – P61 PANEL (CPDLC SYSTEM ONLY)

23-22-92-99Z – ANNUNCIATOR INSTL – PANELS P1-3 & P3-3

23-22-95-99Z – PRINTER INSTL – P8 ELECTRONIC (DLINK+ ACARS PRINTER ONLY)

23-51-51-99Z – HEADPHONE ASSY - ELECTRICAL


24-51-53-99Z – CIRCUIT BREAKER INSTL – P11-1


25-31-99-01Z – HOT JUG INSTL – GALLEY NO.1A



Chapter 28 FUEL




31-31-01-01Z – EQUIPMENT INSTL – SOLID STATE FLIGHT DATA RECORDER

31-31-99-01Z – EQUIPMENT INSTL – MINI QAR


Chapter 33 LIGHTS


34-58-01-99Z – ANTENNA INSTL - GPS

34-58-05-99Z – SENSOR INSTL - GPS

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 11 Front Page 11-31-04-01Z 0 APR 01/16 11-31-04-01Z 1 APR 01/16 Chapter 23 Front Page 23-22-06-99Z 0 APR 01/16 23-22-06-99Z 1 APR 01/16 23-22-90-99Z 0 APR 01/16 23-22-90-99Z 1 APR 01/16 23-22-92-99Z 0 APR 01/16 23-22-92-99Z 1 APR 01/16 23-22-95-99Z 0 APR 01/16 23-22-95-99Z 1 APR 01/16 23-51-51-99Z 0 APR 01/16 23-51-51-99Z 1 APR 01/16 Chapter 24 Front Page 24-51-53-99Z 0 APR 01/16 24-51-53-99Z 1 APR 01/16 Chapter 25 Front Page 25-31-99-01Z 0 APR 01/16 25-31-99-01Z 1 APR 01/16 25-31-99-01Z 3 APR 01/16 25-31-99-01Z 4 APR 01/16 Chapter 31 Front Page 31-31-01-01Z 0 APR 01/16 31-31-01-01Z 1 APR 01/16 31-31-99-01Z 0 APR 01/16 31-31-99-01Z 1 APR 01/16 Chapter 34 Front Page 34-58-01-99Z 0 APR 01/16 34-58-01-99Z 1 APR 01/16 34-58-05-99Z 0 APR 01/16 34-58-05-99Z 1 APR 01/16

CHAPTER

11 PLACARDS AND

MARKINGS

B757 ILLUSTRATED PARTS CATALOGUE

11-31-04-01Z 11-31-04 AERODEC MOD 1040 Fig 1Z APR 01/16 Page 0


PLACARD INSTL – SELCAL AND REGISTRATION FIGURE 1Z




FIG ITEM PART NUMBER NOMENCLATURE EFF

CODE UNITS PER

ASSY 1234567

1Z --1 MEO-1040-001 SELCAL ADDRESS CODE PIN PROGRAMMING CHANGE 239239 RF

10 AL232-1613-001 • PLACARD - SELCAL 2 20 MS24617-2 • SCREW 4

-- ITEMS NOT ILLUSTRATED

CHAPTER

23 COMMUNICATIONS


23-22-06-99Z 23-22-06 MOD-0006 Fig 99Z APR 01/16 Page 0


PANEL INSTL – P8 ELECTRONIC (DLINK+ ACARS UNIT ONLY) FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 2-59475-702 DLINK+ UNIT INSTL (EMTEQ DRAWING) 239239 RF

10 14114-1-02 (MOD 3) • UNIT – DLINK+ ACARS 1 EQUIPMENT NUMBER: M9000

--20 CCD-14513-* • CONFIGURATION FILE 1 (* LATEST REVISION)

--30 12854-4 • UNIT – PERSONALITY MODULE 1 EQUIPMENT NUMBER: M9001





ETHERNET RECEPTACLE INSTL – P61 PANEL (CPDLC SYSTEM ONLY) FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 2-59475-703-101 ETHERNET RECEPT INSTL (EMTEQ DRAWING) 239239 RF

20 2-59475-101-104 • ETHERNET HARNESS ASSY 1 30 MS35206-215 • SCREW 4 40 NAS1149FN416P • WASHER 8 50 MS21042-04 • NUT 4 60 RJFC2B • CAP 1 70 2-59475-401-015 • PLACARD (DLINK+ ETHERNET) 1





ANNUNCIATOR INSTL – PANELS P1-3 & P3-3 FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 365-23-0005 INSTL OF A CPDLC SYSTEM (365 AEROSPACE DRAWING) 239239 RF

10 95-41-12-B6-E1EXM • ANNUNCIATOR – ATC/ACARS 2 20 95-41-11-B6-E0YKD • ANNUNCIATOR – DLINK REC 1

--30 18-200 • CONNECTOR 3





PRINTER INSTL – P8 ELECTRONIC (DLINK+ ACARS PRINTER ONLY) FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 2-59475-704 DATA PRINTER UNIT INSTL (EMTEQ DRAWING) 239239 RF

10 8055515-4503 • PRINTER – DATA (PTA-45B) V97896 1 EQUIPMENT NUMBER: M9003 OPTIONAL PART: 8055515-4502 8055515-4506

--20 8050917-0006 • PAPER ROLL – DATA PRINTER V97896 1





HEADPHONE ASSY - ELECTRICAL FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0123-001 CHANGE FOR THE INTRODUCTION OF A BOSE A20 HEADSET RF

10 324843-2020 • HEADSET – NOISE CANCELLING (MODEL: BOSE A20) 3 (11-08728)


CHAPTER

ELECTRICAL POWER




CIRCUIT BREAKER INSTL – P11-1 FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 2-59475-603 INSTL – CIRCUIT BREAKER (EMTEQ DRAWING) 239239 RF

10 MS22073-3 • CIRCUIT BREAKER – 3 AMPS 1 20 MS22073-7 1/2 • CIRCUIT BREAKER – 7.5 AMPS 1 30 2-59475-401-002 • PLACARD - “PRINTER” 1 40 2-59475-401-001 • PLACARD - “ACARS” 1

--50 2-59475-401-004 • PLACARD - “C9001” 1 --60 2-59475-401-003 • PLACARD - “C9000” 1


CHAPTER

25 EQUIPMENT/

FURNISHINGS




HOT JUG INSTL – GALLEY NO.1A FIGURE 1Z (SHEET 1 OF 2)




HOT JUG INSTL – GALLEY NO.1A FIGURE 1Z (SHEET 1 OF 2)





CODE UNITS PER

ASSY 1234567

1Z --1 MEO-1043-001 REPLACEMENT OF EXISTING WATER BOILER WITH HOT JUG 239239 RF --1 AL253-1608 DRIESSEN COMBO (HOT JUG) INSTL – GALLEY NO.1A 239239 RF --1 AL253-1681 CLOSING PANEL DRIESSEN GALLEY G1A 239239 RF --1 AL253-1682 COMBO ADAPTER PANEL ASSY DRIESSEN GALLEY G1A 239239 RF --1 AL253-0247 BRACKET – DRIESSEN COMBO CONNECTOR 239239 RF --1 AL253-0248 PLACARD – DRIESSEN COMBO USER INSTRUCTIONS 239239 RF --1 AL253-0524 PLACARD – MODIFICATION 239239 RF

10 JF003001 • COMBO ASSY – HOT JUG 1

--20 AL253-1682-001 • ADAPTER PANEL 1 ATTACHING PARTS

--21 NAS604-14 • SCREW 4 --22 NAS1149F0463P • WASHER 4

- - - - - - - - - - * - - - - - - - - - - --30 34-00318 • BRACKET 1

ATTACHING PARTS --31 NAS514P1032-12 • SCREW 2

- - - - - - - - - - * - - - - - - - - - - --40 AL253-0247-001 • BRACKET 1

ATTACHING PARTS --41 NAS603-12 • SCREW 4 --42 NAS1149F0332J • WASHER 4

- - - - - - - - - - * - - - - - - - - - - --50 AL253-1681-001 • CLOSING PANEL 1

ATTACHING PARTS --51 NAS603-12 • SCREW 5 --52 NAS1149F0332J • WASHER 5

- - - - - - - - - - * - - - - - - - - - - --60 AC16707 • CONNECTOR 1

ATTACHING PARTS --61 MS51960-31 • SCREW 4 --62 NAS1149D0616J • WASHER 4 --63 AN935-6 • WASHER 4 --64 MS35650-364 • NUT 4

- - - - - - - - - - * - - - - - - - - - - 70 MS51505-B4-4S • ELBOW 1 80 BACC18R4A • CIRCUIT BREAKER 1 90 AL253-1608-129 • PLACARD – “DO NOT USE…” 1

100 AL253-1608-128 • PLACARD – “WATER BOILER” 1 110 AL253-1608-127 • PLACARD – “COMBO” 1

--120 9-028-13 • SCREW 2






CODE UNITS PER

ASSY 1234567

--130 BACC10DK5 • P-CLIP 3 ATTACHING PARTS

--131 NAS603-7 • SCREW 3 --132 NAS1149D0332J • WASHER 5

- - - - - - - - - - * - - - - - - - - - - --140 AL113-0524-001 • PLACARD – MOD DATA 1 --150 AL113-0248-001 • PLACARD – USER INSTRUCTIONS 1


CHAPTER


SYSTEM




EQUIPMENT INSTL – SOLID STATE FLIGHT DATA RECORDER FIGURE 1Z





CODE UNITS PER

ASSY 1234567

1Z --1 MEO-1044-001 INSTALLATION OF A SOLID STATE FLIGHT DATA RECORDER 239239 RF

10 980-4700-042 • RECORDER – FLIGHT DATA (FDR) 1 (ALT PART NO. 980-4700-001 & 980-4700-003)





EQUIPMENT INSTL – MINI QAR FIGURE 1Z





CODE UNITS PER

ASSY 1234567

1Z --1 MEO-1042-001 INSTALLATION OF A MINI QUICK ACCESS RECORDER (QAR) 239239 RF

10 804-0005 • RECORDER – MINI QUICK ACCESS (QAR) 1


CHAPTER

34 NAVIGATION




ANTENNA INSTL – GPS FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF --1 365-25-0003 GPS ANTENNA INSTL (365 AEROSPACE DRAWING) 239239 RF

10 81194 • ANTENNA - GPS 1 EQUIPMENT NUMBER: M9002

20 NAS1473C3 • NUTPLATE 4 --30 365-23-0005-101 • PLACARD (GPS M9002) 1 50 PM570 • EROSION BOOT 1 60 TA71000438 • GASKET - GEL 1

--80 365-23-0005-104 • PLACARD (D9005) 1 110 AN510C10R16 • SCREW 4 120 365-25-0003-101 • GPS PLATE 1





SENSOR INSTL – GPS FIGURE 99Z





CODE UNITS PER

ASSY 1234567

99Z --1 EO-0006-001 INSTL OF A CPDLC SYSTEM 239239 RF

10 84327-50-200B • SENSOR – GPS/WAAS 1 EQUIPMENT NUMBER: M9004

--20 365-23-0005-201 • GPS – MOUNTING BRACKET 1


AIRCRAFT

MAINTENANCE

MANUAL

Contents

AMM-CONTENTS Page 1





23-22-00 – ACARS

PAGE BLOCK 1 – DESCRIPTION AND OPERATION

PAGE BLOCK 201 – SOFTWARE INSTALLATION

PAGE BLOCK 501 – ADJUSTMENT/TEST

23-22-01 – ACARS DLINK+ UNIT

PAGE BLOCK 401 – REMOVAL AND INSTALLATION

23-22-02 – PERSONALITY MODULE






Chapter 28 FUEL




31-31-00 – FLIGHT DATA RECORDER SYSTEM



31-31-01 – FLIGHT DATA RECORDER

PAGE BLOCK 201 – MAINTENANCE PRACTICES

31-31-99 – QUICK ACCESS RECORDER (MINI)

PAGE BLOCK 201 – MAINTENANCE PRACTICES

31-33-00 – DATA PRINTER


PAGE BLOCK 201 – PAPER ROLL REPLACEMENT


31-33-01 – DATA PRINTER


AMM-CONTENTS Page 2


Chapter 33 LIGHTS


34-22-00 – ELECTRONIC FLIGHT INSTRUMENT SYSTEM


34-46-00 – GROUND PROXIMITY WARNING SYSTEM


34-53-00 – AIR TRAFFIC CONTROL (ATC) SYSTEM


34-58-01 – GPS ANTENNA


Chapter 35 OXYGEN




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 31-31-00 528 AMM Contents 1 31-31-00 529 AMM Contents 2 31-31-00 530 AMM-List of Effective Pages 1 31-31-00 531 Chapter 23 Front Page 31-31-00 532 23-22-00 1 APR 01/16 31-31-00 533 23-22-00 2 APR 01/16 31-31-00 534 23-22-00 3 APR 01/16 31-31-00 535 23-22-00 201 APR 01/16 31-31-00 536 23-22-00 501 APR 01/16 31-31-01 201 23-22-00 502 APR 01/16 31-31-01 202 23-22-00 503 APR 01/16 31-31-01 203 23-22-00 504 APR 01/16 31-31-99 201 23-22-00 505 APR 01/16 31-31-99 202 23-22-01 401 APR 01/16 31-33-00 1 23-22-01 402 APR 01/16 31-33-00 2 23-22-02 401 APR 01/16 31-33-00 3 23-22-02 402 APR 01/16 31-33-00 201 Chapter 31 Front Page 31-33-00 202 31-31-00 1 APR 01/16 31-33-00 203 31-31-00 2 APR 01/16 31-33-00 501 31-31-00 3 APR 01/16 31-33-00 502 31-31-00 4 APR 01/16 31-33-01 401 31-31-00 5 APR 01/16 31-33-01 402 31-31-00 6 APR 01/16 Chapter 34 Front Page 31-31-00 501 APR 01/16 34-22-00 501 31-31-00 502 APR 01/16 34-46-00 501 31-31-00 503 APR 01/16 34-46-00 502 31-31-00 504 APR 01/16 34-53-00 501 31-31-00 505 APR 01/16 34-58-01 401 31-31-00 506 APR 01/16 34-58-01 402 31-31-00 507 APR 01/16 34-58-01 403 31-31-00 508 APR 01/16 34-58-01 404 31-31-00 509 APR 01/16 34-58-01 405 31-31-00 510 APR 01/16 31-31-00 512 APR 01/16 31-31-00 513 APR 01/16 31-31-00 514 APR 01/16 31-31-00 515 APR 01/16 31-31-00 516 APR 01/16 31-31-00 517 APR 01/16 31-31-00 518 APR 01/16 31-31-00 519 APR 01/16 31-31-00 520 APR 01/16 31-31-00 521 APR 01/16 31-31-00 522 APR 01/16 31-31-00 523 APR 01/16 31-31-00 524 APR 01/16 31-31-00 525 APR 01/16 31-31-00 526 APR 01/16 31-31-00 527 APR 01/16

CHAPTER

23 COMMUNICATIONS

B757 AIRCRAFT MAINTENANCE MANUAL

EFFECTIVITY

23-22-00 AIRPLANES WITH SPECTRALUX DLINK+ ACARS Page 1 MOD-0006 APR 01/16


ACARS – DESCRIPTION AND OPERATION 1. General

A. ACARS (Aircraft Communications Addressing and Reporting System) is a digital data link system that enhances two-way communications between the airplane and a ground station.

B. ACARS enhances air/ground communications by easing the flight compartment work load, and

eliminating much of the air/ground voice communication traffic. ACARS enables a high-speed computer controlled digital data link between the airplane and ground facilities using: a VHF transceiver, ARINC or other data link stations, landlines, a central control station, and airline terminals. The data link exchanges routing airlines operations information.

C. ACARS receives data inputs from airplane sensors, external systems, and the pilot inputs.

Data communications is displayed to the pilot via Dlink+ ACARS Display. Outgoing data communications are sent automatically or manually. Data is sent using ARINC assigned frequencies in ARINC encoded audio frequency tone modulation over the ground data link stations.

D. ACARS receives power from the left 28v dc bus. The system circuit breaker is on the

overhead panel P11. 2. Component Details (Fig. 1)

A. Dlink+ ACARS Unit.

(1) The Dlink+ ACARS Unit provides Aircraft Communication Addressing and Reporting System (ACARS) message functionality by combining three ARINC devices into one cockpit equipment panel mounted device. The three devices are: (a) ARINC 7248 Communication Management Unit (CMU) (b) ARINC 750 VHF Data Link (VDL) Radio (c) ARINC 739 Multi-purpose Control Display Unit (MCDU)

Dlink+ ACARS Unit provides air to ground and ground to air data only communication. The system sends and receives free text messages and ACARS messages to support Aircraft Operational Control (AOC) communications over the ACARS VHF data link. The system has a Personality Module (PM) which is a serial EEPROM that houses the unit's configuration and database. When the unit power-up it reads the configuration from the PM into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.

(2) The Dlink+ ACARS Unit design features are:

(a) Keyboard & display assembly (b) Display unit/power supply printed circuit assembly (DU/PS PCA) (c) Single board computer printed circuit assembly (SBC PCA) (d) Auxiliary input/output printed circuit assembly (AI/O PCA) (e) VHF data link PCA (VDL PCA) (118-136.975MHz Receiver and 15W Transmitter) (f) Electronic assembly (g) Soft keys


EFFECTIVITY



ACARS – Component Location

Figure 1

DLINK+ ACARS

FLIGHT COMPARTMENT

PRINTER


EFFECTIVITY



B. Personality Module (PM).

(1) The personality Module (PM) stores database used by the DI ink+ ACARS Unit. When the Dlink+ Unit is power-up it reads the configuration from the (PM) into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.

(2) The Personality Module (PM) is a cable wrapped to one of the Dlink+ ACARS Unit mating

connector's cable. The Personality Module has a pigtail of four wires that are inserted into the associated mating connector. These wires are used to load the stored database to the Dlink+ ACARS Unit (RAM) and download new database information.

C. Data Printer

(1) The printer is used to print the various Dlink+ ACARS Unit screen forms. Additionally,

if connected to other compatible subsystem, it will also print the screen forms for that subsystem.

3. Operation

A. Functional Description

(1) Off mode

(a) Dlink+ ACARS Unit is off when 28v de left bus power is removed from the unit. There is no system activity or indications.

(2) Operation

(a) When the Dlink+ ACARS Unit is power on, the unit reads the configuration of the

Personality Module PM to random access memory (RAM), internal to the Dlink+. Once powered, the unit can provide the capabilities for sending and receiving free text messages and ACARS messages to support end-to-end Aircraft Operational Control (AOC) communication over the ACARS data link.


EFFECTIVITY



ACARS - SOFTWARE INSTALLATION 1. General

A. This procedure contains the task to install the Spectralux Dlink+ ACARS Unit software into the Personality Module using a Laptop computer and the Ethernet maintenance port located on the P61 maintenance panel.

2. ACARS Software Installation with a Laptop Computer

A. References

(1) AMM 24-22-00/201, Electrical Power- Control.

B. Access

(1) Location Zones

211/212 Flight Compartment

C. Procedure

(1) Make sure the following circuit breaker is close:

(a) P11-1 Overhead Circuit Breaker:

1) ACARS

(2) On the P61 maintenance panel, connect the Laptop computer containing the Laptop Loader Software to the Ethernet port.

(3) Turn the Laptop computer ON and start the Laptop Loader Software containing the Dlink+

configuration files for the aircraft.

(4) To load the Dlink+ ACARS configuration to the personality module click on the Write Config button and select the appropriated file that is provided for the aircraft.

(5) Once the appropriated file is selected, click OPEN to access the configuration software

file.

(6) Enter the Tail Number and the ICAO address for the aircraft and press OK.

NOTE: The Laptop Loader will close and the DI ink+ ACARS Unit will reboot.

(7) After the Dlink+ ACARS Unit reboot is completed, start the Laptop Loader Software and click the Write DB button.

(8) Select the customer or test database file provided for the aircraft and click OPEN.

NOTE: The Laptop Loader will close and the Dlink+ Unit will reboot

(9) Turn off the Laptop and disconnect the Ethernet cable from the P61 maintenance panel's

Ethernet port.

(10) Do an ACARS System Test per AMM 23-22-00/501.


EFFECTIVITY



ACARS – ADJUSTMENT/TEST 1. General

A. There are two tasks in this procedure. The first task is the operational test of the Dlink+ Aircraft Communications Addressing and Reporting System (ACARS). The second is the system test of the ACARS.

B. The operational test is a minimum check of the basic ACARS System.

C. The system test contains checks of all of the primary ACARS functions. The test includes

checks of the OOOI operation, and the ACARS interfaces.

D. When the ACARS cannot make a link with the ground station it is not a system failure. This is usually one of the following conditions:

(1) The RF path between the VHF antenna and the ground station is blocked. It can help to

move the airplane to a better position.

(2) The ground station has a problem. Tell them that you cannot make a link. If they have a problem, other airplanes that use the data link will also get no ACARS communication.

E. If you tow the airplane, or move it with its power, open the ACARS circuit breaker. If you

do not, the ACARS may transmit the Out time. 2. ACARS Operational Test

A. References

(1) 23-22-00/201, ACARS Software Installation.

(2) 24-22-00/201, Electrical Power - Control.

B. Prepare for the Operational Test

(1) Supply electrical power (AMM 24-22-00/201)

(2) Make sure these circuit breakers are closed:

(a) P11-1 Overhead Circuit Breaker Panel: 1) ACARS 2) Data Printer

C. Procedure

(1) Test Setup

(a) Locate the aircraft on the airfield away from any existing structures that may

shadow the reception from a remote VHF ground station.

(b) From the main menu of the Dlink+ ACARS Unit, locate the maintenance menu by navigating thru the unit's menu selection.

NOTE: The menus will look different depending on specific aircraft type and

installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ ACARS Unit main menu.

(c) From the Dlink+ ACARS Unit main menu, select the Line Select Key (LSK) adjacent to

the MISC or MAINT menu option as required to access the maintenance menu pages.

NOTE: The Dlink+ ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the A half of the first page and typically contains a menu to check specific systems on page B.


EFFECTIVITY



(2) Dlink+ VHF Ping Test

(a) From the Dlink+ ACARS Unit maintenance menu (page B), select the Line Select Key

(LSK) adjacent to the PING TEST prompt.

(b) From the PING TEST screen, select the Line Select Key (LSK) L2 adjacent to the TEST CONTROL prompt and verify that the display changes form STOP to GO.

(c) Verify for proper VHF connection and that the Ping Test passes by verifying that

the TEST CONTROL display changes to WAIT and then returns to STOP.

NOTE: The DELAY CNT will count the seconds until the response is received. The AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.

(3) Annunciator Lights Test

(a) On the Dlink+ ACARS Unit, press and hold the A/B Line Select Key (LSK).

(b) Verify that the Dlink+ ACARS Unit annunciator lights (MSG, TEMP and FAIL) come on.

D. Put the Airplane back to its Initial Condition

(1) Return the Dlink+ ACARS display to the main menu page.

(2) Remove electrical power (AMM 24-22-00/201).

3. ACARS System Test

A. References (1) AMM 24-22-00/201, Electrical Power- Control (2) AMM 31-31-00/501, Flight Data Recorder System (3) AMM 31-41-00/501, EICAS System (4) AMM 32-09-02/501, Air/Ground Relay System (5) AMM 32-44-00/501, Parking Brake System (6) AMM 33-13-00/501, Integral Panel Lights (7) AMM 34-12-00/501, Left Air Data Computer System (8) AMM 34-21-00/501, Inertial Reference System (9) AMM 34-61-00/501, Left Flight Management System (10) AMM 52-71-00/501, Door Warning System Proximity Sensors

B. Prepare for the System Test

(1) Supply electrical power (AMM 24-22-00/201)

(2) Make sure all aircraft doors are closed.

(3) Make sure the parking brake is set.


(a) P11-1 Overhead Circuit Breaker Panel:

1) A CARS 2) Data Printer

C. Procedure

(1) Test Setup

(a) Locate the aircraft on the airfield away from any existing structures that may shadow the reception from a remote VHF ground station.


EFFECTIVITY



(b) From the main menu of the Dlink+ ACARS Unit, locate the maintenance menu by navigating thru the unit's menu selection.

NOTE: The menus will look different depending on specific aircraft type and

installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ ACARS Unit main menu.

(c) From the Dlink+ ACARS Unit main menu, select the Line Select Key (LSK) adjacent to

the MISC or MAINT menu option as required to access the maintenance menu pages.

NOTE: The Dlink+ ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the A half of the first page and typically contains a menu to check specific systems on page B

(2) Annunciator Lights Test

(a) On the Dlink+ ACARS Unit, press and hold the NB Line Select Key (LSK).

(b) Verify that the Dlink+ ACARS Unit annunciator lights (MSG, TEMP and FAIL) come on.

(3) Dlink+ OOOI Interface Test

(a) From the Dlink+ ACARS Unit maintenance (page A}, verify that the OOOI are

operating by changing the discrete states on the aircraft and verifying that they change state in the OOOI status maintenance menu screen:

DOORS (L1 & L2) Open/Close BRAKES (Parking Brake Set/Release) On/Off SQUAT (Aircraft Air/Ground Logic) Air/Ground

(4) Dlink+ Application Software Version Test


(LSK) adjacent to the DUNK CONFIG prompt.

(b) From the CONFIG screen, select the Line Select Key (LSK) adjacent to the VERSION menu option.

(c) From the VERSION screen, Verify that the following Application Software are being

used: SBC 6B70 10 5D58 DU D849

NOTE: The Application Software versions are provided by Spectralux.

(d) Return to the Dlink+ ACARS Unit CONFIG menu screen.

(5) Dlink+ Aircraft Registration & ICAO Address Test

(a) From the CONFIG screen, select the Line Select Key (LSK) adjacent to the USER EDIT

prompt.

NOTE: The USER EDIT option can edit the user's configurations.

(b) Verify that the PASSWORD menu screen is displayed.

(c) Type in the user password in the proper location and press the ENTER key.

NOTE: The default user password is "USEROO"

(d) Verify that the EDIT CONFIGURATION 1/3 menu screen is displayed.


EFFECTIVITY



(e) From the EDIT CONFIGURATION screen (page 1), verify that the correct aircraft registration number and ICAO address is displayed.

(f) Return to the Dlink+ ACARS Unit to the maintenance menu screen.

(g) If any changes were made to the EDIT CONFIGURATION screen. Follow the steps to

return to the Dlink+ ACARS Unit maintenance menu screen.

1) Select the Line Select Key (LSK) adjacent to the RETURN prompt, and verify that the CONFIRMATION menu is displayed.

2) On the CONFIRMATION menu screen, press the Line Select Key (LSK) until the NO

or YES option is displayed.

NOTE: Pressing the LSK will cycle the selection to NO, CANCEL and YES.

3) Once the NO or YES option is selected, select the Line Select Key (LSK) adjacent to the RETURN prompt to return the Dlink+ ACARS Unit to the maintenance menu screen.

(6) Dlink+ Monitor Bus Status Test


(LSK) adjacent to the MONITOR prompt.

NOTE: The Monitor menu will display the status of each of the 429 busses and some of the key variables interfaced to the Dlink+ ACARS Unit.

(b) From the MONITOR Bus Status screen, verify that each of the following 429 busses

EICAS, FMC, ADC and IRU display a GOOD status.

(c) Open each of the respective C/B for the EICAS, FMC, ADC and IRU systems. Verify that each of the respective 429 busses EICAS, FMC, ADC, and IRU display a FAIL status.

(d) Reset the C/B for the EICAS, FMC, ADC and IRU systems. Verify that each of the

following 429 busses EICAS, FMC, ADC, and IRU display a GOOD status.

(e) If there are any Variables displayed on the MONITOR Bus Status screen, verify that each of the variables display a value and not XXX.

(f) Return to the Dlink+ ACARS Unit maintenance menu screen.

(7) Dlink+ Printer Interface Test


(LSK) adjacent to the PRINT TEST prompt.

(b) From the PRINTER TEST screen, select the Line Select Key (LSK) adjacent to the PRINT prompt and verify that the data printer prints the information selected on the Dlink+ ACARS screen.

(c) Return to the Dlink+ ACARS Unit maintenance menu screen.

(8) Dlink+ VHF Ping Test

(a) From the Dlink+ ACARS Unit maintenance menu (page B}, select the Line Select Key

(LSK) adjacent to the PING TEST prompt.

(b) From the PING TEST screen, select the Line Select Screen (LSK) L2 adjacent to the TEST CONTROL prompt and verify that the display changes form STOP to GO.


EFFECTIVITY



(c) Verify for proper VHF connection and that the Ping Test passes by verifying that the TEST CONTROL display changes to WAIT and then returns to STOP.

NOTE: The DELAY CNT will count the seconds until the response is received. The

AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.

(d) Return to the Dlink+ ACARS Unit menu screen.

(9) Dlink+ Free Text Message Test

(a) From the Dlink+ ACARS Unit menu screen page A, select the Line Select Key (LSK)

adjacent to the FREE TEXT prompt.

(b) Select FREE TEXT option.

(c) From the FREE TEXT MSG screen (page A), Type in a message with a minimum length of 24 characters. The outgoing message should request the recipient to reply with a text message.

(d) Select (page B) of the FREE TEXT MSG screen and select the Line Select Key (LSK)

adjacent to the SEND option.

(e) Verify that the free text message was transmitted.

(f) Return to the Dlink+ ACARS Unit menu screen.

(g) Verify that the Dlink+ MSG (white) annunciator illuminates when the up-linked message is received. Confirm the received message is in response to the sent message.

D. Put the Airplane back to its Initial Condition

(1) Return the Dlink+ ACARS display to the main menu page.



EFFECTIVITY



ACARS DLINK+ UNIT - REMOVAL/INSTALLATION

1. General

A. There are two tasks in this procedure. The first task is the removal of the Dlink+ ACARS Unit. The second task is the installation of the Dlink+ ACARS Unit.

B. The Dlink+ ACARS Unit is installed on the P8 Aft Electronic Control Panel.

2. Dlink+ ACARS Unit - Removal

A. Access

(1) Location Zones


B. Procedure

(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:


1) ACARS 2) PRINTER

(2) Remove the Dlink+ ACARS Unit (AMM 20-10-01/401).

(a) Loosen the four quarter-turn fasteners that attach the Dlink+ ACARS Unit to the

panel.

(b) Lift the Dlink+ Unit to get access to the electrical connectors.

(c) Disconnect the electrical connectors.

(d) Put a protective cover on the electrical connector. 3. Dlink+ ACARS Unit- Installation

A. Access

(1) Location Zones


B. References

(1) 24-22-00/201, Electrical Power - Control

C. Procedure

(1) Make sure these circuit breakers are open:

(a) P11-1 Overhead Circuit Breaker Panel

1) ACARS 2) PRINTER

(2) Install the Dlink+ ACARS Unit (AMM 20-10-01/401).

(a) Remove the protective cover from the electrical connector.

(b) Examine the electrical connectors for bent or broken pins, dirt, and damage.


EFFECTIVITY



(c) Connect the electrical connector.

(d) Put the Dlink+ ACARS Unit in its position on the PS Panel.

(e) Tighten the four quarter-turn fasteners.

(3) Remove the DO-NOT-CLOSE tags and close these circuit breakers:


1) ACARS 2) PRINTER



EFFECTIVITY



PERSONALITY MODULE- REMOVAL/INSTALLATION 1. General

A. There are two tasks in this procedure. The first task is the removal of the Personality Module. The second task is the installation of the Personality Module.

B. The Personality Module is installed to one of the Dlink+ ACARS Unit mating connector harness

located in the P8 Aft Electronic Control Panel. 2. Personality Module - Removal

A. Access

(1) Location Zones


B. Procedure



1) ACARS 2) PRINTER

(2) Remove the Personality Module (AMM 20-10-01/401).

(a) Remove the Dlink+ ACARS Unit from PS aft electronic control panel (AMM 23-22-

01/401).

(b) Cut the tie cords that secure the Personality module to the connector harness.

(c) Disconnect the electrical connector.

(d) Put a protective cover on the electrical connector. 3. Personality Module - Installation

A. Access

(1) Location Zones


B. References


C. Procedure



1) ACARS 2) PRINTER

(2) Install the Personality Module (AMM 20-10-01/401 ).


(b) Examine the electrical connectors for bent or broken pins, dirt, and damage.


EFFECTIVITY




(d) Attach the Personality Module to the connector harness using tie cord.

(e) Install the Dlink+ ACARS Unit from PS aft electronic control panel (AMM 23-22-01/401).



1) ACARS 2) PRINTER

(4) Install the Personality Module Configuration and Database software per AMM 23-22-00/201.


CHAPTER


SYSTEM


EFFECTIVITY

31-31-00 AIRPLANES WITH HONEYWELL SSFDR Page 1 AERODEC MOD 1044 APR 01/16


FLIGHT DATA RECORDER SYSTEM - DESCRIPTION AND OPERATION 1. General (Fig. 1)

A. The system consists of a digital flight data acquisition unit (DFDAU) and a digital flight data recorder (SSFDR). It also consists of a flight recorder control panel, an accelerometer, and relay sensors.

B. All input signals are connected to the DFDAU. The DFDAU conditions the input

signals to produce a digital output which is sent to the SSFDR for recording. The recorded data is stored in a crash protected container inside the SSFDR.

C. The system is turned on automatically when the airplane is in flight, or on the

ground when an engine is running. The system may also be turned on manually or tested by means of a toggle switch on the flight recorder control panel.

D. The flight recorder system is monitored continuously by BITE during operation.

System failures are displayed on the flight recorder control panel and on the DFDAU and EICAS.

2. Component Details (Fig. 1)

A. Flight Recorder Control Panel (1) The flight recorder control panel (FRCP) provides system manual power control

and indicates system status. The control panel consists of a function (ON-NORM-TEST) switch, a relay and OFF annunciator.

(2) The function switch is normally set to the NORM position. In this position,

power to the system is automatically controlled through the system power relays. The ON position is used manually to turn on the DFDAU and the SSFDR. The TEST position is spring-loaded and is used to turn on power to the DFDAU and the SSFDR for testing purposes.

(3) The OFF light on the FRCP comes on when the SSFDR and/or the DFDAU fails, the

system is not turned on, or in the absence of electrical power.

B. Accelerometer (1) The flight recorder accelerometer is installed in the left wheel well.

(2) The accelerometer provides vertical, lateral, and longitudinal acceleration

signals to the DFDAU. The accelerometer measures vertical acceleration from -3G to +6G. It measures lateral and longitudinal accelerations from -1G to +1G.

C. Flight Recorder/System Relays.

(1) The flight recorder system relays include the left and right ENG START-TO-STOP relays and the SYS NO. 2 AIR/GND relay. The ENG START-TO-STOP relays provide AC power to the SSFDR when the corresponding engine is running. The SYS NO. 2 AIR/GND relay also provides AC power to the SSFDR when the airplane is airborne.

D. Flight Data Acquisition Unit (FDAU)

(1) The FDAU is a microprocessor controlled unit that sequentially receives specific data from various airplane systems and sensors. The acquired data is scaled and formatted into a digital data format. The FDAU outputs this data to the SSFDR for recording.


EFFECTIVITY



Flight Data Recorder System - Component Location Figure 1 (Sheet 1)


EFFECTIVITY



Flight Data Recorder System - Component Location Figure 1 (Sheet 2)


EFFECTIVITY



(2) The functions of the FDAU are as follows:

(a) A BITE and S/W PN positions switch - the toggle switch allows the operator to perform the BITE check of the FDAU and initiate the software configuration check. 1) Setting the switch to the BITE position will initiate the integrity

check of the FDAU. The FDAU, SSFDR, and the DMM or ACMS will light up in sequence. If no fault occurs then the status display will indicate NO FAULT. If a fault does occur, then the appropriate LED fault indicator will remain illuminated and the status display will read FDAU ERROR or ACMS ERROR.

2) Setting the switch to the S/W PN position enables the FDAU to display

the software configuration and part number.

(b) LED fault indicators - There are three fault indicators on front of the FDAU. They are the FDAU, SSFDR and the DMM or ACMS. If a fault occurs, the appropriate LED indicator will illuminate to identify the culprit.

(c) ATE connector - the connector allows the operator to connect the test

equipment to the FDAU for testing and trouble shooting the FDAU.

E. Digital Flight Data Recorder (SSFDR) (1) The flight data recorder writes the data for the last 25 hours of airplane

operation. The data is stored in solid state memory. The solid state memory is in a crash-proof container in the flight data recorder.

(2) The SSFDR is installed on the voice and flight recorder rack E7. This rack is

located above the aft galley ceiling. The exterior of the SSFDR is painted bright orange and has reflective tape affixed to it to aid in its location in the event of an accident.

(3) The underwater locator beacon (ULB) aids in location of a submerged SSFDR by

sending out an acoustic signal when the unit is submerged in water.

(4) The ULB is contained in a cylindrical watertight case designed to withstand high impact shock and deep water immersion. It is mounted on the front panel of the SSFDR.

(5) The ULB is battery operated and is designed to operate for at least 30 days

when immersed. It will withstand water depths of 20,000 feet and has a maximum detection range of 2,000 to 4,000 yards.

3. Operation

A. Functional Description (1) Power Distribution and Control

(a) During normal operation, ac power is supplied to the flight recorder system through the left and right ENG START-TO-STOP relays. The relays are wired in parallel so that any one relay can provide power to the SSFDR.


EFFECTIVITY



(b) The left and right ENG START-TO-STOP relays are actuated when the corresponding engine is first started. The engine ignition switches control the operation. At engine start, when an engine ignition switch is first turned on, the corresponding ENG START-TO-STOP relay (left or right) is energized. After the fuel control switch is set to RUN, it will cause the flight recorder control relay to remain energized after the ignition switch is selected to OFF. The relays remain energized until the fuel control switches are set to CUTOFF.

(c) The system No. 2 AIR/GND relay is also wired in parallel with the ENG

START-TO-STOP relays to provide power to the SSFDR. This relay de-energizes when the airplane becomes airborne, resulting in a contact closure that provides an additional means to maintain power to the SSFDR during flight.

(d) Manual power switching is accomplished with the ON-NORM-TEST switch on the

flight recorder control panel. During normal operation, the switch is set to NORM and power is controlled by the automatic switching network. When the switch is set to either ON or to the momentary TEST position, power is supplied to the system.

(e) The OFF light on the flight recorder control panel is a status indicator.

It is controlled by the status relay within the control panel. When the flight recorder system is powered and no faults exist, the status relay is energized and the OFF light is off. 28v dc from the SSFDR system status output and a ground from the FDAU BITE output energizes the relay. If power is interrupted or if a system fault occurs, the network opens, the status relay de-energizes and the OFF light comes on.

(2) Parameter Inputs

(a) The FDAU receives inputs from sensors and signals from other airplane systems. The inputs are grouped as analog, discrete, and ARINC 429 digital inputs.

(b) Accelerometer

1) The accelerometer receives 28-volt dc power from the DFDAU.

2) The unit consists of three independent accelerometers, one for each axis. Each accelerometer operates as a closed loop servo system that is responsive to linear acceleration along its sensitive axis. An applied acceleration results in a force on a seismic pendulum which disturbs the servos capacitive balanced bridge. As a result of this imbalance, the servo applies current to a torquer coil to return the pendulum to its original position. A sensing resistor in series with the torquer coil, provides a voltage that is proportional to the acceleration input. The voltage is then amplified and output to the FDAU.

(c) ARINC 429 DITS Inputs

1) The left and right engine EPR transmitters provide the EPR signals.


EFFECTIVITY



2) The left or right EICAS computer, via the EICAS select switch provides control surface signals. These signals are: a) Thrust Reverser In-Transit and Deployed b) Left and Right Aileron posiiton c) Left and Right Elevator Position d) Left and Right Rudder Position

3) The left or right ADC provides altitude and airspeed signals.

4) The left or center EFIS symbol generator provides pitch and roll

attitude and magnetic heading signals.

5) The left IRU provides longitude and latitude signals.

(3) Flight Data Acquisition Unit Function (a) The FDAU receives 115v ac power from the FLIGHT RECORDER AC circuit

breaker. The FDAU contains a switching regulator power supply that generates the necessary internal voltages and provides excitation outputs as follows:

(b) The FDAU receives the flight parameters to be recorded. It processes and

formats the signals. It then transmits the date to the SSFDR for recording. Data acquisition, signal processing and output data streams are controlled by the central processing unit (CPU).

(c) The FDAU BITE continuously performs internal circuit checks as soon a

power is applied. A BITE detected fault is output in a status word to the SSFDR and stored in a non-volatile memory for access by shop test equipment. The stored fault data provides a history of intermittent faults as well as identifying current faults. Current faults are indicated by the fault indicator on the FDAU's front panel.

(4) SSFDR Functions

(a) The SSFDR receives 115V ac power from the FLIGHT RECORDER AC circuit breaker through either the manual or automatic switching network. The SSFDR contains a regulated power supply that generates the necessary operating voltages.

(b) Under normal operation the FLT DATA REC message are not shown on the EICAS

status message. If the SSFDR malfunctions this will cause a discrete signal to be sent to the EICAS to generate the FLT DATA REC status message (Ref 31-41-00).

(5) Underwater Locator Beacon

(a) The underwater locator beacon is powered by a self contained battery. The ULB is activated when its water switch is immersed in water. The water switch is part of a low-current trigger circuit that turns on the oscillator circuit. The oscillator output drives a transducer that is mechanically coupled to the units case, radiating 37 kHz acoustic energy into the surrounding water. It sends out acoustic rf pulses when it is immersed in water up to 20,000 feet. It has a detection range of 2,000 to 4,000 yards.

(6) System Self Test

(a) A system self-test may be performed by momentarily setting the function switch on the control panel to the TEST position. The OFF light will extinguish if no fault is


EFFECTIVITY



FLIGHT DATA RECORDER SYSTEM - ADJUSTMENT/TEST 1. General

A. This procedure has these tasks.

(1) An operational test of the flight data recorder system. (2) A system test of the flight data recorder system.

TASK 31-31-00-715-001-003 2. Flight Data Recorder System - Operational Test

A. General

(1) The operational test makes sure the switches for the manual and automatic power sources operate correctly. A BITE test is also included in this operational test. No test equipment is necessary.

B. References

(1) AMM 24-22-00/201, Electrical Power Control (2) AMM 31-31-01/401, Flight Data Recorder (3) AMM 31-31-03/401, Digital Flight Data Acquisition Unit (4) AMM 32-09-02/201, Air/Ground Relays (5) FIM 31-31-00/101, Fig. 104

C. Prepare for the Test

S 865-002-003

(1) Supply electrical power (AMM 24-22-00/201).

S 865-003-003 (2) Make sure these circuit breakers are closed:

(a) On the overhead equipment panel P11:

1) 11J2, EICAS CMPTR LEFT 2) 11J3, EICAS UPPER IND 3) 11J7, FLIGHT RECORDER AC 4) 11J8, FLIGHT RECORDER DC 5) 11J29, EICAS CMPTR RIGHT 6) 11J30, EICAS LOWER IND 7) 11J31, EICAS DISPLAY SW 8) 11S15, AIR/GND SYS 1 9) 11S19, AIR/GND SYS 2

S 865-004-003


(a) On the miscellaneous equipment panel P6: 1) 6E1, FUEL VALVES L SPAR 2) 6E2, FUEL VALVES R SPAR

(b) On the overhead equipment panel P11:

1) 11D19, ENGINE START CONT LEFT 2) 11D20, ENGINE START CONT RIGHT


EFFECTIVITY



D. Flight Recorder Control Panel (FRCP) Test

S 715-005-003 (1) Make sure the function switch on the FRCP is in the NORM position.

S 715-006-003

(2) Make sure the OFF light on the FRCP is on.

S 715-007-003 (3) Push and hold the function switch on the FRCP in the TEST position.

(a) Make sure the OFF light goes off.

S 715-008-003 (4) Set the FRCP function switch in the ON position.

NOTE: The OFF light will come on momentarily when you turn the function

switch from the TEST position to the ON position.

(a) Make sure the OFF light stays off.

S 865-009-003 (5) Set the function switch to the NORM position.

E. Air/Ground Switch Test

S 865-010-003

WARNING: PREPARE THE SAFETY-SENSITIVE SYSTEMS FOR THE AIR MODE BEFORE YOU OPEN THE

AIR/GROUND CIRCUIT BREAKERS. IN THE AIR MODE, MANY OF THE AIRPLANE SYSTEMS CAN OPERATE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(1) Prepare the safety-sensitive systems for air mode simulation (AMM 32-09-

02/201).

S 865-011-003 (2) Open these circuit breakers:

(a) On the P11 panel: 1) 11C19, LANDING GEAR POS SYS 2 ALTN 2) 11S19, AIR/GND SYS 2

S 715-012-003

(3) Make sure the OFF light on the FRCP goes off.

S 865-013-003 (4) Close these circuit breakers:

(a) On the P11 panel: 1) 11C19, LANDING GEAR POS SYS 2 ALTN 2) 11S19, AIR/GND SYS 2

S 715-014-003

(5) Make sure the OFF light on the FRCP comes on.

S 865-015-003 (6) Put the safety-sensitive systems back to their initial conditions (AMM 32-09-

02/201).


EFFECTIVITY



F. Engine Automatic Switch Test

S 865-016-003 (1) Open these circuit breakers and attach DO-NOT-CLOSE tags:

(a) On the overhead equipment panel P11: 1) 11D7, ENGINES STBY IGNITION LEFT 1 2) 11D8, ENGINES STBY IGNITION LEFT 2 3) 11D9, ENGINES STBY IGNITION RIGHT 1 4) 11D10, ENGINES STBY IGNITION RIGHT 2 5) 11D20, BATTERY POWER ENGINE START CONT, R 6) 11L1, LEFT ENGINE IGN 1 7) 11L28, RIGHT ENGINE IGN 1

S 865-017-003

(2) Remove the DO-NOT-CLOSE tags and close these circuit breakers: (a) On the P11 panel:

1) 11D19, ENGINE START CONT LEFT

S 715-018-003 (3) Make sure the L and R FUEL CONT switches on the control stand is in the CUTOFF

position.

S 715-019-003 (4) Make sure the function switch on the FRCP is in the NORM position.

(a) Make sure the OFF light on the FRCP is on.

S 715-020-003 (5) On the pilots overhead panel, set the left engine start switch on the engine

start/RAT control panel to the GND position. (a) Make sure the OFF light on the FRCP goes off.

S 715-021-003

(6) Set the left engine start switch to the AUTO position. (a) Make sure the OFF light on the FRCP comes on.

S 865-022-003

(7) Open this circuit breaker and attach DO-NOT-CLOSE tags: (a) On the P6 panel:

1) 6C1, FUEL COND CONT L

(b) Make sure the OFF light on the FRCP goes off.

S 865-023-003 (8) Open this circuit breaker and attach a DO-NOT-CLOSE tag:

(a) On the P11 panel: 1) 11D19, ENGINE START CONT LEFT

S 865-024-003


1) 11D20, ENGINE START CONT RIGHT

S 715-025-003 (10) Make sure the L and R FUEL CONT switch is set to the CUTOFF position.


EFFECTIVITY



S 715-026-003 (11) At the pilots overhead panel, set the right engine start switch on the engine

start/RAT control panel to the GND position. (a) Make sure the OFF light on the FRCP is off.

S 715-027-003

(12) Set the right engine start switch to the AUTO position. (a) Make sure the OFF light on the FRCP comes on.

S 865-028-003

(13) Open this circuit breaker and attach a DO-NOT-CLOSE tag: (a) On the P6 panel:

1) 6C2, FUEL COND CONT R

(b) Make sure the OFF light on the FRCP goes off.

S 865-029-003 (14) Open this circuit breaker and attach a DO-NOT-CLOSE tag:

(a) On the P11 panel: 1) 11D20, ENGINE START CONT RIGHT

(b) Make sure the OFF light on the FRCP comes on.

G. BITE Test

S 745-342-003

(1) Do the steps that follow: (a) Set the FRCP function switch to the ON position.

1) Make sure the OFF light on the FRCP go off.

(b) At the main equipment rack, set the BITE S/W PN switch on the DFDAU to the BITE position then release. 1) On the DFDAU make sure the eight charater display segments and the all

BITE LED's come on then go off.

2) Make sure the DFDAU display shows NO FAULT.

(c) Set the function switch on the FRCP to the NORM position. 1) Make sure the OFF light comes on.

H. EICAS Message Test

S 865-032-003

(1) Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) On the P11 panel:

1) 11K9, LEFT ENGINE OIL PRESS 2) 11K35, RIGHT ENGINE OIL PRESS

S 865-033-003

(2) Make sure these circuit breakers are closed: (a) On the P11 panel:

1) 11D19, ENGINE START CONT LEFT 2) 11D20, ENGINE START CONT RIGHT


EFFECTIVITY



S 865-034-003 (3) Remove the DO-NOT-CLOSE tags and close these circuit breakers:

(a) On the P6 panel: 1) 6C1, FUEL COND CONT L 2) 6C2, FUEL COND CONT R

S 865-035-003

(4) Set the function switch on the FRCP to the ON position.

S 865-036-003 (5) Push the ECS MSG and AUTO EVENT switch on the EICAS MAINT panel on the right

side panel, P61.

S 865-037-003 (6) Push the ERASE switch on the EICAS MAINT panel for 1 second.

S 865-038-003

(7) Set the L and R FUEL CONT switches on the P10 panel to the RUN position and wait a minimum of 4 minutes.

S 715-039-003

(8) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure these EICAS messages, FLT DATA REC and FLT DATA ACQ, do not show

on the bottom display.

S 715-040-003 (9) Set the COMPUTER switch on the EICAS DISPLAY select panel to the R position.

(a) Make sure these EICAS message, FLT DATA REC and FLT DATA ACQ, do not show on the bottom display.

S 865-041-003

(10) Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) On the P11 panel:

1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC

S 025-042-003

(11) Remove the flight data recorder (FDR) (AMM 31-31-01/401).

NOTE: Wait a minimum of 60 seconds before you do the next step.

S 865-043-003 (12) Remove the DO-NOT-CLOSE tags and close these circuit breakers:

(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC

S 715-044-003

(13) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure the EICAS message, FLT DATA REC, shows on the bottom display.

(b) Make sure the EICAS message, FLT DATA AQC, does not show on the bottom

display.


EFFECTIVITY



S 715-045-003 (14) Set the COMPUTER switch on the EICAS DISPLAY select panel to the R position.

(a) Make sure the EICAS message, FLT DATA REC, shows on the bottom display.

(b) Make sure the EICAS message, FLT DATA AQC, does not show on the bottom display.

S 865-046-003

(15) Open this circuit breaker and attach the DO-NOT-CLOSE tag: (a) On the P11 panel:

1) 11J7, FLIGHT RECORDER AC

S 025-047-003 (16) Remove the DFDAU (AMM 31-31-03/401).

S 865-048-003

(17) Remove the DO-NOT-CLOSE tag and close this circuit breaker: (a) On the P11 panel:

1) 11J7, FLIGHT RECORDER AC

S 715-049-003 (18) Make sure the EICAS message, FLT DATA AQC, shows on the bottom display.

S 715-050-003

(19) Make sure the EICAS message, FLT DATA REC, does not show on the bottom display.

S 715-051-003

(20) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure the EICAS message, FLT DATA AQC, shows on the bottom display.

(b) Make sure the EICAS message, FLT DATA REC, does not show on the bottom

display.

S 015-052-003 (21) Open these circuit breakers and attach the DO-NOT-CLOSE tags:

(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDED DC

S 425-053-003

(22) Install the FDR (AMM 31-31-01/401).

S 425-054-003 (23) Install the DFDAU (AMM 31-31-03/401).

S 865-055-003


1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDED DC

(b) Return the L and R FUEL CONT SWITCHES to the CUTOFF position.

(c) Set the FRCP to the NORM position.


EFFECTIVITY



S 865-056-003 (25) Remove the DO-NOT CLOSE tags and close these circuit breakers:

(a) On the P11 panel: 1) 11D7, ENGINES STBY IGNITION LEFT 1 2) 11D8, ENGINES STBY IGNITION LEFT 2 3) 11D9, ENGINES STBY IGNITION RIGHT 1 4) 11D10, ENGINES STBY IGNITION RIGHT 2 5) 11K9, LEFT ENGINE OIL PRESS 6) 11K35, RIGHT ENGINE OIL PRESS 7) 11L1, LEFT ENGINE IGN 1 8) 11L28, RIGHT ENGINE IGN 1

S 865-057-003


1) 6E1, FUEL VALVES L SPAR 2) 6E2, FUEL VALVES R SPAR

TASK 31-31-00-705-058-003 3. Flight Data Recorder System - System Test

A. General (1) The system test does a test of the input parameters that are connected to the

flight data recorder. (2) Test equipment is necessary to do this task. (3) These tasks use the word SUBFRAME 0, 5, or 6 to make a selection of a

parameter. Some portable testers or on board test equipment do not have a switch position for SUBFRAME 0, 5, or 6. On these test sets, make a selection of SUBFRAMES as follow:

For SUBFRAME 0, use SUBFRAME 1, 2, 3, and 4. For SUBFRAME 5, use SUBFRAME 1 and 3. For SUBFRAME 6, use SUBFRAME 2 and 4.

B. Equipment

(1) Portable Tester - Teledyne P/N 2229738-1 Teledyne Controls 12333 West Olympic Boulevard West Los Angeles, CA 90064

(2) A31007-59 Adapter Cable - Tester (3) 964-0446-001 Hand Held Download Unit (HHDLU)

27914 AlliedSignal Inc., DBA AlliedSignal Aerospace 2100 Northwest 62nd Street Fort Lauderdale, FL 33309 (a) AIRPLANES WITH FDR P/N 980-4700-042;

The HHDLU must have mod 1 completed. (4) 704-2567-001 Adapter Cable - Tester (5) Multi-Purpose AIDS Display Units - AACO Inc.

FAA-0032-001 AACO Inc. 5011 Barton Place Seattle, WA 98118

(6) EGA-0005-001, Adapter Cable - MADU


EFFECTIVITY



(7) T-24B Set - Test, DME, RAMP (alternative)

Tel-Instrument Electronics Corp. 728 Garden St. Carlstadt, NJ 07072-1621

01-0331-00 Set - Test, DME, RAMP (alternative) 400 Industrial Pky. Industrial Airport, KS 66031

ATC600A Set - Test, ATC Transponder / DME, RAMP (alternative) IFR Systems Inc. 10200 West York St. Wichita, KS 67215-8935

C. References

(1) AMM 22-10-00/501, Autopilot/Flight Control System (2) AMM 22-32-00/501, Thrust Management System (3) AMM 22-21-00/501, YAW Damper System (4) AMM 22-41-00/501, Maintenance Control Display Panel (5) AMM 23-11-00/501, HF Communications System (6) AMM 23-12-00/501, VHF Communications System (7) AMM 24-22-00/201, Electrical Power - Control (8) AMM 27-32-00/501, Stall Warning System (9) AMM 27-41-00/501, Horizontal Stabilizer Trim Control System (10) AMM 27-51-00/501, Trailing Edge Flap System (11) AMM 27-81-00/501, Leading Edge Slat System (12) AMM 29-11-00/201, Main Hydraulic Systems (13) AMM 31-25-00/501, Clocks (14) AMM 31-41-00/501, Engine Indicating and Crew Altering System (15) AMM 32-09-02/201, Air/Ground Relays (16) AMM 34-12-00/501, Air Data Computing System (17) AMM 34-21-00/201, Inertial Reference System (18) AMM 34-21-00/501, Inertial Reference System (19) AMM 34-22-00/501, Flight Instrument System (20) AMM 34-26-00/501, Air Data Inertial Reference System (21) AMM 34-31-00/501, Instrument Landing System (22) AMM 34-33-00/501, Radio Altimeter System (23) AMM 34-46-00/501, Ground Proximity Warning System (GPWS) (24) AMM 34-51-00/501, VOR Navigation System (25) AMM 34-55-00/501, Distance Measurement Equipment System (26) AMM 34-61-00/501, Flight Management Computer System

D. Access

(1) Location Zone

212 Flight Compartment, Right

E. Prepare for the Test

S 215-396-003 (1) Do this task: DFDAU Software Configuration Check (AMM 31-31-03/201).


EFFECTIVITY



S 865-059-003 (2) Open these circuit breakers and attach DO-NOT-CLOSE tags:

(a) On the overhead equipment panel P11: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC

S 865-060-003

(3) If you use test equipment other than the hand-held download unit (HHDLU), install the tester to the test connector at the right side panel, P61.

S 865-061-003

(4) If you use the hand-held download unit (HHDLU), attach the HHDLU to the test connector at the front side of the flight data recorder.

NOTE: To get access to the FDR, open the lower ceiling panel No. 1 above the

aft galley (AMM 25-22-02/401). The HHDLU can only be connected to the AlliedSignal flight data recorder (FDR).

S 865-062-003


1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC 3) 11S1, MISC SYS AIDS SENSOR

S 865-063-003


S 865-064-003 (7) With the Data Signal Display Unit (DSDU), set the control switches on the

tester as follows: (a) Set the power switch to the ON position. (b) Set the INPUT switch to the ARINC INPUT DATA position. (c) Set the SYNC switch to the SYNC B position. (d) Set the DATA PARAMETER/DOCUMENTARY switch to the DATA PARAMETER position. (e) Set the OCTAL DISPLAY switch to the 12 BIT position. (f) Set the SUBFRAME and WORD as specified.

S 865-065-003

(8) With the Teledyne tester (P/N 2222786), set the switches on the tester as follows: (a) Set the POWER switch to the ON position. (b) Set the READOUT switch to the ACTF DATA position. (c) Set the UPDATE switch to the AUTO position. (d) Set the DFDAU/DFDR DATA SELECTOR switch to the DFDAU position. (e) Set the DATA switch to the 12 BIT position.


EFFECTIVITY



(f) Set the SUBFRAME and WORD as specified.

S 865-066-003

(9) With the Teledyne tester (P/N 2229738), set the switches on the tester as follows: (a) Push the CLR switch two or three times to clear all inputs.

NOTE: The tester will default to 64 words per second frame rate. This

setting will need to be changed in order for the tester to interface properly with the DFDR system.

(b) Push the WPS switch.

(c) Enter 256 and push the ENTER switch.

(d) Set the SUBFRAME and WORD as specified.

S 865-067-003

(10) With the hand-held download unit (HHDLU), do the steps that follow:

NOTE: These steps are for airplanes equipped with Allied Signal FDR only.

(a) On the flight recorder control panel (FRCP), set the function switch to the ON position.

(b) Push the red button on top of the HHDLU.

(c) Set the DSDU switch.

(d) Set the word number to WRD1, WRD2, or WRD3. (e) Set the BASE switch.

(f) In the BASE SELECT menu, set OCT for octal values.

(g) Set the SUBFRAME and WORD as specified.

S 865-068-003

(11) With the MADU, set the switches as follows: (a) Set the power switch to the ON position.

(b) Push the FUN switch, then enter the number 5 to set the LRU A on the

tester.

(c) Push the DATA switch, then the number 03 to set the DFDAU-H on the tester.

(d) Push the FUN switch, then the number 03 for SUBFRAME.

(e) Set a subframe (1 thru 4) on the keyboard switch.

(f) Push the DATA switch, then the number 04 for WORD.

(g) Set a word (1 thru 64) on the keyboard.

(h) Push the FUN switch, then the number 02 to set the FORMAT field on the tester.


EFFECTIVITY



(i) Push the number 02 to set the OCTAL 10 on the tester.

(j) Set the SUBFRAME and WORD as specified.

F. Greenwich Mean Time (GMT) Test

S 715-069-003 (1) Make sure the clock system operates correctly (AMM 31-25-00/501).

S 865-070-003

(2) On the tester, set the SUBFRAME to 1 and the WORD to 255.

S 865-071-003 (3) Set the captain's clock to 1 hour 5 minutes.

S 735-072-003

(4) Put the captain's clock in the RUN mode. (a) Make sure the tester display shows 0212 or 0213.

S 865-073-003

(5) Set the captain's clock to the correct time.

G. Traffic Collision Avoidance System (TCAS) Test

S 705-074-003 (1) Make sure these circuit breakers are closed:

(a) On the P11 panel: 1) 11S15, LANDING GEAR-AIR/GND SYS 1 2) 11S19, LANDING GEAR-AIR/GND SYS 2

S 705-075-003

(2) Do the the TCAS test that follows: (a) Set the SUBFRAME to 0 and the WORD to 223.

(b) On the TCAS/ATC control panel, push and release the TEST switch.

1) Make sure the BIT (DISCRETE) 12 shows a 1.

2) Make sure the TCAS is not in the self test mode and no resolution advisories are shown.

3) Make sure the BIT (DISCRETE) 12 shows a 0.

H. Captain's Air Data Computer (ADC) Select Switch Test

S 715-076-003

(1) Make sure the air data computing system operates correctly (AMM 34-12-00/501).

S 865-077-003 (2) Set the ADC switch on the left instrument source panel to the NORM position.

S 735-078-003


(a) Make sure the BIT (DISCRETE) 1 shows a 1.


EFFECTIVITY



S 735-079-003 (4) Set the ADC switch on the left instrument source select panel to the ALTN

position. (a) Make sure the BIT (DISCRETE) 1 shows a 0.

I. ADC Data Bus Test

S 715-080-003

(1) Make sure the air data computing system operates correctly (AMM 34-12-00/501).

S 865-081-003 (2) Set the ADC switch on the left instrument source select panel to the NORM

position.

S 865-082-003 (3) Push and hold the test switch for the left air data computer on the P61 test

panel in the test position for more than 7 seconds.

S 735-083-003 (4) On the tester, set the SUBFRAME to 0 and the WORD 96.

(a) Make sure the tester display shows between 2040 and 2160.

S 865-084-003 (5) Set the ADC switch on the left instrument source select panel to the ALTN

position.

S 865-085-003 (6) Push and hold the test switch for the right air data computer on the P61 test

panel in the test position for more than 7 seconds.

S 735-086-003 (7) Set the SUBFRAME to 0 and the WORD to 96.


S 865-087-003 (8) Set the ADC switch on the left instrument source select panel to the NORM

position.

J. Radio Altimeter (RA) Data Bus Test

S 715-088-003 (1) Make sure the RA system operates correctly (AMM 34-33-00/501).

S 865-089-003


S 735-090-003 (3) On the left RA receiver/transmitter, push the test switch.


S 865-091-003 (4) On the tester, set the SUBFRAME to 3.


EFFECTIVITY



S 735-092-003 (5) On the right RA receiver/transmitter, push the test switch.

(a) Make sure the tester displays between 0036 and 0062.


S 735-094-003

(7) On the center RA receiver/transmitter, push the test switch. (a) Make sure the tester displays between 0036 and 0062.

K. Captain's FMC Switch Position Test

S 735-340-003

(1) Do the FMC switch test that follows: (a) Make sure the flight management computer system is operational (AMM 34-61-

00/501).

(b) On the tester, set the SUBFRAME and WORD listed in the table that follows for each captain's FMC select switch.

(c) Make sure the tester shows the correct value shown on the table that

follows:

TESTER SETUP CAPTAIN’S FMC SWITCH POS.

TESTER DISPLAY

SUBFRAME WORD BIT (DISCRETE) VALUE

0 193

L FMC 1 1

R FMC 1 1

L CDU 1 0

L FMC 2 1

R FMC 2 0

L CDU 2 0

S 865-341-003

(2) Set the FMC and the IRS back to the usual condition.

L. Captain's Inertial Reference System (IRS) Switch Test

S 715-100-003 (1) Make sure the inertial reference system operates correctly (AMM 34-21-00/501).

S 865-101-003

(2) Set the IRS switch on the left instrument source select panel to the NORM position.

S 735-102-003

(3) On the tester, set the SUBFRAME to 0 and the WORD to 97. (a) Make sure the BIT (DISCRETE) 2 shows a 1.


EFFECTIVITY



S 735-103-003 (4) Set the IRS switch on the left instrument source select panel to ALTN

position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 865-104-003

(5) Set the IRS switch on the left instrument source select panel back to the NORM position.

M. IRS Data Bus Test

S 715-105-003

(1) Make sure the IRS operates correctly (AMM 34-21-00/501).

S 865-106-003 (2) Open these circuit breakers:

(a) On the P11 panel: 1) 11E9, FMCS CMPTR L 2) 11E30, FMCS CMPTR R

S 865-107-003


S 735-108-003

(4) Make sure the left IRU is aligned (AMM 34-21-00/201).

S 865-109-003 (5) On the tester, set the SUBFRAME to 0 and the WORD to 45.

S 735-110-003

(6) Push and hold the TEST switch on the left IRU for at least 10 seconds. (a) Make sure the tester display shows between 2760 and 3220.

S 865-111-003

(7) Close these circuit breakers: (a) On the P11 panel:

1) 11E9, FMCS CMPTR L 2) 11E30, FMCS CMPTR R

N. Captain's EFIS Select Switch Test

S 715-112-003

(1) Make sure the EFIS system operates correctly (AMM 34-22-00/501).

S 865-113-003 (2) Set the EFI switch on the left instrument source select panel to the NORM

position.




EFFECTIVITY



S 865-115-003 (4) Set the EFI switch on the left instrument source select panel to the ALTN


S 865-116-003

(5) Set the EFI switch on the left instrument source select panel to the NORM position.

P. EFIS Data Bus Test

S 715-117-003

(1) Make sure the EFIS system operates correctly (AMM 34-22-00/501).

S 865-118-003 (2) Make sure the EFIS switch on the left instrument source select panel is at the

NORM position.

S 715-119-003 (3) Make sure the left IRS operates correctly (AMM 34-21-00/501).

S 865-120-003


S 865-121-003

(5) Make sure the left IRU is aligned (AMM 34-21-00/501).


S 735-123-003

(7) Push and hold the TEST switch on the left IRU for at least 10 seconds. (a) Make sure the tester display shows between 0750 and 1030.

S 865-124-003

(8) Set the EFI switch on the left instrument source select panel to the ALTN position.

S 865-415-003


S 735-126-003 (10) Push and hold the TEST switch on the left IRU for at least 10 seconds.


S 865-127-003 (11) Set the EFI switch on the left instrument source select panel to the NORM

position.

Q. FCC Data Bus Test

S 715-128-003 (1) Make sure the autopilot/flight control system operates correctly (AMM 22-10-

00/501).


EFFECTIVITY



S 715-129-003 (2) Make sure the Maintenance Control Display Panel (MCDP) operates correctly (AMM

22-41-00/501).

S 865-130-003 (3) Make sure hydraulic pressure is removed from the hydraulic systems (AMM 29-11-

00/201).

S 735-131-003 (4) Push FLT FAULTS on the Maintenance Control Display Panel (MCDP).

S 735-132-003

(5) Push GND TEST on the MCDP.

S 865-133-003 (6) Push the L CMD swtich on the Mode Control Panel (MCP) until the L CMD switch

light comes on.



S 735-135-003 (8) Push the L CMD switch on the MCP.

(a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 0.

S 865-136-003 (9) Push the R CMD switch on the MCP until the R CMD switch light comes on.

S 735-137-003

(10) On the tester, set the WORD to 33 and the SUBFRAME to 2. (a) Make sure the BIT (DISCRETE) 2 shows a 1.

S 735-138-003

(11) Push the R CMD switch on the MCP. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 865-139-003

(12) Push the C CMD switch on the MCP until the C CMD switch light comes on.

S 735-140-003 (13) On the tester, set the WORD to 33 and the SUBFRAME to 4.


S 735-141-003 (14) Push the C CMD switch.


S 865-142-003 (15) Push FLT FAULTS on the MCDP.

R. Mode Control Panel (MCP) Switch Test

S 865-143-003

(1) Set the SUBFRAME to 0 and the WORD to 250 on the tester.


EFFECTIVITY



S 735-144-003 (2) Set the F/D switch on the left side of the MCP to the ON position.


S 735-145-003 (3) Set the F/D switch on the left side of the MCP to the OFF position.


S. Thrust Management Computer (TMC) Data Bus Test

S 715-146-003 (1) Make sure the thrust management system operates correctly (AMM 22-32-00/501).

S 715-147-003

(2) Make sure the EICAS system is operational (AMM 31-41-00/501).


S 865-149-003

(4) Make sure the MCDP is off.

S 865-150-003 (5) Set the autothrottle arm switch on the autopilot mode control panel to the ARM

position.

S 865-151-003 (6) Make sure the TMC is in the T/O mode on the EICAS display (AMM 22-32-00/501).

S 735-152-003

(7) Push the thrust reference set control on the EICAS display select panel. (a) On the tester display, make sure that BIT (DISCRETE) 2 shows a 1.

S 735-153-003

(8) On the TMSP, remove the T/O mode. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 865-154-003

(9) Set the TMC and the EICAS back to normal.

T. Electronic Engine Control (EEC) Data Bus Test

S 865-155-003 (1) Make sure this circuit breaker is closed:

(a) On the overhead equipment panel, P11: 1) 11L5, LEFT ENGINE EEC SUPV

S 865-156-003

(2) Set the left throttle lever to the full forward position.

S 865-157-003 (3) Set the right throttle lever to the full aft position.


EFFECTIVITY



S 865-158-003

(4) At the E1-1 rack next the left EEC unit, set the LEFT EEC GND TEST switch (S10379) to the up position.

S 865-159-003

(5) At the E3-1 rack next the right EEC unit, set the RIGHT EEC GND TEST switch (S10380) to the up position.

S 735-160-003

(6) On the tester, set the SUBFRAME to 0 and the WORD to 23. (a) Make sure the tester display shows between 5434 and 6000.

S 735-161-003


S 865-162-003

(8) At the E1-1 rack next the left EEC unit, set the LEFT EEC GND TEST switch (S10379) to the down position.

S 865-163-003

(9) At the E3-1 rack next the right EEC unit, set the RIGHT EEC GND TEST switch (S10380) to the down position.

S 865-164-003

(10) Open this circuit breaker: (a) On the P11 panel:

1) 11L5, LEFT ENGINE EEC SUPV


(a) On the P11 panel: 1) 11L32, RIGHT ENGINE EEC SUPV

S 865-166-003

(12) Set the left throttle lever to the full aft position.

S 865-167-003 (13) Set the right throttle lever to the full forward position.

S 865-168-003

(14) At the E1-1 rack next the left EEC unit, set the LEFT EEC GND TEST switch (S10379) to the up position.

S 865-169-003

(15) At the E3-1 rack next the right EEC unit, set the RIGHT EEC GND TEST switch (S10380) to the up position.

S 735-170-003


S 735-171-003



EFFECTIVITY



S 865-172-003 (18) At the E1-1 rack next the left EEC unit, set the LEFT EEC GND TEST switch

(S10379) to the down position.

S 865-173-003 (19) At the E3-1 rack next the right EEC unit, set the RIGHT EEC GND TEST switch

(S10380) to the down position.

S 865-174-003 (20) Close this circuit breaker:

(a) On the P11 panel: 1) 11L5, LEFT ENGINE EEC SUPV

U. Distance Measuring Equipment (DME) Data Bus Test

S 715-175-003

(1) Make sure the DME system operates correctly (AMM 34-55-00/501).

S 715-176-003 (2) Make sure the VOR navigation system operates correctly (AMM 34-51-00/501).

S 865-177-003

(3) On the left VOR control panel, set the frequency to 108.00 MHZ.

S 865-178-003 (4) On the DME ramp test set, set the tester NAV control dial to 108.00 MHZ with a

distance of 50 NM.



S 865-180-003 (6) On the right VOR control panel, set the frequency to 108.00 MHZ.

S 865-181-003

(7) On the DME ramp test set, set the distance to 100 NM.



V. Instrument Landing System (ILS) Data Bus Test

S 715-183-003 (1) Make sure the ILS operates correctly (AMM 34-31-00/501).

S 865-184-003

(2) Open these circuit breakers: (a) On the P11 panel:

1) 11A3, ILS C (MMR C) 2) 11E31, ILS R

S 865-185-003



EFFECTIVITY



S 865-186-003 (4) Push the self test button on the ILS control panel, P8.

S 735-187-003

(5) Wait for a one dot right indication on the EHSI. (a) Make sure the tester display shows between 0574 to 0634.

S 865-188-003


1) 11E10, ILS L (MMR L)


(a) On the P11 panel: 1) 11E31, ILS R (MMR R)

S 865-190-003

(8) On the tester, set the SUBFRAME to 3.


S 735-192-003

(10) Wait for a one dot right indication on the EHSI. (a) Make sure the tester display shows between 0574 to 0634.

S 865-193-003


1) 11E31, ILS R (MMR R)


(a) On the P11 panel: 1) 11A3, ILS C (MMR C)

S 865-195-003

(13) On the tester, set the SUBFRAME to 4.


S 735-197-003

(15) Wait for a one dot right indication on the EHSI. (a) Make sure the tester display shows between 0574 and 0634.

S 865-198-003

(16) Close these circuit breakers: (a) On the P11 panel:

1) 11E10, ILS L (MMR L) 2) 11E31, ILS R (MMR R)


EFFECTIVITY



W. Yaw Damper Engage Test

S 715-199-003 (1) Make sure the yaw damper system operates correctly (AMM 22-21-00/501).

S 865-200-003 WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE

THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(2) Supply hydraulic power (AMM 29-11-00/201).

S 715-201-003

(3) Make sure the IRS operates correctly (AMM 34-21-00/501).

S 865-202-003 (4) Make sure the IRUs are aligned (AMM 34-21-00/201).

S 715-203-003

(5) Make sure the left and right yaw dampers are not engaged.


(a) Make sure the BIT (DISCRETE) 2 shows a 0. (b) Make sure the BIT (DISCRETE) 1 shows a 0.

S 865-205-003

(7) Push the left yaw damper switch on the P5 panel to the ON position. (a) Make sure the BIT (DISCRETE) 2 shows a 1.

S 865-206-003

(8) Push the left yaw damper switch on the P5 panel to disengage the left yaw damper.

S 865-207-003

(9) Push the right yaw damper switch on the P5 panel to the ON position. (a) Make sure the BIT (DISCRETE) 1 shows a 1.

S 865-208-003

(10) Push the right yaw damper switch on the P5 panel to disengage the right yaw damper.

X. VHF Omnidirectional Range (VOR) Data Bus Test

S 715-209-003

(1) Make sure the VOR navigation system operates correctly (AMM 34-51-00/501).

S 865-210-003 (2) Set a frequency of 110.00 MHZ on the left VOR control panel.

S 735-211-003

(3) On the tester, set the SUBFRAME to 4 and the WORD to 222. (a) Make sure the tester display shows 4000 or 4001.


EFFECTIVITY



S 865-212-003 (4) Set a frequency of 109.60 MHZ on the right VOR control panel.

S 735-213-003

(5) On the tester, set the SUBFRAME 2. (a) Make sure the tester display shows 2260 or 2261.

Y. Master Warning Test

S 865-214-003

(1) Make sure these circuit breakers are closed: (a) On the P11 panel:

1) 11A31, IND LTS TEST 2) 11A34, IND LTS 3 3) 11F4, GND PROX CMPTR

S 865-215-003


S 735-216-003 (3) Momentarily set the test switch on the miscellaneous test panel to the GND

PROX position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 735-217-003

(4) Push the MASTER WARNING light switch. (a) Make sure the BIT (DISCRETE) 2 shows a 1.

Z. Brake Pressure Test

S 715-218-003

(1) Make sure you put chocks on the wheels.

S 865-219-003

WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(2) Pressurize the right hydraulic system and reservoir (AMM 29-11-00/201).

S 715-220-003

(3) Make sure the engine indicating and crew alerting system (EICAS) operates correctly (AMM 31-41-00/501).

S 865-221-003

(4) Push the ELEC/HYD switch on the EICAS MAINT panel on the right side panel, P61.

S 715-222-003

(5) Make sure the parking brake is released.



EFFECTIVITY



S 735-224-003 (7) Push and hold the captain's left brake pedal to the full stop position.

(a) Make sure the tester display shows the value in the Table 501.

NOTE: The value must agree with the nearest hydraulic system pressure. Test data X can have all values.

Table 501

HYDRAULIC SYSTEM (Pressure as displayed on EICAS status page)

TESTER DISPLAY

2300 52XX-60XX

2400 54XX-62XX

2500 55XX-63XX

2600 57XX-65XX

2700 61XX-67XX

2800 63XX-71XX

2900 65XX-74XX

3000 67XX-75XX

S 865-225-003

(8) Release the captain's left brake pedal.


S 735-227-003

(10) Push and hold the captain's right brake pedal to the full stop position. (a) Make sure the tester display shows the value in the Table 502.

NOTE: The value must agree with the nearest hydraulic system pressure.

Test data X can have all values.

Table 502


TESTER DISPLAY

2300 52XX-60XX

2400 54XX-62XX

2500 55XX-63XX


EFFECTIVITY



Table 502 (Continued)


TESTER DISPLAY

2600 57XX-65XX

2700 61XX-67XX

2800 63XX-71XX

2900 65XX-74XX

3000 67XX-75XX

S 865-228-003

(11) Release the captain's right brake pedal.

S 865-229-003 (12) Remove the pressure from the right hydraulic system and reservoir (AMM 29-11-

00/201).

S 865-230-003 (13) Pump the brake pedals at least six times to fully deplete the accumulator.

S 865-231-003

(14) Pressurize the left hydraulic system and reservoir (AMM 29-11-00/201).


S 735-232-003

(16) Push and hold the captain's left brake pedal to the full stop position. (a) Make sure the tester display shows the value in the Table 501.

NOTE: The value must agree with the nearest hydraulic system pressure.

Test data X can have all values.

S 865-233-003 (17) Release the captain's left brake pedal.

S 865-429-003


S 735-234-003 (19) Push and hold the captain's right brake pedal to the full stop position.

(a) Make sure the tester display shows the value in Table 502.

NOTE: The value must agree with the nearest hydraulic system pressure. Test data X can have all values.

S 865-235-003

(20) Release the captain's right brake pedal.


EFFECTIVITY



S 865-236-003 (21) Remove the pressure from the left hydraulic system and reservoir (AMM 29-11-

00/201).

AA. Brake Pedal Test

S 735-394-003 (1) For the captain's brake pedal, do the steps that follow:

(a) On the tester, set the SUBFRAME to 0 and the WORD to 192.

(b) Push the captain's brake pedal. 1) Make sure the value of bit 2 is 0.

(c) Release the captain's brake pedal.

1) Make sure the value of bit 2 is 1.

S 735-395-003 (2) For the first officer's brake pedal, do the steps that follow:

(a) On the tester, set the SUBFRAME to 0 and the WORD to 192.

(b) Push the first officer's brake pedal. 1) Make sure the value of bit 1 is 0.

(c) Release the first officer's brake pedal.

1) Make sure the value of bit 1 is 1.

AB. Seat Belt Signal Test


(a) On the P11 panel: 1) 11P9, PASS SIGN CONT

S 865-238-003

(2) On the overhead panel, P5, set the SEATBELTS switch on the passenger signs control panel to the ON position.

S 735-239-003

(3) On the tester, set the SUBFRAME to 0 and the WORD to 105. (a) On the tester, make sure the BIT (DISCRETE) 1 shows a 0.

S 735-240-003

(4) On the passenger signs control panel, set the SEATBELTS switch to the OFF position. (a) On the tester, make sure the BIT (DISCRETE) 1 shows a 1.

AC. EICAS Computer Switch Test

S 715-241-003

(1) Make sure the EICAS operates correctly (AMM 31-41-00/501).

S 865-242-003 (2) Set the COMPUTER select switch on the EICAS DISPLAY select panel to the R

position.


EFFECTIVITY



S 735-243-003 (3) On the tester, set the SUBFRAME to 0 and the WORD to 161


S 735-244-003 (4) Set the COMPUTER switch on the EICAS DISPLAY select panel in the AUTO

position. (a) On the tester, make sure the BIT (DISCRETE) 1 shows a 1.

AD. Captain's Control Column Position (Syncro) Test

S 865-245-003

(1) Make sure the left, center, and right hydraulic systems are depressurized (AMM 29-11-00/201).

S 865-246-003


S 865-423-003 (3) Make sure the control column is in the neutral positon.

(a) Make sure the test display shows between 7764 and 0014.

S 735-247-003 (4) Set the control column to the full aft position against the stop.

(a) Make sure the tester shows between 0416 and 0560.

S 735-248-003 (5) Set the control column to the full forward position against the stop.


AE. First Officer's Control Column Position (Syncro) Test

S 865-399-003 (1) Make sure the left, center, and right hydraulic systems are depressurized (AMM

29-11-00/201).


S 865-352-003

(3) Set the control column to the full aft position against the stop. (a) Make sure the tester shows between 7140 and 7520.

S 865-353-003

(4) Set the control column to the full forward position against the stop. (a) Make sure the tester shows between 0300 and 0465.

AF. Captain's Control Column Force Position (Syncro) Test

S 865-357-003



EFFECTIVITY




(a) Make sure there is no pressure to the control column.

S 735-359-003 (3) Set the captain's control column to the full aft position against the stop.

(a) Make sure the octal display increases in value.

S 735-360-003 (4) Set the captain's control column to the full forward position against the

stop. (a) Make sure the octal display decrease in value.

AG. First Officer's Control Column Force Position (Syncro) Test

S 865-402-003


S 865-361-003

(2) On the tester, set the SUBFRAME to 0 and the WORD to 43. (a) Make sure there is no pressure to the control column.

S 735-362-003

(3) Set the first officer's control column to the full aft position against the stop. (a) Make sure the octal display increases in value.

S 735-363-003

(4) Set the first officer's control column to the full forward position against the stop. (a) Make sure the octal display decrease in value.

S 865-364-003

(5) Set the control column to the neutral position.

AH. Captain's Control Wheel Position (Syncro) Test


29-11-00/201).


S 865-424-003

(3) Make sure the control wheel is in the neutral positon. (a) Make sure the test display shows between 7764 and 0014.

S 735-252-003

(4) Turn the control wheel to the full counter clockwise against the stop. (a) Make sure the tester display shows between 1020 and 1100.


EFFECTIVITY



S 735-253-003 (5) Turn the control wheel to the full clockwise against the stop.


AI. First Officer's Control Wheel Position (Syncro) Test


29-11-00/201).


S 865-355-003

(3) Turn the control wheel to the full counter clockwise against the stop. (a) Make sure the tester display shows between 1020 and 1100.

S 735-356-003

(4) Turn the control wheel to the full clockwise against the stop. (a) Make sure the tester display shows between 6700 and 6760.

AJ. Captain's Control Wheel Force Test

S 865-400-003


S 865-365-003

(2) On the tester, set the SUBFRAME to 0 and the WORD to 170. (a) Make sure there is no pressure to the control wheel.

S 735-366-003

(3) Turn the control wheel to the full counter clockwise against the stop. (a) Make sure the octal display decreases in value.

S 735-367-003

(4) Turn the control wheel to the full clockwise against the stop. (a) Make sure the octal display increases in value.

AK. First Officer's Control Wheel Force Test

S 865-401-003


S 865-368-003

(2) On the tester, set the SUBFRAME to 0 and the WORD to 171. (a) Make sure there is no pressure to the control wheel.

S 735-369-003

(3) Turn the control wheel to the full counter clockwise against the stop. (a) Make sure the octal display decreases in value.

S 735-370-003

(4) Turn the control wheel to the full clockwise against the stop. (a) Make sure the octal display increases in value.


EFFECTIVITY



S 865-254-003 (5) Set the control wheel back to the neutral position.

AL. Rudder Pedal Position (Syncro) Test

S 865-255-003

(1) Make sure the left, center, and right hydraulic systems are depsressurized (AMM 29-11-00/201).

S 865-256-003


S 865-427-003 (3) Make sure the rudder pedal is in the neutral positon.

(a) Make sure the test display shows between 7764 and 0014.

S 735-257-003 (4) Set the left rudder pedal to the full forward against the stop.


S 735-258-003 (5) Set the right rudder pedal to the full forward against the stop.


S 865-259-003 (6) Set the rudder pedals back to the neutral position.

AM. Horizontal Stabilzer Position Test

S 715-371-003

(1) Make sure the horizontial stabilizer trim control system is operational (AMM 27-41-00/501).

S 865-372-003


S 865-373-003 (3) Set the stabilizer to the 0 trim position.


S 865-378-003 (4) Set the stabilizer to the 14 trim position.


S 865-374-003 (5) Set the stabilizer back to the normal position.

AN. Captain's Manual Stab Trim Test

S 865-260-003

(1) Make sure the horizontal stabilizer trim control system operates correctly (AMM 27-41-00/501).

S 735-261-003



EFFECTIVITY



S 735-262-003 (3) On the captain's control wheel, set the trim switch to the down position.

(a) On the tester display, make sure the BIT(DISCRETE) 2 shows a 1.

S 865-263-003 (4) Release the trim switch on the control wheel.


S 735-264-003 (5) On the captain's control wheel, set the trim switch to the up position.


S 865-265-003 (6) Release the trim switch on the control wheel.


AO. Automatic/Manual Electrical Pitch Trim Test

S 865-266-003 (1) Make sure the horzontal stabilizer trim control system operates correctly (AMM

27-41-00/501).

S 865-267-003 (2) On the tester, set the SUBFRAME to 0 and the WORD 46.

S 865-268-003

(3) On the control wheel, set the control wheel trim switch to the NOSE DOWN position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 735-269-003

(4) Release the control wheel trim switch. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 1.

S 865-417-003

(5) On the tester, set the WORD to 41.

S 735-271-003 (6) On the control wheel, set the control wheel trim switch to the NOSE UP


S 735-272-003

(7) Release the control wheel trim switch. (a) On the tester display, make sure the BIT (DISCRETET) 2 shows a 1.

AP. Flap Alternate Test

S 715-273-003

(1) Make sure the trailing edge flap operates correctly (AMM 27-51-00/501).

S 865-274-003 (2) On the P3-1 panel, push the T.E. FLAP arm switch to the armed position.


EFFECTIVITY





S 735-276-003 (4) On the P3-1 panel, push the TE FLAP arm switch to the disarmed position.


AQ. Slat Alternate Test

S 865-277-003 (1) On the P3-1 panel, set the LE flap arm switch to the armed position.

S 735-278-003


S 735-279-003

(3) Set the LE flap switch to the disarmed position. (a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 0.

AR. Flap Handle Position Test

S 865-280-003

(1) Make sure the flap handle operates correctly (AMM 27-51-00/501).

S 865-281-003 (2) Make sure the flap handle is set at the 0 (UP) position.

S 735-282-003


S 735-283-003

(4) Set the flap handle to 15. (a) Make sure the tester display shows between 4426 and 5156.

S 865-284-003

(5) Set the flap handle back to the normal position.

AS. Leading Edge Slat Position Test

S 865-285-003 (1) Make sure the leading edge slat system operates correctly (AMM 27-81-00/501).

S 865-286-003

WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE

THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(2) Pressurize the left hydraulic system and reservoir (AMM 29-11-00/201).

S 865-287-003



EFFECTIVITY



S 735-288-003 (4) Set the LE slats to the full extended position.


S 735-289-003 (5) Set the LE slats to the not fully extended position.



S 735-291-003

(7) Set the LE slats to the partial extended position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 1.

S 735-292-003

(8) Set the LE slats to the not partial extended position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.

S 865-293-003


S 735-294-003 (10) Set the LE slats to the retracted position.


S 735-295-003 (11) Set the LE slats to the not retracted position.


S 865-296-003 (12) Set the LE slats back to the normal position.

S 865-297-003

(13) Remove the power from the left hydraulic system (AMM 29-11-00/201).

AT. Left and Right VHF Test

S 865-298-003 (1) Make sure the VHF communication systems operate correctly (AMM 23-12-00/501).

S 865-299-003

(2) Tune the VHF transceivers to an approved test frequency.

NOTE: Key only one transceiver at a time.



S 865-301-003 (4) On the captain's audio selector panel, push the L VHF MIC switch.

S 735-302-003

(5) Push the PTT switch on the captain's or first officer's control wheel. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.


EFFECTIVITY



S 865-303-003 (6) Release the PTT switch.


S 865-304-003 (7) On the captain's audio selector panel, push the R VHF MIC switch.

S 735-305-003

(8) Push the PTT switch on the control wheel. (a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 0.

S 865-306-003

(9) Release the PTT switch.

AU. Center VHF Test

S 735-419-003 (1) On the tester, set the WORD to 6.

(a) Make sure the BIT (DISCRETE) 1 shows a 1

S 865-308-003 (2) On the captain's audio selector panel, push the C VHF MIC switch.

S 735-309-003

(3) Push PTT switch on the captain's or first officer's control wheel. (a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 0.

S 865-310-003

(4) Release the PTT switch.

AV. Left HF Test

S 865-311-003 (1) Make sure the HF communication systems operates correctly (AMM 23-11-00/501).

S 865-312-003

(2) Tune the left HF transceiver to an approved test frequency.



S 865-314-003 (4) On the captain's audio selector panel, push the L HF MIC switch.

S 735-315-003

(5) Push the PTT switch on the captain's control wheel. (a) Make sure the BIT (DISCRETE) 2 shows a 0.

S 865-316-003

(6) Release the PTT switch. (a) Make sure the BIT (DISCRETE) 1 shows a 1.

S 865-317-003

(7) On the captain's audio selector panel, push the R HF MIC switch.


EFFECTIVITY



S 735-318-003 (8) Push the PTT switch on the captain's control wheel.


S 865-319-003 (9) Release the PTT switch.

AW. Ground Proximity Warning System Test

S 865-320-003

(1) Make sure the ground proximity warning system operates correctly (AMM 34-46-00/501).

S 735-321-003


S 735-322-003

(3) Set the test switch on the miscellaneous test panel to the GND PROX position. (a) Make sure the GLIDESLOPE lamp illuminates.

(b) On the tester display, make sure the BIT (DISCRETE) 8 shows a 1.

S 865-323-003

(4) Set the ground proximity warning system back to normal.

AX. Stick Shaker Test

S 865-324-003 (1) Make sure the stall warning system operates correctly (AMM 27-32-00/501).

NOTE: If the Hydraulic Power is used, the STALL TEST will also start the

auto slat if the flaps are in the takeoff range and slats are sealed.



S 735-326-003 (3) Set the L STALL switch on miscellaneous test panel to the TEST position.


S 735-327-003 (4) Release L STALL TEST switch on the miscellaneous test panel.


S 735-328-003 (5) Set the R STALL switch on miscellaneous test panel to the TEST position.


S 865-329-003 (6) Release the R STALL switch on the miscellaneous test panel.

S 865-330-003

(7) Set the stall warning system back to normal.


EFFECTIVITY



AY. Air/Ground Test

S 865-331-003 WARNING: PREPARE THE SAFETY-SENSITIVE SYSTEMS FOR THE AIR MODE BEFORE YOU OPEN THE

AIR/GROUND CIRCUIT BREAKERS. IN THE AIR MODE, MANY OF THE AIRPLANE SYSTEMS CAN OPERATE AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(1) Do the deactivation procedure for flight mode simulation (AMM 32-09-02/201).

S 865-332-003

(2) Open the circuit breaker: (a) On the P11 panel:

1) 11S19, AIR/GND SYS 2




(a) On the P11 panel: 1) 11S19, AIR/GND SYS 2

(b) Make sure the BIT (DISCRETE) 1 shows a 1.

AZ. Accelerometer Test

S 865-335-003

(1) On the tester, set the SUBFRAME and WORD as shown in the table that follows.

S 735-336-003 (2) Make sure the tester display shows the correct data as shown in the table that

follows:

SIGNAL TESTER SETUP

TESTER DISPLAY SUBFRAME WORD

VERTICAL 0 2 3442 to 3706

LATERAL 0 35 4000 to 4243

LONGITUDINAL 0 33 4000 to 4243

BB. Put the Airplane Back to its Usual Condition

S 865-337-003

(1) If you used the HHDLU, do the steps that follow: (a) Set the function switch on the flight recorder control panel to the NORM

position.

(b) Push the red button on top of the HHDLU.


EFFECTIVITY



(c) Remove the HHDLU adapter cable from the flight data recorder.

(d) Install the test plug to the test connector at the flight data recorder.

S 865-338-003 (2) If you used test equipment other than the HHDLU, do the steps that follow:

(a) Turn the tester off.

(b) Open these P11 panel circuit breakers: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC

(c) Disconnect the tester from the right side of the P61 panel.

(d) Install the test plug to the test connector at the P61 panel.

(e) Close these P11 panel circuit breakers:


S 865-339-003

(3) Remove electrical power if it is not necessary (AMM 24-22-00/201).


EFFECTIVITY



FLIGHT DATA RECORDER – MAINTENANCE PRACTICES 1. General

A. Use the applicable copy recorder to make a copy of the flight data recorder (FDR) data.

B. The FDR is installed in the voice and flight recorder rack, E7.

TASK 31-31-01-912-322

2. Make a Copy of the Flight Data with a Sundstrand Held Download Unit

A. General

(1) This task uses a hand held download unit (HHDLU) to make a copy of the flight data from a flight data recorder that records on solid state.

(2) You can use the HHDLU to make a copy of the flight data without the removal of

the solid state flight data recorder (FDR) from the airplane. A different procedure to access the flight data is to remove the FDR from the airplane (AMM 31-31-01/401). The flight data is then removed from the FDR.

(3) The ATE connector is on the front of the FDR.

B. Equipment

(1) 964-0446-001 Unit - Hand Held Download

97896 Honeywell International Inc. 15001 NE 36TH ST. P.O. Box 97001 Redmond, WA 98052-5317

(a) AIRPLANES WITH FDR P/N 980-4700-042;

The HHDLU must have mod 1 completed.

C. References

(1) AMM 24-22-00/201, Electrical Power - Control (2) AMM 25-22-02/401, Lower Ceiling Panel

D. Access

(1) Location Zone

253 Area Above Passenger Cable Ceiling, LH

E. Prepare to Make a Copy of the Flight Data from the FDR

S 862-224



EFFECTIVITY



S 862-183 (2) Open these circuit breakers and attach DO-NOT-CLOSE tags:

(a) On the overhead equipment panel, P11:


S 012-233

(3) To get access to the FDR, lower the ceiling panel No. 1 above the aft galley (AMM 25-22-02/401).

S 422-226

(4) Connect the connector of the HHDLU cable to the FDR ATE connector.

S 422-227 (5) Install the removable media into the HHDLU.

S 862-184


(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC

S 862-185

(7) At the P61 panel, set the ON-NORM-TEST switch on the flight recorder control panel (FRCP) to the ON position.

S 862-186

(8) Push the power switch, installed adjacent to the HHDLU's RS-422 port.

NOTE: When power is first applied to the HHDLU, the HHDLU display will not be on. After approxiamtely 30 seconds. The HHDLU display will show the main menu.

(a) Make sure the HHDLU display shows DNLD in the main menu.

F. Procedure

S 912-187

(1) Push the DNLD key.

(a) Make sure the DOWNLOAD MENU shows on the display.

NOTE: The maximum quantity of flight data the HHDLU can make a copy of is 27.2 hrs. If file DOWNLOAD01.DLU already exists on the removable media, the HHDLU will change the filename until a filename that is not used is found. To change the time or filename, push the TIME or FILE key.


EFFECTIVITY



S 862-228 (2) Push the GO key.

(a) If the HHDLU display shows DISK FULL, do these steps:

1) Push a key. 2) Make sure the DELETE FILE menu shows on the display. 3) Use the NEXT or PREV key to move up and down the filenames.

4) Push the DEL key to make a selection of the file to be erased.

a) Make sure the CONFIRM DELETE menu shows on the display.

5) Push the YES key to erase the file.

6) Erase files until sufficient memory is available to make a copy of the

flight data.

NOTE: After each file is erased, the HHDLU makes sure the HHDLU has sufficient memory space. If there is sufficient memory, the HHDLU will start to make a copy.

7) Make sure the HHDLU display shows REC BLKS and XFER BLKS.

NOTE: REC BLKS is the number of blocks the HHDLU will move to the

removable media. XFER BLKS is the number of blocks the HHDLU will move from the FDR. The REC BLKS and XFER BLKS fields will change during the copy procedure.

(b) After the copy procedure is completed, push a key to show the main menu.

G. Put the Airplane to Its Usual Condition

S 862-267

(1) On the HHDLU, push the red power switch to remove the power.

S 022-266 (2) Remove the media from the HHDLU.

S 862-229

(3) At the P61 panel, set the FRCP to the NORM position.

S 862-230 (4) Disconnect the interface cable from the FDR.

S 862-231

(5) Put the cover on the FDR ATE connector.

S 862-232 (6) Remove electrical power if it is not necessary (AMM 24-22-00/201).


EFFECTIVITY

31-31-99 AIRPLANES WITH AVIONICA MINI QAR Page 201 AERODEC MOD 1042 APR 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

31-31-99 AIRPLANES WITH AVIONICA MINI QAR Page 202 AERODEC MOD 1042 APR 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.


EFFECTIVITY



DATA PRINTER - DESCRIPTION AND OPERATION 1. General

A. The Data Printer is a general purpose airborne message, thermal line printer designed specifically for commercial aircraft.

B. The Data Printer contains a power supply, stepper motor, controller module, print drive

module, selector light module, and stationary thermal printer head to produce prints.

C. Data Printer meets the specifications of ARINC 740 to include the following capabilities:

• Interfaces with up to 12 ARINC 429 subsystems using prioritized polling • Variable print formats - 40, 64, 80, 80 sideways • Up to 80 characters per line and 7 lines per inch • Multiple print characters sets available (32K byte font memory) • Supports paper width of 4.375 inches, 100 feet per roll • Print rate of 120 40-character lines per minute

D. Data Printer receives power from the left 115v ac bus. The system circuit breaker is on the

overhead panel, P11. 2. Component Details (Fig. 1)

A. Data Printer

(1) The Data Printer is a single Line Replaceable Unit (LRU) designed to fit standard flight deck instrument rails.

(2) All Data Printer processing and control is performed by a single plug in circuit board,

the controller module. The controller contains a 32K byte EPROM in which the operational software and character fonts are individually partitioned. Print messages are buffered in two RAMs, which provide data protection from power interrupts by retaining data for up to two minutes upon power interruption. Fault diagnostic is provided by a single digit hexadecimal display, viewed when the paper access panel is open.

(3) The printer drive module contains all the circuitry for interfacing the print head

mechanism as well as the high current drivers for the print head and stepper motor.

(4) The stepper motor supplies the mechanical drive to advance the paper during printing operations or paper feeding operations.

(5) The sensor light module is a reflective object sensor which deactivates the print head

when there is no paper left on the spindle, preventing print head damage.

(6) Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.

B. Operation

(1) Data Printer is off when 115v ac left bus power is removed.

(2) Message Printing:

(a) Print message priority is determined by port number allocation, port #1 has the highest priority. Print message polling is defined by ARING 740.

(b) When a message has finished printing, the Data Printer will automatically advance

the paper outside the printer.


EFFECTIVITY



Data Printer - Location Figure 1

FLIGHT COMPARTMENT

PRINTER


EFFECTIVITY



(c) A message being printed will always be completed before polling for subsequent messages.

(d) Dual blades allow for two-way paper tear for print removal.

(3) Data Printer Switch/Indicator:

(a) SLEW switch - depress to advance paper.

(b) TEST switch - performs a functional BITE test and generates a print out of a

graphic test pattern and fault diagnostics messages.

(c) ALERT RESET switch - reset the printer's alert relay contacts (not applicable to this installation).

(d) MSG annunciator - illuminates to indicate receipt of a message. Depress the RESET

button to extinguish the annunciator.

(e) PAPER Indicator - illuminates when the printer is out of paper.

(f) FAIL Indicator - illuminates when a fault is detected by the BITE test.

(g) PAPER FULL/EMPTY Indicator - mechanical indicator which shows the amount of paper loaded in the printer.


EFFECTIVITY



DATA PRINTER – PAPER ROLL REPLACEMENT 1. General

A. This procedure contains the task to replace the paper roll in the Data Printer.

B. Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.

C. The Data Printer is installed on the P8 Aft Electronic Control Panel.

2. Data Printer - Paper Roll Replacement

A. Access

(1) Location Zones


B. Procedure


(a) P11-1 Overhead Circuit Breaker: 1) PRINTER

(2) Paper Roll Replacement (Figure 1):

(a) On the face of the Data Printer, turn the thumbscrew counterclockwise to release the

front panel.

(b) Open the front panel to the 180° position.

(c) Release the hinged paper roll spindle by pushing to the right and pulling straight out to the full 90° position. Remove the empty paper roll.

(d) Load new paper roll onto the spindle with the end of the paper facing towards the

printer.

(e) Close the spindle with the paper roll and lock into place by pushing to the right.

(f) Thread the end of the paper through the guide (drag) bar as indicated by the arrows until end of paper extends under the finger bar and rest on the platen roller. Continue to thread the paper out of the paper cutter slot at the bottom of the front panel.

(g) Close the front panel and secure with the thumbscrew.



1) PRINTER

(4) Depress the Data Printer SLEW switch. Ensure the paper feeds though the print head

properly.


EFFECTIVITY



Data Printer – Paper Roll Replacement Figure 1


EFFECTIVITY



(5) Do a Data Printer Operational Test per AMM 31-33-00/501.

C. Put the Airplane back to its Initial Condition



EFFECTIVITY



DATA PRINTER -ADJUSTMENT/TEST 1. General

A. There are two tasks in this procedure. The first task is the operational test of the Data Printer. The second is the system test of the Data Printer.

B. The operational test is a self-test of the Data Printer.

C. The system test contains the operational test and checks the interface between the Data

Printer and ACARS. 2. Data Printer Operational Test

A. References


B. Access

(1) Location Zones


C. Prepare for the Operational Test

(1) Supply electrical power (AMM 24-22-00/201 ).



1) ACARS 2) PRINTER

D. Procedure

(1) Data Printer Self-Test:

(a) On the front panel of the Data Printer, depress the TEST button.

(b) The Data Printer outputs a graphical test pattern (printer fonts) and no fault code

messages.

E. Put the Airplane back to the Initial Condition

(1) Remove electrical power (AMM 24-22-00/201) 3. Data Printer System Test

A. References

(1) 24-22-00/201, Electrical Power - Control (2) 23-22-00/501, ACARS

B. Access

(1) Location Zones


C. Prepare for the System Test.



EFFECTIVITY





1) ACARS 2) PRINTER

D. Procedure

(1) Data Printer Self-Test:

(a) On the front panel of the Data Printer, depress the TEST button.

(b) The Data Printer outputs a graphical test pattern (printer fonts) and no fault code

messages.

(2) Dlink+ ACARS/PRINTER Interface Test:

(a) At the P8 aft electronic panel, on the Dlink+ ACARS Unit, locate the maintenance menu by navigating thru the unit's menu selection.

(b) From the Dlink+ ACARS menu screen, select Line Select Key (LSK) adjacent to the

MISC or MAINT menu option as required to access the maintenance menu pages.

(c) From the ACARS MISC or MAINT screen page B, depress the Line Select Key (LSK) adjacent to PRINTER TEST.

(d) From the PRINTER TEST screen, select the Line Select Key (LSK) adjacent to the

PRINT prompt and verify that the data printer prints the information selected on the Dlink+ ACARS screen.

(e) Return the Dlink+ ACARS display to the main menu page.

E. Put the Airplane back to its Initial Condition



EFFECTIVITY



DATA PRINTER - REMOVAL/INSTALLATION

1. General

A. There are two tasks in this procedure. The first task is the removal of Data Printer. The second task is the installation of the Data Printer. The installation task includes an operational test of the Data Printer.

B. The Data Printer is installed on the P8 Aft Electronic Control Panel.

2. Data Printer - Removal

A. Access

(1) Location Zones


B. Procedure



1) PRINTER

(2) Remove the Data Printer:

a) Loosen the four quarter-turn fasteners that attach the Data Print to the panel.

b) Lift the Data Printer to get access to the electrical connector.

c) Disconnect the electrical connector.

d) Put a protective cover on the electrical connector. 3. Data Printer - Installation

A. References


B. Access

(1) Location Zones


C. Procedure



1) PRINTER

(2) Install the Data Printer:


(b) Examine the electrical connector for bent or broken pins, dirt, and damage.



EFFECTIVITY



(d) Put the Data Printer in its position on the PS Aft Electronic Control Panel.

(e) Tighten the four quarter-turn fasteners.



1) PRINTER

(4) Do a Data Printer System Test per AMM 31-33-00/501.

CHAPTER

34 NAVIGATION


EFFECTIVITY

34-22-00 239 Page 501 AERODEC MOD-1038 APR 01/16


ELECTRONIC FLIGHT INSTRUMENT SYSTEM - ADJUSTMENT/TEST 1. General

A. This procedure has two tasks, to carry out a left and Right EFIS Test, and a Center EFIS Symbol Generator 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. Left and Right EFIS Test A. Procedure

(1) Carry out the Left and Right EFIS Test in accordance with 34-22-00 Page Block 501.

(2) Make sure that the Hex Codes displayed on the EADIs are as follows:

UPPER CODE MIDDLE CODE LOWER CODE

00101F4 801C008 E080000

3. Center EFIS Symbol Generator Test A. Procedure

(1) Carry out the Center EFIS Symbol Generator Test in accordance with 34-22-00 Page Block 501.

(2) Make sure that the Hex Codes displayed on the EADI is as follows:

UPPER CODE MIDDLE CODE LOWER CODE

00101F4 801C008 E080000


EFFECTIVITY



GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST 1. General

A. This procedure has three tasks:

(1) To carry out a Level 1 Self Test of the Enhanced Ground Proximity Warning System.

(2) To carry out a Level 2 Self Test of the Enhanced Ground Proximity Warning

System. (3) To carry out a Level 3 Self Test of the Enhanced Ground Proximity Warning

System.

B. Any other test associated with the Ground Proximity Warning System in accordance with 34-46-00 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. Level 1 Self Test A. Procedure

(1) Carry out the Level 1 Self Test in accordance with 34-46-00 Page Block 501.

(2) Make sure that the following Altitude Callouts are enunciated over the

Flight Deck Audio System:

ALTITUDE CALLOUT

MINIMUMS

1000

500

100

50

40

30

20

10


EFFECTIVITY





(2) Make sure that the following Altitude Callouts are enunciated over the


ALTITUDE CALLOUT

CURRENT FAULTS

NO FAULTS

PRESS TO CONTINUE



(2) Make sure that the following Altitude Callout is enunciated over the


ALTITUDE CALLOUT

ALTITUDE CALLOUT MENU 91


EFFECTIVITY



AIR TRAFFIC CONTROL (ATC) SYSTEM - ADJUSTMENT/TEST 1. General

A. This procedure has two tasks:

(1) To carry out a system test of the Left Mode S ATC Transponder System (2) To carry out a system test of the Right Mode S ATC Transponder System

B. Any other test associated with the Air Traffic Control System in accordance

with 34-53-00 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. Left Mode S ATC Transponder System A. Procedure

(1) Carry out a system test of the Left Mode S ATC Transponder System in accordance with 34-53-00 Page Block 501.

(2) Make sure that the Mode S ATC Transponder Address Code is as follows:

AIRCRAFT REGISTRATION

SERIAL NUMBER HEXADECIMAL

CODE OCTAL CODE

OO-TFA 25622 44D0C1 21150301

3. Right Mode S ATC Transponder System A. Procedure

(1) Carry out a system test of the Right Mode S ATC Transponder System in accordance with 34-53-00 Page Block 501.

(2) Make sure that the Mode S ATC Transponder Address Code is as follows:

AIRCRAFT REGISTRATION

SERIAL NUMBER HEXADECIMAL

CODE OCTAL CODE

OO-TFA 25622 44D0C1 21150301


EFFECTIVITY



GPS ANTENNA - REMOVAL/INSTALLATION 1. General

A. This procedure has two tasks. The first task is the removal of a GPS antenna. The second task is the installation of a GPS antenna.

B. For the purposes of the 365 Aerospace modification referenced below; the GPS antenna is

installed at station 690 2. GPS Antenna Removal (Fig. 401)

A. Equipment

(1) Sealant removal tool - hardwood or plastic

B. Access

(1) Location Zones

107 Forward Half of Cabin, Right

C. Removal Procedure

(1) Open this circuit breaker on the overhead circuit breaker panel and attach DO-NOT-CLOSE tags:

(a) C9002, GPS

(2) Remove the GPS antenna:

CAUTION: BE CAREFUL WHEN YOU USE THE SEALANT REMOVAL TOOL TO BREAK THE SEAL. TOO MUCH

FORCE CAN CAUSE DAMAGE TO THE AIRPLANE SKIN, THE COAXIAL CABLE, OR THE ANTENNA.

(a) Use the sealant removal tool to break the seal all around the antenna.

(b) Remove the sealant that covers the antenna screws.

(c) Remove the antenna screws. CAUTION: MOVE THE ANTENNA THE LEAST DISTANCE NECESSARY TO DISCONNECT THE CONNECTOR.

DAMAGE TO THE CABLE CAN OCCUR IF YOU PULL THE CABLE WITH TOO MUCH FORCE.

(d) Carefully pull the antenna until you can get access to the connector.

(e) Disconnect the connector.

NOTE: Make sure the cable and connector do not fall into the airplane fuselage.

(f) Remove the GPS antenna.


EFFECTIVITY



Global Positioning System Antenna Installation Figure 401


EFFECTIVITY



3. GPS Antenna Installation (Fig. 401).

A. Equipment

(1) Resistance measuring bridge or ohmmeter (2) Spatula - fillet smoothing tool, hardwood or plastic

B. Consumable Materials

(1) A00145 Sealant - BMS 5-95, Class B-2 (2) B00184 Solvent - BMS 11-7 (3) C00175 Primer - BMS 10-79, Type III (4) C00855 Alodine (5) D00254 Grease - Silicone - Dow Corning 4 - SAE AS8660 (6) G00033 Woven Cheesecloth - BMS 15-5 (7) G00009 Corrosion Inhibiting Compound - BMS 3-27 (Preferred) (8) C50056 Compound - Non-drying Corrosion Inhibiting Resin Mix, BMS 3-38 (Alternate) (9) G50136 Paste - Corrosion Inhibiting Non-drying, BMS 3-38 (Alternate) (10) G50237 Compound - Corrosion Inhibiting Non-drying Cor-Ban 27L, BMS 3-38 (Alternate)

C. References

(1) AMM 20-10-22/701, Metal Surfaces (2) AMM 24-22-00/201, Manual Control (3) AMM 51-21-04/701, Alodine Coating (4) AMM 51-31-01/201, Seals and Sealing

D. Access

(1) Location Zones

107 Forward Half of Cabin, Right

E. Installation Procedure

(1) Open this circuit breaker on the overhead circuit breaker panel and attach DO-NOT-CLOSE tags:

(a) C9002, GPS

(2) Clean the airplane skin and the inner antenna surface with the solvent, BMS 11-7 (AMM

20-10-22/701).

(3) If there is corrosion on the airplane skin below the antenna, prepare the airplane skin as follows:

(a) Remove the corrosion (AMM 20-10-22/701).

(b) Clean the airplane skin in the area of the corrosion with the solvent, BMS 11-7

(AMM 20-10-22/701).

(c) Apply a layer of alodine on the airplane skin in the area where the antenna touches the skin (AMM 51-21-04/701).

(d) On top of the alodine, apply two layers of the BMS 10-79 Type III primer.

NOTE: Let each layer dry for the correct cure time.

(4) Apply a layer of the BMS 3-27 (preferred) or BMS 3-38 (alternate) corrosion inhibiting

compound in the screw holes and in the coaxial cable hole.


EFFECTIVITY



(5) Install the gel gasket, making sure it is aligned with the screw holes, and gently bring the coaxial cable through the hole in the middle of the gasket.

(6) Apply a layer of the BMS 3-27 (preferred) or BMS 3-38 (alternate) corrosion inhibiting

compound on the threads and shank of the antenna screws.

(7) Install the GPS antenna.

(a) Connect the electrical connector to the antenna.

(b) Apply a large quantity of Dow Corning 4 grease, D00254, to the outside coaxial connector, and at the exterior connector/antenna interface.

(c) Put the antenna into its position on the airplane.

(d) Install three of the bolts that hold the antenna.

NOTE: For GPS antenna connectors with hex nuts, make sure the bolts are tightened

to 8 to 12 in-lbs. For the coaxial connector that does not have hex nuts, these bolts are installed manually. Do not use power or pneumatic tools to install these bolts.

(8) Do a check of the resistance between the antenna and the airplane skin as follows:

(a) Connect the ohmmeter between the base of the antenna and the airplane skin.

NOTE: Get access to the base of the antenna through the hole for the last screw.

1) Make sure the measured resistance is 0.025 ohms or less.

(9) Install the last screw that holds the antenna.

(10) Remove the unwanted BMS 3-27 corrosion inhibiting compound from around the head of each

screw with the BMS 11-7 solvent (AMM 20-10-22/701).

(11) Apply the aerodynamic seal as follows (AMM 51-31-01/201):

(a) Apply the BMS 5-95 sealant around the antenna where it touches the airplane skin.

NOTE: Make sure no air bubbles are in the sealant. Use a sufficient quantity of the sealant to make the surface smooth.

(b) Make an aerodynamic fillet seal with the fillet smoothing spatula.

(c) Remove all the unwanted BMS 5-95 sealant from the area around the antenna.

(d) Fill the screw holes with the BMS 5-95 sealant.

NOTE: Make the sealant smooth in relation to the antenna surface.

F. GPS Antenna Installation Test


(2) Remove the DO-NOT-CLOSE tags on the overhead circuit breaker panel and close this

circuit breakers:

(a) C9002, GPS

(3) Move the airplane to a position where the GPS antennas have a clear view of the GPS satellites.

(4) Set the FMC source select switch to the NORMAL position.


EFFECTIVITY



(5) Do these steps to see the GPS position output:

(a) Push the INIT REF key on one of the DLINK+ ACARS Unit.

(b) Push the line select key (LSK) that is adjacent to <INDEX.

(c) Push the LSK that is adjacent to <POS.

(d) Push the NEXT PAGE key on the DLINK+ ACARS Unit two (2) times.

1) Make sure the GPS is shown on a line of the DLINK+ ACARS Unit display.

G. Put The Airplane Back to Its Usual Condition

(1) Remove electrical power if it is not necessary (AMM 24-22-00/201).

Documents

AIRCRAFT MANUAL SUPPLEMENT · MOD-1040 SELCAL Code Change AERODEC MOD-1041 Mode S Code Change AERODEC MOD-1042 Introduction of Mini QAR AERODEC MOD-1043 Installation of a Hot Jug