Document No. AMS-737-345-28881 AIRCRAFT MANUAL … · 2017-06-16 · Document No. AMS-737-345-28881 Produced by Aerospace Design and Engineering Consultants (AeroDEC ®) Limited,

Document No. AMS-737-345-28881

AIRCRAFT MANUAL

SUPPLEMENT To comply with EASA Regulation CS-25.1529 and CS-25 Appendix H and FAA Regulation CDR 14 25.1529 and to support the continued airworthiness of:

B737-300/400/500 – MSN 28881 Document No: AMS-737-345-28881

Intro Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.

®


Produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. AeroDEC own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.

®

HIGHLIGHTS Issue 3 COMPLETE RE-ISSUE OF MANUAL SUPPLEMENT Issue 4 WDM – 23-24-11 – ADDED AMM – 25-11-11 – ADDED, 34-22-00 – ADDED Issue 5 AMM – 23-24-00 – AMENDED AMM – 23-24-11 – AMENDED AMM – 34-22-00 – AMENDED Issue 6 Wiring Diagram Manual 22-11-75 – Added Aircraft Maintenance Manual 22-11-01 – Added Issue 7 Aircraft Maintenance Manual 23-71-00 - Changed Issue 8 Wiring Diagram Manual 25-33-58 – Added Illustrated Parts Catalogue 25-31-11-99Z - Added Aircraft Maintenance Manual 23-24-00 THRU 23-24-11 Changed



®

RECORD OF REVISION

Issue DIN No. Date Issue DIN No. Date Initial DIN-0166 JUL 01/06

2 DIN-0494 MAR 01/07 3 DIN-2279 FEB 01/11 4 DIN-2289 MAR 01/11 5 DIN-2358 APR 01/11 6 DIN-2761 JAN 01/12 7 DIN-3606 APR 01/13 8 DIN-3888 SEP 01/13

The Aircraft Manual Supplement (AMS) is to be used in conjunction with the related aircraft’s manuals. The information contained within this manual relates to various alterations/changes/modifications that have been carried out on the associated aircraft. A list of effective alterations/changes/modifications can be found in the Introduction pages to this manual. These alterations/changes/modifications are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related convention. This manual complies with EASA Regulations CS-25.1529 and CS-25 Appendix H, which in turn mirror the FAA regulation CDR 14 25.1529. DINs are Document Issue Notes and are administration documents used to issue this manual to the customer and are used for record purposes only.

RRA-00 Page 1



®

INTRODUCTION

1. General A. This publication was prepared by Aerospace Design and Engineering Consultants (AeroDEC®) Ltd and is in accordance with

Air Transport Association of America Specification No. 100, Specification for Manufacturers Technical Data. The data contained within is related to certain changes/modifications/alterations that are in addition to the associated airplane’s type design.

NOTE: THIS MANUAL IS PREPARED SPECIFICALLY TO COVER THE AIRPLANE LISTED IN THE "INTRODUCTION"

SECTION, FOR THE OWNER/OPERATOR NAMED ON THE TITLE PAGE.

THIS MANUAL IS NOT SUITABLE FOR USE, INCLUDING WITHOUT LIMITATION, GENERAL INSTRUCTIONS OR TRAINING, FOR ANY AIRPLANES NOT LISTED HEREIN.

B. The convention for the use of this publication is in the same convention (ATA 100) as the associated manufacturers AMM,

WDM, and IPC. Therefore, this publication is a SUPPLEMENT to the associated AMM, WDM, and IPC, and instructions on how to use this manual are equivalent to the instructions on how to use the manufacturers AMM, WDM and IPC.

C. This Manual Supplement has been raised to give historic design information pertaining to the following related aircraft

manuals: WDM – Wiring Diagram Manual

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

CUSTASSIGNED AIRPLANE

IDENT

B737-49R 001 PV301 2833 28881

INTRO-00 Page 1 SEP 01/13



®

LIST OF EFFECTIVE PAGES

Description Page No. Date Description Page No. Date

Front Page IPC Front Page Highlights IPC Contents 1 Record of Revision and Approval 1 IPC Contents 2 Introduction 1 SEP 01/13 Chapter 23 Front Page Introduction 2 SEP 01/13 23-24-00-01Z 0 FEB 01/11 List of Effective Pages 1 SEP 01/13 23-24-00-01Z 1 FEB 01/11 List of Effective Pages 2 SEP 01/13 23-24-00-02Z 0 FEB 01/11 Report/Feedback Sheet 23-24-00-02Z 1 FEB 01/11 WDM Front Page 23-24-00-03Z 0 FEB 01/11 WDM Contents 1 23-24-00-03Z 1 FEB 01/11 WDM Contents 2 23-71-13-01Z 0 FEB 01/11 Chapter 22 Front Page 23-71-13-01Z 1 FEB 01/11 22-11-52 1 FEB 01/11 Chapter 25 Front Page 22-11-62 1 FEB 01/11 25-11-11-18Z 0 FEB 01/11 22-11-75 1 JAN 01/12 25-11-11-18Z 1 FEB 01/11 Chapter 23 Front Page 25-11-11-66Z 0 FEB 01/11 23-22-01 1 FEB 01/11 25-11-11-66Z 1 FEB 01/11 23-24-11 1 MAR 01/11 25-11-21-22Z 0 FEB 01/11 23-71-01 1 Sht 1 FEB 01/11 25-11-21-22Z 1 FEB 01/11 23-71-01 1 Sht 2 FEB 01/11 25-31-11-07Z 0 FEB 01/11 Chapter 25 Front Page 25-31-11-07Z 1 FEB 01/11 25-33-58 113 Sht 6 SEP 01/13 25-31-11-07Z 2 FEB 01/11 25-33-58 113 Sht 7 SEP 01/13 25-31-11-07Z 3 FEB 01/11 Chapter 31 Front Page 25-31-11-07Z 4 FEB 01/11 31-31-01 1 FEB 01/11 25-31-11-99Z 0 SEP 01/13 Chapter 33 Front Page 25-31-11-99Z 1 SEP 01/13 33-17-01 1 FEB 01/11 25-31-21-04Z 0 FEB 01/11 Chapter 34 Front Page 25-31-21-04Z 1 FEB 01/11 34-22-11 1 FEB 01/11 25-31-21-04Z 2 FEB 01/11 34-22-21 1 FEB 01/11 25-31-41-07Z 0 FEB 01/11 34-26-11 1 FEB 01/11 25-31-41-07Z 1 FEB 01/11 34-26-13 1 FEB 01/11 25-31-41-07Z 2 FEB 01/11 34-26-21 1 FEB 01/11 Chapter 31 Front Page 34-26-23 1 FEB 01/11 31-24-24-99Z 0 FEB 01/11 34-49-04 1 FEB 01/11 31-24-24-99Z 1 FEB 01/11 34-53-12 1 FEB 01/11 Chapter 33 Front Page 34-53-16 1 FEB 01/11 33-11-00-05Z 0 FEB 01/11 34-53-22 1 FEB 01/11 33-11-00-05Z 1 FEB 01/11 34-61-02 1 FEB 01/11 Chapter 34 Front Page 34-61-11 1 FEB 01/11 34-28-31-02Z 0 FEB 01/11 Chapter 49 Front Page 34-28-31-02Z 1 FEB 01/11 49-31-12 1 FEB 01/11 34-53-21-01B 0 FEB 01/11 Wire List (WL) 34-53-21-01B 1 FEB 01/11 Index Chapter 35 Front Page W0007 1 FEB 01/11 35-12-00-02Z 0 FEB 01/11 W0009 1 FEB 01/11 35-12-00-02Z 1 FEB 01/11 W0011 1 FEB 01/11 35-12-00-02Z 2 FEB 01/11 W0069 1 FEB 01/11 35-12-00-20Z 0 FEB 01/11 W0967 1 FEB 01/11 35-12-00-20Z 1 FEB 01/11 W9001 1 FEB 01/11 Chapter 49 Front Page W9002 1 FEB 01/11 49-70-00-02Z 0 FEB 01/11 W9076 1 FEB 01/11 49-70-00-02Z 1 FEB 01/11

LEF-00 Page 1 SEP 01/13



®

LIST OF EFFECTIVE PAGES

Description Page No. Date Description Page No. Date

Chapter 53 Front Page 34-53-02 5 FEB 01/11 53-42-00-80Z 0 FEB 01/11 34-53-02 6 FEB 01/11 53-42-00-80Z 1 FEB 01/11 34-53-02 7 FEB 01/11 53-42-00-81Z 0 FEB 01/11 34-53-02 8 FEB 01/11 53-42-00-81Z 1 FEB 01/11 34-53-02 9 FEB 01/11 AMM Front Page 34-53-02 501 FEB 01/11 AMM Contents 1 34-53-02 502 FEB 01/11 AMM Contents 2 34-53-02 503 FEB 01/11 Chapter 22 Front Page 34-53-02 504 FEB 01/11 22-11-01 501 JAN 01/12 34-53-02 505 FEB 01/11 22-11-01 502 JAN 01/12 34-53-02 506 FEB 01/11 Chapter 23 Front Page 34-53-02 507 FEB 01/11 23-24-00 1 SEP 01/13 34-53-02 508 FEB 01/11 23-24-00 101 SEP 01/13 34-53-02 509 FEB 01/11 23-24-00 201 SEP 01/13 34-62-01 501 FEB 01/11 23-24-00 501 SEP 01/13 34-62-01 502 FEB 01/11 23-24-11 401 SEP 01/13 34-62-01 503 FEB 01/11 23-71-00 501 APR 01/13 Chapter 49 Front Page 23-71-00 502 APR 01/13 49-72-11 401 FEB 01/11 23-71-00 503 APR 01/13 49-72-11 402 FEB 01/11 23-71-00 504 APR 01/13 49-72-11 403 FEB 01/11 23-71-00 505 APR 01/13 49-72-11 404 FEB 01/11 23-71-00 506 APR 01/13 49-72-11 405 FEB 01/11 23-71-00 507 APR 01/13 Chapter 25 Front Page 25-11-11 201 MAR 01/11 25-11-11 202 MAR 01/11 25-11-11 203 MAR 01/11 25-11-11 204 MAR 01/11 25-11-11 205 MAR 01/11 25-11-11 206 MAR 01/11 25-11-11 207 MAR 01/11 25-11-11 208 MAR 01/11 25-11-11 209 MAR 01/11 25-11-11 210 MAR 01/11 25-11-11 211 MAR 01/11 25-11-11 212 MAR 01/11 Chapter 31 Front Page 31-24-24 201 FEB 01/11 31-24-24 202 FEB 01/11 Chapter 34 Front Page 34-22-00 501 APR 01/11 34-22-00 502 APR 01/11 34-49-03 501 FEB 01/11 34-49-03 502 FEB 01/11 34-53-02 1 FEB 01/11 34-53-02 2 FEB 01/11 34-53-02 3 FEB 01/11 34-53-02 4 FEB 01/11

LEF-00 Page 2 SEP 01/13



®

REPORT/FEEDBACK SHEET

This Report/Feedback Sheet is provided for the purpose of communicating to Aerospace Design and Engineering Consultants (AeroDEC) Ltd. any errors or suggested improvements arising fro this Aircraft Manual Supplement

AMS Section: Applicants Name:ATA Ref(s): Applicants Signature: Date:(Please provide details below):

FEEDBACK ONLY (Please provide details below):

WIRING

DIAGRAM

MANUAL

Contents

WDM-CONTENTS Page 1


®

Chapter 11 PLACARD & MARKINGS

Chapter 21 AIR CONDITIONING

Chapter 22 AUTO FLIGHT

22-11-52 – DFCS “A” MCP/FCC INTERFACE

22-11-62 – DFCS “B” MCP/FCC INTERFACE

22-11-75 – DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS

Chapter 23 COMMUNICATIONS

23-22-01 – SELCAL

23-24-11 – EMERGENCY LOCATOR TRANSMITTER

23-71-01 – COCKPIT VOICE RECORDER

Chapter 24 ELECTRICAL POWER

Chapter 25 EQUIPMENT/FURNISHINGS

25-33-58 – DRIESSEN AIRCRAFT SYSTEMS CMM P/N 101719 PAGE 113 SHEET 6

25-33-58 – DRIESSEN AIRCRAFT SYSTEMS CMM P/N 101719 PAGE 113 SHEET 7

Chapter 26 FIRE PROTECTION

Chapter 27 FLIGHT CONTROLS

Chapter 28 FUEL

Chapter 29 HYDRAULIC POWER

Chapter 30 ICE AND RAIN PROTECTION

Chapter 31 INDICATING/RECORDING SYSTEMS

31-31-01 – DFDRS INTERCONNECT GROUP 1

Chapter 32 LANDING GEAR

Chapter 33 LIGHTS

33-17-01 – MAP, FLIGHT KIT, AND READING LIGHTS

Chapter 34 NAVIGATION

34-22-11 – EFIS POWER/PROGRAM PIN - LEFT

34-22-21 – EFIS POWER/PROGRAM PIN - RIGHT

34-26-11 – INERTIAL REFERENCE SYSTEM NO.1 POWER

34-26-13 – INERTIAL REFERENCE NO.1 OUTPUT BUSSES

34-26-21 – INERTIAL REFERENCE SYSTEM NO.2 POWER

34-26-23 – INERTIAL REFERENCE NO.2 OUTPUT BUSSES

34-49-04 – GROUND PROXIMITY WARNING

34-53-12 – ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING

WDM-CONTENTS Page 2


®

34-53-16 – NO.1 AND NO.2 ATC ENHANCED SURVEILLANCE BUSSES

34-53-22 – ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING

34-61-02 – FLIGHT MANAGEMENT COMPUTER SYSTEM DATA BUS AND CONTROL

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

Chapter 35 OXYGEN

Chapter 36 PNEUMATIC

Chapter 38 WATER/WASTE

Chapter 49 AIRBORNE AUXILIARY POWER

49-31-12– APU – MANUAL START-STOP

Chapter 52 DOORS

Chapter 53 FUSELAGE

Chapter 54 NACELLES / PYLONS

Chapter 55 STABILIZERS

Chapter 56 WINDOWS

Chapter 57 WINGS

Chapter 71 POWER PLANT

Chapter 73 ENGINE FUEL AND CONTROL

Chapter 74 IGNITION

Chapter 75 AIR

Chapter 77 ENGINE INDICATING

Chapter 78 EXHAUST

Chapter 79 OIL

Chapter 80 STARTING

Chapter 91 CHARTS

Chapter 93 PANELS

CHAPTER

AUTO FLIGHT

B737-300/400/500 WIRING DIAGRAM MANUAL

PV301

DFCS “A” MCP/FCC INTERFACE 22-11-52 INCORPORATES: 22-11-52 AERODEC MOD 0090

Page 1 Page 1

FEB 01/11 FEB 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.


PV301

DFCS “B” MCP/FCC INTERFACE 22-11-62 INCORPORATES: 22-11-62 AERODEC MOD 0090

Page 1 Page 1



PV301

DFCS CROSS REFERENCES AND CONFIGURATION PIN OPTIONS

22-11-75 INCORPORATES: 22-11-75 AERODEC MOD 1093

Page 1 Page 1

JAN 01/12 JAN 01/12 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

M924FLIGHT CONTROL COMPUTER "A"

W011

W011−737−20

D1671A

2

18

19

26

STD OPT ILS DEVN WARN

25

BIT 1

22

D1795A

D1795B

44

61

STD OPT ALT ALERT

CONFIG PINS

G/S SUPERFLAG

2

D1671B

28

30

32

35

44

62

27

29

33

42

57

BIT 2

STD OPT AIRSPEED WARNSTD OPT CWS WARN

STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO

STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL

STD OPT ODD PARITYSTD OPT EFIS

STD OPT DUAL CHANNELAUTO F/D TOGA

LOC BEFORE G/S

6

7

LVOR/LOC DEVN

R

10

11

BDATA BUS IRU−L−3

A

12

34

20

FRN IRS XFR−A

FMC/ANCDU SELAFDS WARN

43

67

51

R/A FLAG

NAV SELF TESTILS TEST INHIBIT

D1791A

DNG/S DEVN

UP

LORADIO ALTITUDE

HI

1

1

6

7

58


A

9

D1791B

8 BDATA BUS FMC−1

A

26

D1793A

25 BDATA BUS DAA−L−2

A

54 DME HOLD

D1793B

67 26V AC IN LNAV REF

2

6

LOLNAV STRG CMD

HI

30

34

35

36

39

42

51

52

LVOR/LOC DEVN

R

VOR/LOC SUPERFLAG

1ADI BAR GRADIENT

2AUTO/MANUAL TUNE

ADATA BUS ANCDU−1

B

FWD LOC ANTENNA SELECT

LOCAL IRS XFR

D4317P

1

J

3

5

7

9

11

14

16

13

2

4

6

8

12

15

17

Z9

Z4

Z3

XA1

XD5

XA5

E1−3 SHELF

W069

34−31−05

34−33−11

34−31−08

34−26−13

34−31−04

34−26−23

34−33−11

34−31−09

34−61−02

34−61−05

34−31−04

34−26−12

34−31−08

34−26−12

34−31−08

34−31−01

NOT USED

NOT USED

NOT USED

NOT USED

NOT USED

GDX22−DC

GDX22−DC

GD701−DC

GD701−DC

GD701−DC

T1015STA 314.5WL 182.5LBL 19.2

P7 GLARESHIELD PANEL

M198DFCS MODE CONTROL PANEL

27

D1815

26

29

34−31−11

49

31

50

30

51

27

D299

34−31−11

26

29

30

31

49

50

51

15

1433−11−31

D301

6LCD TEST 33−18−05

RESOLVER

GND

5V ACLIGHTING

731−20

738−20

725−20

729−20

727−20

730−20

753−20

726−20

735−20

733−20

796−20

736−20

732−20

734−20

728−20

W011−739−20

W011−013−20

W011−003−20

3110

NOTES:UNLESS OTHERWISE SPECIFIED, ALL REFERENCE DESIGNATIONS ARE PREFIXED 3343−.UNLESS OTHERWISE SPECIFIED, ALL WAYCODES ARE W9.PIN LOCATIONS SUFFIXED BY (−) DENOTES LOWER CASE LETTERS.THE FOLLOWING ENGINEERING DRAWINGS WERE USED: 83340200/T/2, 83340204/A/2, 82430054/G/4 AND AL344−1264.INDICATES PROTECTIVE TUBING.

W737−071−22

072−22

075−22

074−22

073−22

076−22

077−22

078−22

079−22

080−22

081−22

082−22

084−22

085−22

086−22

087−22

W737−083−22

M923FLIGHT CONTROL COMPUTER "B"

W069−557−20

D1655A

2

D1661A

D1661B

44

61

G/S SUPERFLAG

2

D1655B

6

7

LVOR/LOC DEVN

R

10

11


A

12

34

20

FRN IRS XFR−B

FMC/ANCDU SELAFDS WARN

43

67

51

R/A FLAG

NAV SELF TESTILS TEST INHIBIT

D1657A

DNG/S DEVN

UP

LORADIO ALTITUDE

HI

1

1

6

7

58

BDATA BUS IRU−R−2

A

9

D1657B

8BDATA BUS FMC−1

A

26

D1657A

25BDATA BUS DAA−R−2

A

54DME HOLD

D1657B

6726V AC IN LNAV REF

2

6

LOLNAV STRG CMD

HI

30

34

35

36

39

42

51

52

LVOR/LOC DEVN

R

VOR/LOC SUPERFLAG

1ADI BAR GRADIENT

2AUTO/MANUAL TUNE

ADATA BUS ANCDU−2

B

FWD LOC ANTENNA SELECT

LOCAL IRS XFR

D4117P

32

J

34

36

38

40

42

45

47

44

33

35

37

39

43

46

48

34−31−05

34−33−21

34−31−08

34−26−23

34−31−04

34−26−13

34−33−21

34−31−09

34−61−02

34−61−06

34−31−04

34−26−12

34−31−08

34−26−12

34−31−08

34−31−01

NOT USED

NOT USED

NOT USED

NOT USED

NOT USED

GDX6−DC

GDX6−DC

541−20

539−20

535−20

548−20

537−20

540−20

511−20

536−20

545−20

524−20

554−20

542−20

544−20

538−20

549−20

W069−560−20

W011−011−20

W011−009−20

41

W373−032−22

033−22

036−22

035−22

034−22

037−22

038−22

039−22

040−22

041−22

042−22

043−22

045−22

046−22

047−22

048−22

W373−044−22

W737−061−20

W737−062−20

W737−063−20

XB1

XA2

XC2

XB5

Z9

Z4

Z3

XA1

XD5

XA5

GD701−DC

GD701−DC

GD701−DC

T1017STA 314.5WL 182.5LBL 19.2

W737−061−20

062−20

W373−063−20

XB1

XA2

XC2

XB5

18

19

26

STD OPT ILS DEVN WARN

25

BIT 1

22

STD OPT ALT ALERT

CONFIG PINS

28

30

32

35

44

62

27

29

33

42

57

BIT 2

STD OPT AIRSPEED WARNSTD OPT CWS WARN

STD OPT CWS OVERRIDESTD OPT FAA OR CAA VMO/MMO

STD OPT F/D TOGASTD OPT HDG SEL/WINGS LEVEL

STD OPT ODD PARITYSTD OPT EFIS

STD OPT DUAL CHANNELAUTO F/D TOGA

LOC BEFORE G/S

31

CHAPTER

COMMUNICATIONS


PV301

SELCAL 23-22-01 INCORPORATES: 23-22-01 AERODEC MOD 0935

Page 1 Page 1



PV301

EMERGENCY LOCATOR TRANSMITTER 23-24-11 INCORPORATES: 23-24-11 AERODEC MOD 0889

Page 1 Page 1

MAR 01/11 MAR 01/11 Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.


PV301

COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0916

Page 1 Page 1 Sheet 1 Sheet 1


AG

M S

ER

VIC

ES

DR

AW

ING

: A

GM

10-

B7

3W-0

138


PV301

COCKPIT VOICE RECORDER 23-71-01 INCORPORATES: 23-71-01 AERODEC MOD 0916

Page 1 Page 1 Sheet 2 Sheet 2


AG

M S

ER

VIC

ES

DR

AW

ING

: A

GM

10-

B7

3W-0

138

CHAPTER

EQUIPMENT/

FURNISHINGS


PV301

DREISSEN AIRCRAFT SYSTEMS COMPONENTS MAINTENANCE MANUAL

P/N 101719

25-33-58 INCORPORATES: 25-33-58 AERODEC MOD 1022 Page 113 Page 113

Sheet 6 of 9 Sheet 6 of 9 SEP 01/13 SEP 01/13

Page produced by Aerospace Design and Engineering Consultants (AeroDEC®) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

D

A001 8

C

B

A

C003 8

B002 8

N004 8 4

3

2

1 A006 8

C008 8

B007 8

N012 10

C044 8

B030 8

2

L2

3

F

C

B

A

D

E

G

P8

1

2

3

3

5

8

4

67

GND

B036 20

B037 20

B038 20

B039 20B040 20

B041 20

3

5

8

GND

4

67

B1 L1

A/C POWERINTERFACE

MS6029−4S−4TERMINAL COVER

P1 TB1

−9 (−101 MOD 001 & −301 MOD 001 ONLY)

5

6

7

N042 16

N032 20

N043 20

N033 20

3

B1 B2

CB4

A1 A2

CB2

B1 B2

C1 C2

F

C

B

A

D

E

G

J8

4

3

2

1

6

5

4

3

2

1

6

5

J4

SP1

C1 C2

5

3

2

1

J3

S2

53

WORK LIGHT

C

A/C GND

CASE GND

COPPER STRAP

3

LIGHT ASSY(DRIESSEN)

239002−21

S1

1A 5

2

64

3

1

BONDINGPLATE

A/C GNDINTERFACE

COPPER STRAP

COFFEEMAKERSUMP

PLUMBING

WORKCOUNTER

AC GND

115 VAC C

115 VAC B

115 VAC A PHASE A

PHASE B

PHASE C

AC NEUTRAL

CASE GROUND

CASE GROUND

COFFEEMAKER64753−001−003RAIL ASSY64759−151

HOT CUPDLH545−017DRIESSEN

MAKERCOFFEE

GNDELECTRICALPANEL

CB3HOT CUP

7.5A

BRT

DIM

OFF

4

2

3

15

S3

2

L2

6

4

3

BRT

DIM

1 OFF

AREA LIGHTING

1

3

10A C023 16

B022 16

A021 16

S025 16

S027 16

N024 14

S090 10

S026 10

C093 16

B092 16

A091 16

S095 16

N094 16

S096 16

C045 20 C047 16

C046 16

S048 16

S049 10

D50 22

D51 22

D53 22

D52 22

N033 20

B034 20

N035 20

B031 20

N032 20

B030 8

S029 12

S028 12

S005 8 S009 8

S010 8

3

4

CASE GND

AC GROUND

5 STATIC GROUND TO BRACKET, PANEL OR TO SHELL OF INSERT

A1 A2

CB9001HOT JUG

4 A A9001 20 25−33−58 SHEET 7A9004 10

Note: This Drawing relates to Sheet 6 of 9, of Dreissen CMM 25-33-58 for P/No. 101719


PV301

DREISSEN AIRCRAFT SYSTEMS COMPONENTS MAINTENANCE MANUAL

P/N 101719

25-33-58 INCORPORATES: 25-33-58 AERODEC MOD 1022 Page 113 Page 113

Sheet 7 of 9 Sheet 7 of 9 SEP 01/13 SEP 01/13


Note: This Drawing relates to Sheet 7 of 9, of Dreissen CMM 25-33-58 for P/No. 101719

2

16

5

7

6

32

115 VAC

CASE GND

6

J5

S055 16

B101 16

C400 16

B401 16

A402 16

DCN058 20

S084 10

3

4

CASE GND

AC GROUND

3

1

21

25

31

10

9

8

13

14

15

26

28

30

29

115 VAC

HEATER

FAN

NTRL

DC +

DC −

DC +

LOW

HIGH

MED

DC −

DC059 20

DC060 20

DC061 20

DC062 20

A063 16

B064 16

C065 16

A066 16

D067 16

C068 16

DCN057 20

DC056 20

N103 16

4

1

5

16

14

DC −

P6

3

2

18

20

22

24

21

23

25

6

7S073 20

S072 20

N071 20

N070 20

N069 20

C

A PHASE

P7

B079 20

D

B

T1

4

3

2

1

TB2

5

6

4

3

2

1

TB1

5

6

7

SP2

SP3

SP4

B1 B2

CB5DC CONTROL

1A

SP4COPPER

STRAP

NEUTRAL

− DC

+ 28 VDC

TRANSFORMERRECTIFIER

N080 20

5S083 15COPPER

STRAP

3

3

COPPERSTRAP

3

CNTL BOX FORTEMPERATURESELECTION

28 VDC

HEATINGELEMENTS

PHASE A

PHASE B

PHASE C

FANMOTOR

PHASE A

PHASE B

PHASE C

AC NEUTRAL

CASE GND

CASE GND

OVEN #2RUMBOLD67063

OVENCONTROLLERRUMBOLD64213−001−001

C

B

A

C

B

A

C

B

A

A

B

C

7

COPPERSTRAP

3

A100 16

C102 16

B078 8

N017 8

C016 14

B015 14

A014 14

B081 20

25−33−58 SHEET 6

S076 10

−9 (−101 MOD 001 & −301 MOD 001 ONLY)

5 STATIC GROUND TO BRACKET, PANEL OR TO SHELL OF INSERT

6 CAP AND STOW AND ALLOW ADEQUATE LENGTH TO CONNECT TO CIRCUIT BREAKER

3

2

1

A9001 20

COPPERSTRAP

3

HOT JUGJF003001DRIESSEN

S9003 18

A9001 20

N9002 18

CHAPTER

INDICATING/ RECORDING

SYSTEM


PV301

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

Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

454

P18−2

4

8

13

2.5

C109 FLT REC AC

12115V AC

ELEX PWR−1 24−58−11

053−22

2.5

C468

1228V DC

BATT. BUS24−58−11

W089−110−22

2.5

C544 POS SENSORS

1226V AC XFR

NO.224−58−11

127−22

W029

D4100PJ

D4397PJ

D4395PJ

8

W089−199−22FLT REC DC

ELECTRONIC LOAD CIRCUIT BREAKER PANEL

P18 LOAD CONTROL CENTRE − LEFT

STA 254DISC.

W105−008−22

W109−013−22

W047−032−22

W047−033−22

7

W047

1

D8945JP

STA 178DISC.

2

SM4 516−22

517−22

515−2210

11518−22

W419−001−22

008−22

005−22

20519−22 020−24

23058−22 023−24

22035−22 022−24

9252−24B 220−22B

4T230

18

11

251−24R 219−22R

15520−24 007−242

12 015−24NOT USED

8

32254−24B

253−24R 31

34

33

35

14 014−24NOT USED

228−24B

227−24R

225−24R

226−24B

25

26

28

29

30

221−24R

222−24B

223−24R

224−24B

27

NOT USED

4 213−24R

214−24B5

3

6

D483

034−22

19

20

23

22

P5−19 FLIGHT RCRDR AND MACH AIRSPEED PNL

P5 OVERHEAD PANEL

5

3

2

1

FLT RCDRTEST SWITCH

L1 FLIGHT RECORDER LIGHT

1

4

3

2

33−18−04

33−18−04

33−18−16

030−22

W419−003−24

M9009 MICRO QARD1637

1

2

11

3

5

4

9

8

10

6 W419−9001−20

W419−010−20 GD128−DC

A

A

PD8987J

1

2

3

4

5

7

8

9

6

10

11

13

14

15

12

17

18

19

20

PD5955J

3

PD4101J

3 501−22

502−24

503−24

504−24

505−24

W017

522−24

519−24

508−24

633−24R

633−24B

607−24R

608−24B

601−24R

602−24B

619−24R

620−24B

SM536 014−22

013−22

31−31−31

SM503

SM504

31−31−35

518−24

512−24 1

D2295C

7

H

C

115V AC

M675 DIGITAL FLIGHT DATA

513−20GDX22−AC

16 16

J9

D2295A

K9

A

B

DFDR PLAY OUT

10

182−22GDX21−S

G9

H9

A

B

G11

H11

A

B

FDEP DATA IN

180−22GDX21−S

A11

D2295A

A9

B9

A

B

BITE OUT

DIGITAL INPUT

609−24R

610−24B

SM534

SM535

SM533

625−24R

626−24B

J11

K11

A

B

PLAYBACK IN

611−24R

612−24B

183−22 GDX21−S

B11MAINT FLAG

J15DIGITAL GND

K15ANALOGUE GND

515−24

516−22

517−22 GDX23−DC

D2295E

J15

D2295D

K15

DIGITAL GND

CHASSIS GND

H1

510−22

511−22GDX23−DC

H2

A

B

ACARS DATA IN

H3

H4

A

B

ACARS DATA OUT

23−27−12

ACQUISITION UNIT

FDEP DATA OUT

21

22

24

26

27

25

28

29

SM545 509−24

R263 FDAUD1805

X2

X1

A2

A3

STATUS RLY

514−24

520−22GDX23−DC

507−24 SM539

31−31−03

A1

506−24

D1805062−24 SM517

31−31−52

31−31−55

23

W419−021−22

019−22

209−24R

210−24B

215−22R

216−22B

017−20

E2−2 ELECTRONIC SHELF

21

D8987JP D183AM96 DIGITAL FLIGHT

STATUS

22 MAINT FLAG

GD815−S

9

10

A

B

PLAYBACK

7

8

A

B

DIGITAL INPUT

011−22 23 28V DC

029−22 1 115V AC H

002−20 2 115V AC L

6 CHASSIS GNDW419−006−20

GD391−AC

GD393−DC

28

D8997JP

27

E3−2 ELECTRONIC SHELF

M528 ENG ACC UNIT

D1458A

41

28

ENG NO. 1

D1458B

41

28

ENG NO. 2

8361−24

8362−24

8359−24

8360−24 SM160

SM162

8327−24

8328−24

8363−24

8364−24

27

D8909JP

28

24

D5212JP

5

W409−027−24

W409−028−24

W2016−017−24

W2016−054−24

32

33

D2596

GND

A3

A2

A1

AIR

E11 LDG GEAR LOGIC SHELF

R277 GND SENSINGRELAY

DATA RECORDER

31−31−51

181−22GDX21−S

CHAPTER

LIGHTS


PV301

MAP, FLIGHT KIT, AND READING LIGHTS


Page 1 Page 1


CHAPTER

NAVIGATION


PV301

EFIS POWER/PROGRAM PIN - LEFT 34-22-11 INCORPORATES: 34-22-11 AERODEC MOD 0861

Page 1 Page 1



PV301

EFIS POWER/PROGRAM PIN - RIGHT 34-22-21 INCORPORATES: 34-22-21 AERODEC MOD 0861

Page 1 Page 1



PV301

INERTIAL REFERENCE SYSTEM NO.1 POWER


Page 1 Page 1


34-21-01

24-58-11NO.1 PWR28V DC

(MP)D2161B

POSITION MOUNT 1EXTENDED MAGVAR MAPMAGVAR MAP OLD/NEWPOSITION MOUNT 2PROG COMMON

SDI CODE

IRU-1M1161

011-22010-22009-22013-22012-22014-22

001-20002-20005-16004-12003-12

NOT USED

NOT USED

A2K9K3A3A1A6A5

W833

SM1

025-22

008-22007-22006-22

024-22

MSTR TEST IN

24-58-11STBY PWR115V AC

24-58-11STBY PWR BUS

28V DC

36

27

25

SP4007

SM30

23

26

24

33-18-12

ON DC

DC FAIL

INPUTSDISCRETE

CH18

CH

C1011

C1029

C1007

C1013

C1009

23

24

25

D4001J P

14

16

D4151J P

4

61151

SDI

GDX16-AC

D2165C

40

(BP)

1

1187

51

GDX5-DCGDX6-SGDX4-AC

D2161C(BP)

E11E10E12E13F2F1

D2161B(MP)

1 23

W029162-20

DAA/IRS 1 - AC

1 23 163-20DAA/FMC 1 - AC

1 2

IRS 1 - AC3

1 210DAA 1 - DC

1 210IRS 1 - DC

ANNUNCIATOR

PNL LTS

P18-2 CAPT ELEX SYS CIRCUIT BREAKER PANELP18 LOAD CONTROL CENTER - LEFT

069-22DIM CNTL

5V ACCOMM

M1M2

ALIGN

FAULT

MODE SELECT COMM

P5-69 MODE SELECTOR UNIT

P5 PILOTS OVERHEAD PANEL

15

17

1314

12

11181016

12

D2171

W047

33-18-05

33-12-01

DC FAIL

STA 285DISC.

1315

14201716

P D4327J

HC

28V DC INPUT

CHASSIS GNDCH115V AC INPUT

ON DC

M2M1DISCRETE IN

ISDU CONTROLALIGN

FAULT

W175-

E3-5 FWD ELECTRONIC SHELF

W101-040-20

041-20

W101-042-20

W089-

046-16

W175-047-12

W007177-20

176-20

174-20

175-16

173-14

178-20181-16180-20

115V AC IRS INPUT

FMC INPUT28V DC

CHASSIS GNDAC GND

FMC INPUT115V AC

M1163 DAA 1

34-26-14172-14 SM2

756234

D8323P J

166-2234-26-14

SM3

W127-013-22

014-22

015-22

016-22017-22

W127-

020-22

1315

14201716

D4017J P

165-22

170-22171-22167-22

168-22

169-22

E1-2 ELECTRONIC SHELF

164-20

W089-055-16

062-22

056-12

D2165A

D6

GDX10-DC 179-12

(TP)

C

W101-

2 13C1060 DAA/FMC 1 - DC

W089-057-16

H28V DC INPUT

545-16546-20

W175-048-16

810-22

1817151684921203

D2269

066-22067-22068-22

064-22

065-22

P10

405-22

406-22403-22

401-22402-22

404-22

SM8

SM9

SP332334-26-14

484-22481-22483-22482-22480-22485-22486-22

33-18-22

33-18-0233-18-05

W044

GD100B-DCGD100C-DC

M1206 MASTER CAUTION UNIT

MAXIMUM LENGTH 24 INCHES

PANEL

A/G LOGICON DC OUTPUT

FAULTDC FAIL

ON DC INPUTCHASSIS GND

DC GNDIRS WARNING

MASTER CAUTION RECALLMASTER TESTPOWER SUPPLY

P D4238J

DISCRETE

NOTES:

1

GROUND FROM ALL OTHER GROUNDS.SINGLE POINT GROUND. ISOLATE THIS

1

32

030-22GDX10-DC

78

40

STA 254DISC.

D4047PJ

4

2

6

D4393PJ

42

41

24-58-11BAT. BUSSW HOT28V DC

34-26-21

2

SM4007

D12

D13

C4C5

E4E5

J9K9

B12B13

2

2

2

2

GDX30-S

GDX30-S

GDX30-S

GDX30-S

747-22R

748-22B

741-22R742-22B

749-22R750-22B

753-22R754-22B

D2165B

C

C

HC

H

C

H

HC

H

EXCITATIONNAV

EXCITATIONATT-1

EXCITATIONATT-2

EXCITATIONHDG-4

EXCITATIONHDG-5

34-26-12

34-21-01


PV301

INERTIAL REFERENCE SYSTEM NO.1 OUTPUT BUSSES


Page 1 Page 1



PV301

INERTIAL REFERENCE SYSTEM NO.2 POWER


Page 1 Page 1


005-16004-12003-12

002-20

001-20

D2163C

EXTENDED MAGVAR MAPMAGVAR MAP OLD/NEW

28V DC SWITCHED INPUT PWR

IRU-2M1162

A2

W103-

M1206

6

4

2 14537-20

591-20

56

J

ON DC OUT

D4339P

18

047-12

DC FAIL

027-20

15

2

9478

111112

ELECTRONIC SHELF

D4337J

J

SP3957

SP3939

18

14

587-20

56

AIR/GROUND LOGIC

FAULTON DC IN

GDX7-AC

56

P

23

D2271

18

34-26-11

NOTES: 1GROUND FROM ALL OTHER GROUNDS.SINGLE POINT GROUND. ISOLATE THIS

163-20

161-20

586-20

538-20

046-20

W091-

D4401P

1

SM33

J

W091-

W103-

W03145

47

E1-3

060-12

044-20

K9

P10

F2

ON DC E11E12E10F1

E13

073-22072-22

144-22

W047

W383-

046-16

1016

047-20

J

162-20

P6-1 ELECTRONIC LOAD CIRCUIT BREAKER PANELP6 LOAD CONTROL CENTER - RIGHT

045-20

D4409P

585-20

194-16

195-12

8

MSTR TEST

DIM CNTL

W383-

ON DC

DC FAIL

FAULTM1M2

ALIGN

MODE SELECT-COMM

ANN

DISCRETE

P5-69

P5 OVERHEAD PANEL

33-18-05

33-18-12

457-22

142-22

070-22

W044

460-22

143-22

E3-5 FWD ELECTRONIC SHELF

115V AC INPUT

28V DC GNDCHASSIS GND

SDI

PROG COMMON

POSITION MOUNT NO.1

POSITION MOUNT NO.2

ALIGNM2M1

FAULTDC FAIL

D2163B

11

7

1

K3

A1

A6

009-22010-22011-22012-22013-22014-22

GDX1-AC

GDX2-DCGDX3-S

SM501

(MP)

20

SM501

171615

14

13

590-16

1

40

2

3

4

5

67

D4257J

D8325P

D5953J

539-20

198-16

J

P

P

46

W091-

W163-

D2167C

846-20

GDX8-AC

7

11

115V AC FMC INPUT

115V AC IRS INPUT

AC GND28V DC INPUT

DC GND

FMC AC GND INPUTCHASSIS GND

27

(BP)

(BP)

709-12

708-12W069-

D4193J

7

D4063P

P

W069-

(TP)

E1-2 ELECTRONIC SHELF

W00915

16

17

D4019J P

1

4

A2

34-26-14 W835

C

H

34-26-14

17

15

34

8244-20

W069-

D235B

15

17121314

11

D2173

071-22 SM18

SM19

SP3323

407-22

409-22408-22412-22

410-22

411-22

34-26-14

458-22

459-22

461-22

2024302926

13

14

15161720

STA 285DISC.

048-16

P D5981J

W467-013-22

014-22

015-22016-22017-22020-22W467-

802-22

801-22

803-22

804-22805-22806-22807-22

28V DC FMC INPUT

GND

MASTER CAUTION UNIT

16

845-16

3GDX24-DC

NOT USED

NOT USED

INPUTDISCRETE

P D4240J

STA 259DISC.

D235B

D235A

A2

A1

C1

X1

K8

A1

8248-20

735-20

8247-208246-20

8243-20

W011

M1474 INTEG FLT SYS ACCESS UNIT (TP)

X2

X1

DAA/FMC NO.2 DC

IRS NO.2 DC

DAA/FMC NO.2 AC

IRS NO.2 AC

C1010

C1014

C1061

C1008

DAA/IRS NO.2 AC

DAA NO.2 DC

C1012

2

2

21

1

2

1

C1030

1

1

1

10

10

3

3

2

23

3

24-58-21SWITCHEDHOT BAT. BUS28V DC

24-58-21ELEX BUS NO.2115V AC

24-58-21NO.2ELEX BUS115V AC

24-58-21ELEX BUS NO.228V DC

24-58-21NO.2ELEX BUS28V DC

31DS-3XDG

1

1

GDX3-S

1

1

1

GDX3-S

GDX3-S

GDX3-S

GDX3-S

C4

D12

1

SM510

721-22R722-22B

D2167A

719-22R720-22B

723-22R724-22B

725-22R726-22B

727-22R728-22B

729-22R730-22B

D2167B

C5

E4E5

A4A5

J9K9

C14C15

H

C

HC

H

C

H

C

H

C

H

C

EXCITATIONNAV

EXCITATIONATT-1

EXCITATIONATT-2

EXCITATIONHDG-3

EXCITATIONHDG-4

557-22

EXCITATIONATT-3

34-26-22

T/DELAY5 MIN

582-12

W069-597-20596-20

W069-

8225-20

GDX6-DC

SP400934-21-02

1

52

M1164

GDX16-DC

MODE SELECTOR UNIT

DAA 2

34-31-07

024-22

FIRST OBSERVERS PANEL

008-22

025-22K9

A5

A3

5

8

006-22007-22


PV301

INERTIAL REFERENCE SYSTEM NO.2 OUTPUT BUSSES


Page 1 Page 1



PV301

GROUND PROXIMTY WARNING 34-49-04 INCORPORATES: 34-49-04 AERODEC MOD 0865

Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

329

C8ALTITUDE CALLOUT ENABLE

B15PPCNF19 (WGS−84 GPS ALT REF SELECT)

D1153B

A3PPCOM (PROGRAMME PIN COMMON)

W021−501−24

W021−507−22

W9021−050−22

W021−515−24

GDX10−DC

SM1153

B10PPCNF2

A10PPCNF1

D1153A

W9021−047−22

W9021−048−22

W9021−076−24C10PPCNF3

W021−517−24

W021−518−24

AIRCRAFT TYPE SELECT

SP9012D6PPCNF17 (PROGRAMME PIN PARITY) W9021−055−22

B5PPCNF12 (WINDSHEAR CONTROL) W9021−069−22

C4PPCNF11 (AUDIO DECLUTTER / VOLUME / WGS−4)

W9021−054−22

W9021−053−22

W9021−049−22

W9021−052−22

SM50534−49−03

D4PPCNF4

B4PPCNF5

A8PPCNF6

ALTITUDE CALLOUT MENU

D1153B

D14PPCNF7 (OPTIONAL GPS / GPIRS)

C2PPCNF9 (2 ILS / 2 LRRA / 3 LRRA)

B5PPCNF13 (TCF DIS / TAD DIS / SIM REPO)

D15DOUTL1 (GLIDESLOPE CANCEL)

W9021−051−22 SP9009

C12DOUTL4 (WINDSHEAR CAUTION)

B12DOUTL 6 (AUDIO ON)

D1153A

C2PPCNF14 (BANK ANGLE)

W9021−058−22

W9021−077−22 SP9010

W9021−061−22

W9021−060−22

W9021−059−22 SP9013

W9021−079−22

M652 ENHANCED GROUND PROXIMITY COMPUTER

E2−4 SHELF

34−49−03

W021−704−24

34−45−02SM506

34−49−03

34−45−02

B737-300/400/500 AIRCRAFT WIRING MANUAL

PV301

ATC NO.1 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1


A

ER

OD

EC

DW

G: A

L345

-140

3

E3

D149B

875−24MODE S ADDRESS BIT COMMON

D3 874−24BIT 24

C3 873−24BIT 23

B3 872−24BIT 22

A3 871−24BIT 21

K2 870−24BIT 20

J2 869−24BIT 19

H2 868−24BIT 18

G2 867−24BIT 17

F2 866−24BIT 16

E2 865−24BIT 15

D2 864−24BIT 14

C2 863−24BIT 13

B2 862−24BIT 12

A2 861−24BIT 11

K1 860−24BIT 10

J1 859−24BIT 9

H1 858−24BIT 8

G1 857−24BIT 7

F1 856−24BIT 6

E1 855−24BIT 5

D1 854−24BIT 4

C1 853−24BIT 3

B1 852−24BIT 2

A1 851−24BIT 1

J5 850−24ANT BITE PROGRAM

MODE S ADDRESS

C5

D149A

877−24MAX TAS PROGRAMME

D5 876−24PROGRAMME COMMON

SM800

W017

M1469D2681

25

24

23

22

21

20

19

18

17

16

15

14

13

12

11

10

9

8

7

6

5

4

3

2

1

E2−2

1.

SHORTING RECEPTACLE

ELECTRONIC SHELF

M163 ATC−1 TRANSPONDER (MP)

(TP)

A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3

MODE S CODE

ADDRESS BIT

REGISTRY OCTAL

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24

AIRPLANE

D149B AND D2681

1.

OO−TNO 21150717PV301 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 0 1 1 11

1.NOTES:

FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D149B AND D2681


PV301

NO.1 AND NO.2 ATC ENHANCED SURVEILLANCE BUSSES


Page 1 Page 1



PV301

ATC NO.2 MODE S TRANSPONDER ADDRESS AND AIRSPEED CODING


Page 1 Page 1


AE

RO

DE

C D

WG

: AL3

45-1

403

E3

D155B

875−24MODE S ADDRESS BIT COMMON

D3 874−24BIT 24

C3 873−24BIT 23

B3 872−24BIT 22

A3 871−24BIT 21

K2 870−24BIT 20

J2 869−24BIT 19

H2 868−24BIT 18

G2 867−24BIT 17

F2 866−24BIT 16

E2 865−24BIT 15

D2 864−24BIT 14

C2 863−24BIT 13

B2 862−24BIT 12

A2 861−24BIT 11

K1 860−24BIT 10

J1 859−24BIT 9

H1 858−24BIT 8

G1 857−24BIT 7

F1 856−24BIT 6

E1 855−24BIT 5

D1 854−24BIT 4

C1 853−24BIT 3

B1 852−24BIT 2

A1 851−24BIT 1

J5 850−24ANT BITE PROGRAM

MODE S ADDRESS

C5

D155A

877−24MAX TAS PROGRAMME

D5 876−24PROGRAMME COMMON

SM800

W087

M1470D2683

25

24

23

22

21

20

19

18

17

16

15

14

13

12

11

10

9

8

7

6

5

4

3

2

1

E2−4

1.

SHORTING RECEPTACLE

ELECTRONIC SHELF

M381 ATC−2 TRANSPONDER (MP)

(TP)

A1 B1 C1 D1 E1 F1 G1 H1 J1 K1 A2 B2 C2 D2 E2 F2 G2 H2 K2 J2 A3 B3 C3 D3

MODE S CODE

ADDRESS BIT

REGISTRY OCTAL

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24

AIRPLANE

D155B AND D2683

1.

OO−TNO 21150717PV301 0 1 0 0 0 1 0 0 1 1 0 1 0 0 0 1 1 1 0 0 1 1 11

1.NOTES:

FOR EACH MODE S ADDRESS BIT DESIGNATED AS "1" CONNECT THE CORRESPONDING WIRE BETWEEN D155B AND D2683


PV301

FLIGHT MANAGEMENT COMPUTER SYSTEM DATA BUS AND CONTROL


Page 1 Page 1



PV301

FLIGHT MANAGEMENT COMPUTER SYSTEM PROGRAMME PINS


Page 1 Page 1


A

ER

OD

EC

DR

AW

ING

: A

L34

6-12

90

F11

E11

C11

D11

G11

H11

CAA FLT RULES

AIR FRAME / ENG CODE

C13

D10

F10

F12

F14

F15

G10

B13

H12

J10

K15

H10

C10

D2179BM1175 FMC NO.1

DEGGREES F DEFAULT

VOR INHIBIT

TAKEOFF SPEED

ASPIRATED TAT PROBE

PERFORMANCE OPTION

FLT NUMBER ENTRY

KILOGRAM OPTION

TAKEOFF PROFILE

RUNWAY POSITION UPDATE

NON AGILITY DME TYPE

NAV AID SUPPRESSION ON EFIS

SELECTED COURSE INHIBIT ON EFIS

8022−22

8021−22

8025−22

8026−22

8023−22

8024−22

8010−22

8002−22

8011−22

8012−22

8013−22

8014−22

8015−22

8016−22

8017−22

8018−22

8019−22

8007−22

8008−22

2

1

5

6

3

4

9

10

11

12

13

14

15

16

17

18

19

7

8

D6739P

E1−2 ELECTRONICS SHELF

J

W737−002−22

001−22

025−22

026−22

023−22

024−22

049−22

050−22

051−22

052−22

053−22

054−22

055−22

056−22

057−22

058−22

059−22

047−22

XB1

XA1

XC1

XC2

XB2

XA2

XA6

XB6

Z11

Z12

XA8

XC8

XD5

T1013STA 314.5LBL 19.2WL 182.5

W737−003−22WK

028−22WO GD127−S

W737−027−22WV

GD127−SW737−065−22

GD127−SW737−066−22

B10FAA / CAA QRH SPEEDS 8320−22 20 W737−020−22

048−22

XD8

W007

CHAPTER

AIRBORNE AUXILIARY

POWER


PV301

APU – MANUAL START-STOP 49-31-12 INCORPORATES: 49-31-12 AERODEC MOD 0949

Page 1 Page 1



®

WIRE

LIST

INDEX


WIRE LIST Section INDEX Page 1


®

SECTION PAGE NO. DATE SECTION PAGE NO. DATE

W0007 1 FEB 01/11 W0009 1 FEB 01/11 W0011 1 FEB 01/11 W0069 1 FEB 01/11 W0967 1 FEB 01/11 W9001 1 FEB 01/11 W9002 1 FEB 01/11 W9076 1 FEB 01/11


WIRE LIST

91-21-11 Section W0007

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0007 E1-2 ELECTRONIC SHELF PART A 9001 22 R 34-53-16 D9205P 20 SM12 PV301 0057 / 0090 9001 22 B 34-53-16 D9205P 21 SM13 PV301 0057 / 0090 9001 22 34-53-16 D9205P 22 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM14 PV301 0057 / 0090 9002 22 R 34-53-16 D9205P 23 SM131 PV301 0057 / 0090 9002 22 B 34-53-16 D9205P 24 SM132 PV301 0057 / 0090 9002 22 34-53-16 D9205P 25 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR SM8 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W0009

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0009 E1-2 ELECTRONIC SHELF PART B 9001 22 R 34-53-16 D9205P 29 SM517 PV301 0057 / 0090 9001 22 B 34-53-16 D9205P 30 SM518 PV301 0057 / 0090 9001 22 34-53-16 D9205P 31 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM519 PV301 0057 / 0090 9002 22 R 34-53-16 D9205P 26 SM131 PV301 0057 / 0090 9002 22 B 34-53-16 D9205P 27 SM132 PV301 0057 / 0090 9002 22 34-53-16 D9205P 28 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR SM8 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W0011

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0011 E1-3 AUTO PILOT SYSTEM A 9001 22 R 34-53-16 D5977P 50 SM128 PV301 0057 / 0090 9001 22 B 34-53-16 D5977P 51 SM129 PV301 0057 / 0090 9001 22 34-53-16 D5977P 52 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM130 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W0069

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0069 E1-3 AUTO PILOT SYSTEM B 9001 22 R 34-53-16 D5977P 53 SM612 PV301 0057 / 0090 9001 22 B 34-53-16 D5977P 54 SM613 PV301 0057 / 0090 9001 22 34-53-16 D5977P 55 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR SM614 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W0967

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W0967 ATC 1 E2-2 WIRING 9001 22 R 34-53-16 D9004P 11 D149A C2 PV301 0057 / 0090 9001 22 B 34-53-16 D9004P 12 D149A D2 PV301 0057 / 0090 9001 22 34-53-16 D9004P 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR GDX-14 PV301 0057 / 0090 9002 22 R 34-53-16 D9004P 14 D149A A6 PV301 0057 / 0090 9002 22 B 34-53-16 D9004P 15 D149A B6 PV301 0057 / 0090 9002 22 34-53-16 D9004P 16 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR GDX-14 PV301 0057 / 0090 9003 22 R 34-53-16 D9004P 17 D149A A7 PV301 0057 / 0090 9003 22 B 34-53-16 D9004P 18 D149A B7 PV301 0057 / 0090 9003 22 34-53-16 D9004P 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR GDX-14 PV301 0057 / 0090 9004 22 R 34-53-16 D9004P 8 D149A A2 PV301 0057 / 0090 9004 22 B 34-53-16 D9004P 9 D149A B2 PV301 0057 / 0090 9004 22 34-53-16 D9004P 10 9004 SCR PV301 0057 / 0090 9004 22 34-53-16 9004 SCR GDX-14 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W9001

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9001 E2-2 TO E1-2, E1-3 9001 22 R 34-53-16 D9004J 11 D9205J 20 PV301 0057 / 0090 9001 22 B 34-53-16 D9004J 12 D9205J 21 PV301 0057 / 0090 9001 22 34-53-16 D9004J 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR D9205J 22 PV301 0057 / 0090 9002 22 R 34-53-16 D9004J 14 D9205J 23 PV301 0057 / 0090 9002 22 B 34-53-16 D9004J 15 D9205J 24 PV301 0057 / 0090 9002 22 34-53-16 D9004J 16 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR D9205J 25 PV301 0057 / 0090 9003 22 R 34-53-16 D9004J 17 D5977J 50 PV301 0057 / 0090 9003 22 B 34-53-16 D9004J 18 D5977J 51 PV301 0057 / 0090 9003 22 34-53-16 D9004J 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR D5977J 52 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W9002

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9002 E2-4 TO E1-2, E1-3 9001 22 R 34-53-16 D9006J 11 D9205J 29 PV301 0057 / 0090 9001 22 B 34-53-16 D9006J 12 D9205J 30 PV301 0057 / 0090 9001 22 34-53-16 D9006J 13 9001 SCR PV301 0057 / 0090 9001 22 34-53-16 9001 SCR D9205J 31 PV301 0057 / 0090 9002 22 R 34-53-16 D9006J 8 D9205J 26 PV301 0057 / 0090 9002 22 B 34-53-16 D9006J 9 D9205J 27 PV301 0057 / 0090 9002 22 34-53-16 D9006J 10 9002 SCR PV301 0057 / 0090 9002 22 34-53-16 9002 SCR D9205J 28 PV301 0057 / 0090 9003 22 R 34-53-16 D9006J 17 D5977J 53 PV301 0057 / 0090 9003 22 B 34-53-16 D9006J 18 D5977J 54 PV301 0057 / 0090 9003 22 34-53-16 D9006J 19 9003 SCR PV301 0057 / 0090 9003 22 34-53-16 9003 SCR D5977J 55 PV301 0057 / 0090


WIRE LIST

91-21-11 Section W9076

Page 1 FEB 01/11

Bundle No. Part Number Description From To ADEC Info Wire No. GA CO TY Fam FT-IN Diagram Equip Term Type Splice Equip Term Type Splice Effectivity Mod No. W9076 ATC 2 E2-4 WIRING 9005 22 R 34-53-16 D9006P 17 D155A A7 PV301 0057 / 0090 9005 22 B 34-53-16 D9006P 18 D155A B7 PV301 0057 / 0090 9005 22 34-53-16 D9006P 19 9005 SCR PV301 0057 / 0090 9005 22 34-53-16 9005 SCR GDX-14 PV301 0057 / 0090 9006 22 R 34-53-16 D9006P 8 D155A A6 PV301 0057 / 0090 9006 22 B 34-53-16 D9006P 9 D155A B6 PV301 0057 / 0090 9006 22 34-53-16 D9006P 10 9006 SCR PV301 0057 / 0090 9006 22 34-53-16 9006 SCR GDX-14 PV301 0057 / 0090 9007 22 R 34-53-16 D9006P 11 D155A C2 PV301 0057 / 0090 9007 22 B 34-53-16 D9006P 12 D155A D2 PV301 0057 / 0090 9007 22 34-53-16 D9006P 13 9007 SCR PV301 0057 / 0090 9007 22 34-53-16 9007 SCR GDX-14 PV301 0057 / 0090 9008 22 R 34-53-16 D9006P 14 D155A A2 PV301 0057 / 0090 9008 22 B 34-53-16 D9006P 15 D155A B2 PV301 0057 / 0090 9008 22 34-53-16 D9006P 16 9008 SCR PV301 0057 / 0090 9008 22 34-53-16 9008 SCR GDX-14 PV301 0057 / 0090

ILLUSTRATED

PARTS

CATALOGUE

Contents

IPC-CONTENTS Page 1


®





23-24-00-01Z – MODULE INSTL – AFT OVERHEAD PANEL P5 (EMERGENCY LOCATOR TRANSMITTER ONLY)

23-24-00-02Z – TRANSMITTER INSTL – EMER LOCATOR (ELT)

23-24-00-03Z – ANTENNA INSTL – EMER LOCATOR (ELT)

23-71-13-01Z – MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY)



25-11-11-18Z – SEAT INSTL – SECOND OBSERVER

25-11-11-66Z – ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)

25-11-21-22Z – PANEL INSTL – LINING STA 261 TO STA 269

25-31-11-07Z – GALLEY INSTL – UNIT NO.1

25-31-11-99Z – HOT CUP INSTL – GALLEY 1

25-31-21-04Z – GALLEY INSTL – UNIT NO.2

25-31-41-07Z – GALLEY INSTL – UNIT NO.4B



Chapter 28 FUEL




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


Chapter 33 LIGHTS

33-11-00-05Z – LIGHT INSTL – CONT CAB CREW


34-28-31-02Z – EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY)

34-53-21-01B – EQUIPMENT INSTL – ELECT. RACKS (ATC TRANSPONDER ONLY)

IPC-CONTENTS Page 2


®

Chapter 35 OXYGEN

35-12-00-02Z – OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY)

35-12-00-20Z – OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY)




49-70-00-02Z – ENGINE ASSY – APU (INDICATING ONLY)

Chapter 52 DOORS

Chapter 53 FUSELAGE

53-42-00-80Z – ROD INSTL – NO.1 AND NO.4B GALLEY POSITION TIE

53-42-00-81Z – ROD INSTL – NO.2 GALLEY POSITION TIE



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

CHAPTER

COMMUNICATIONS

B737-300/400/500 ILLUSTRATED PARTS CATALOGUE

23-24-00-01Z 23-24-00 MOD 0889 Fig 1Z FEB 01/11 Page 0


MODULE INSTL – AFT OVERHEAD PNL P5 (EMERGENCY LOCATOR TRANSMITTER ONLY) Figure 1Z




FIG ITEM PART NUMBER NOMENCLATURE EFF

CODE UNITS PER

ASSY 1234567

1Z --1 AGM10-B73E-0063 INSTALLATION OF ARTEX C406-1 ELT 001001 RF

10 345-6196-04 • REMOTE SWITCH 1

-- ITEMS NOT ILLUSTRATED




TRANSMITTER INSTL – EMER LOCATOR (ELT) Figure 2Z





CODE UNITS PER

ASSY 1234567

2Z --1 AGM10-B73E-0063 ELT TRANSMITTER INSTALLATION 001001 RF --1 B737-ELT-1 KIT, ARTEX C406-1 ELT INSTALLATION

10 2-23501-302-01 • SUPPORT TRAY ASSY 1

--20 2-23501-302-03 • BRACKET 2--30 2-23501-302-04 • BRACKET 2--40 2-23501-302-05 • BRACKET 1--50 2-22566-302-01 • BUZZER BRACKET 1--60 2-21483-401-004 • PLACARD 1--70 MS27039-1-09 • SCREW 6--80 AN960-10L • WASHER 6--90 MS21042-3 • NUT 6--100 2-23501-301-09 • FILLER 1--110 2-23501-301-08 • FILLER 1120 453-5002-( ) • ELT XMTR 1

--130 455-4010-01 • ELT DONGLE 1--140 452-0133 • BATTERY PACK 1--150 130-4004 • BUZZER 1





ANTENNA INSTL – EMER LOCATOR (ELT) Figure 3Z





CODE UNITS PER

ASSY 1234567

3Z --1 AGM10-B73E-0063 ELT ANTENNA INSTALLATION 001001 RF --1 B737-ELT-1 KIT, ARTEX C406-1 ELT INSTALLATION

10 110-340 • ANTENNA – ELT 120 MS27039C-1-15 • SCREW 6

--30 2-23501-301-01 • CHANNEL 1--40 2-23501-301-02 • CLIP 4--50 2-23501-301-03 • CLIP 2--60 2-23501-301-04 • CLIP 2--70 2-23501-301-05 • CHANNEL 2--80 2-23501-301-06 • NUTPLATE 2--90 2-23501-301-07 • NUTPLATE 1--100 NAS1473A3 • NUT 6--110 2-21483-401-003 • PLACARD 1--120 2-23501-301-08 • FILLER 1--130 2-23501-301-09 • FILLER 1




Page produced by Aerospace Design and Engineering Consultants (AeroDEC) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.

MODULE INSTL – FWD OVERHEAD PNL P5 (VOICE RECORDER SYSTEM ONLY) Figure 1Z





CODE UNITS PER

ASSY 1234567

1Z --1 AGM10-B73E-0138 CVR SWITCH INSTALLATION 001001 RF

10 233A3211-1 • MODULE – COCKPIT VOICE RECORDER 1


CHAPTER

EQUIPMENT/

FURNISHINGS




SEAT INSTL – SECOND OBSERVER FIGURE 18Z





CODE UNITS PER

ASSY 1234567

18Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTALLATION 001001 RF

10 11-007-1 • SEAT ASSY 1--20 65-76688-3 • FILLER 1--30 69-43995-1 • LOOP STRAP 1--40 69-44684-1 • SHIM 1--50 65-46836-2 • VELCRO 1





ASHTRAY INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 66Z





CODE UNITS PER

ASSY 1234567

66Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTL 001001 RF

10 69-44447-2 • ASHTRAY ASSY 120 69-43944-1 • BRACKET ASSY 130 69-44458-3 • SUPPORT ASSY 140 BACS40R05C05F • SHIM - LAMINATED 250 26S55-5AB • STUD 2





PANEL INSTL – LINING STA 261 TO STA 269 FIGURE 22Z





CODE UNITS PER

ASSY 1234567

22Z --1 AGMIS10-B73E-0147 SECOND OBSERVER STATION INSTALLATION 001001 RF

10 69-45405-20 • PANEL – LINING 120 69-45405-21 • PANEL – LINING 1

ATTACHING PARTS --30 SFSW10F8DL26GY • SCREW 14

- - - - - - - - - * - - - - - - - - - -



25-31-11-07Z 25-31-11 AGMIS06-B73E-0126 Fig 7Z FEB 01/11 Page 0


GALLEY INSTL – UNIT NO.1 Figure 7Z (SHEET 1 OF 4)












GALLEY INSTL – UNIT NO.1

Figure 7Z (SHEET 4 OF 4)





CODE UNITS PER

ASSY 1234567

7Z --1 65C37843-1 GALLEY INSTL – UNIT NO.1 001001 RF 5 NAS602-6P • SCREW 9

10 MS51861-34C • SCREW 115 65C35726-5 • RETAINER 120 65C35726-100 • SEAL - BLADE 155 69-50328-9 • ROD INSTL – POSITION TIE 1

FOR DETAILS SEE: 53-42-00-80Z

60 69-622-78-1 • GROUND INSTL 165 NAS1801-3-8 •• SCREW 165 NAS1801-4-8 •• SCREW 170 NAS1149D0316H •• WASHER 375 NAS1149D0316H •• WASHER 275 NAS1149D0416H •• WASHER 280 BACW10P6AL •• WASHER 180 BACW10P11AL •• WASHER 185 MS21042L3 •• NUT 185 MS21042L4 •• NUT 190 NAS1801-4 •• SCREW 190 NAS1801-3 •• SCREW 195 NAS1149D0416H •• WASHER 295 NAS1149D0316H •• WASHER 2100 NAS1149D0316H •• WASHER 2100 NAS1149D0416H •• WASHER 2105 MS21042L3 •• NUT 1105 MS21042L4 •• NUT 1110 1002BC15 •• JUMPER ASSY 1110 BACJ40A20-15 •• JUMPER ASSY 1110 BACJ40D20-120 •• JUMPER ASSY 1110 RBEJ40D11-96 •• JUMPER ASSY 1115 BACB30NT3K6 • BOLT 4120 NAS1149D0316J • WASHER 4125 415N4002-24 • FITTING 1135 BACC10JB032C046 • CLAMP 1140 65C35726-12 • SEAL - FLOOR 1300 101719-101 • GALLEY ASSY 1305 BACB30LE5K9 • BOLT 4310 BACB30LE5K14 • BOLT 4315 BACW10BP5CD • WASHER 8



25-31-11-99Z 25-31-11 MOD-1022 Fig 99Z SEP 01/1 Page 0


HOT CUP INSTL – GALLEY 1 Figure 99Z


25-31-11-99Z 25-31-11 MOD-1022 Fig 99Z SEP 01/13 Page 1



CODE UNITS PER

ASSY 1234567

99Z --1 MEO-1022-001 INTRODUCTION OF DRIESSEN COMBO ASSY ON GALLEY G1A 001001 RF --1 AL253-1577 INSTALLATION OF DREISSEN COMBO ASSY (AERODEC DRAWING) 001001 RF

10 JF003001 • COMBO ASSY – HOT CUP 1

SEE DRIESSEN CMM 25-26-33 50 34-00318 • BRACKET ASSY 160 AL253-0247-001 • BRACKET CONNECTOR 170 9-028-13 • SCREW 2

--80 NAS1836-3-22 • INSERT 490 NAS514P1032-6 • SCREW 2100 NAS1149D0332J • WASHER 4110 NAS603-6 • SCREW 4

--130 AL253-1599-002 • SPACER – ADAPTER PANEL 4160 NAS514P632-12 • SCREW 4170 NAS1149D0616J • WASHER 4180 MS35649-262 • NUT 4190 AC16707 • CONNECTOR 1210 AL113-0248-001 • PLACARD – USER INSTRUCTIONS 1220 AN935-6 • WASHER 4

--230 NAS514P1032-21 • SCREW 4--240 AL253-1599-001 • ADAPTER PANEL 1250 NAS43DD1-10FC • SPACER 4

--260 TC342A-X • CLIP 1














CODE UNITS PER

ASSY 1234567

4Z --5 65C35407-2 GALLEY INSTL – UNIT NO.2 001001 RF

10 65C35407-4 • TAPE - HOOK AR15 415N0019-30 • SEAL ASSY AR25 69-50334-68 • ROD INSTL – POSITION TIE 1

FOR DETAILS SEE: 53-42-00-81Z

30 69-622-78-2 • GROUND INSTL 135 NAS1801-3-8 •• SCREW 135 NAS1801-4-8 •• SCREW 140 NAS1149D0316H •• WASHER 341 NAS1149D0316H •• WASHER 241 NAS1149D0416H •• WASHER 242 BACW10P6AL •• WASHER 142 BACW10P11AL •• WASHER 145 MS21042L3 •• NUT 145 MS21042L4 •• NUT 150 NAS1801-4 •• SCREW 150 NAS1801-3 •• SCREW 155 NAS1149D0416H •• WASHER 255 NAS1149D0316H •• WASHER 260 NAS1149D0316H •• WASHER 260 NAS1149D0416H •• WASHER 265 MS21042L3 •• NUT 165 MS21042L4 •• NUT 170 1002BC15 •• JUMPER ASSY 170 BACJ40A20-15 •• JUMPER ASSY 170 BACJ40D20-120 •• JUMPER ASSY 170 RBEJ40D11-96 •• JUMPER ASSY 175 415N4002-39 • FITTING ASSY 1

ATTACHING PARTS 80 NAS623-3-4 • SCREW 1685 AN960-10 • WASHER 16

- - - * - - - 145 65C35407-5 • SEAL - FLOOR AR145 65C35726-7 • SEAL - FLOOR AR270 101069-1 • GALLEY ASSY 1

--275 BACB30LE5K14 • BOLT 4--280 NAS6605-8 • BOLT 4--285 AN960-516 • WASHER 8





GALLEY INSTL – UNIT NO.4B





GALLEY INSTL – UNIT NO.4B






CODE UNITS PER

ASSY 1234567

7Z --1 65C37843-2 GALLEY INSTL – UNIT NO.4B 001001 RF 5 69-50329-11 • ROD INSTL – POSITION TIE 1 FOR DETAILS SEE: 53-42-00-80Z

10 69-50329-12 • ROD INSTL – POSITION TIE 1 FOR DETAILS SEE: 53-42-00-80Z

15 69-622-78-4 • GROUND INSTL 120 NAS1801-3-8 •• SCREW 120 NAS1801-4-8 •• SCREW 125 NAS1149D0316H •• WASHER 330 NAS1149D0316H •• WASHER 230 NAS1149D0416H •• WASHER 235 BACW10P6AL •• WASHER 135 BACW10P11AL •• WASHER 140 MS21042L3 •• NUT 140 MS21042L4 •• NUT 145 NAS1801-4 •• SCREW 145 NAS1801-3 •• SCREW 150 NAS1149D0416H •• WASHER 250 NAS1149D0316H •• WASHER 255 NAS1149D0316H •• WASHER 255 NAS1149D0416H •• WASHER 260 MS21042L3 •• NUT 160 MS21042L4 •• NUT 165 1002BC15 •• JUMPER ASSY 165 BACJ40A20-15 •• JUMPER ASSY 165 BACJ40D20-120 •• JUMPER ASSY 165 RBEJ40D11-96 •• JUMPER ASSY 170 BACB30NT3K5 • BOLT 1675 NAS1149D0332J • WASHER 1680 415N4002-39 • FITTING ASSY 285 BACC10JB032C046 • CLAMP 190 65C35726-12 • SEAL - FLOOR 1250 101721-101 • GALLEY ASSY 1

--255 BACB30LE5K13 • BOLT 8--260 BACW10BP5CD • WASHER 8


CHAPTER


SYSTEM




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





CODE UNITS PER

ASSY 1234567

99Z --1 MEO-0952-001 INSTALLATION OF A MINI QUICK ACCESS RECORDER 001001 RF

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


CHAPTER

LIGHTS




LIGHT INSTL – CONT CAB CREW Figure 5Z





CODE UNITS PER

ASSY 1234567

5Z --1 AGMIS10-B73E-0147 SECOND OBSERVERS STATION INSTL 001001 RF

10 34265-8 • LIGHT ASSY 120 65-45757-5 • BRACKET 1


CHAPTER

NAVIGATION




EQUIPMENT INSTL – ELECT. RACKS (INERTIAL REFERENCE UNIT ONLY) FIGURE 2Z





CODE UNITS PER

ASSY 1234567

3Z --1 AGM10-B73E-0048 IRS 2005 MAGNETIC VARIATION TABLE ACTIVATION 001001 RF

10 S242T101-117 • UNIT – INERTIAL REFERENCE 1 NOTE: EXISTING IRU PART NO. S242T101-114, WILL BECOME S242T101-117 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AE-34-0027 PER BOEING SERVICE LETTER 737-SL-34-177

10 S242T101-118 • UNIT – INERTIAL REFERENCE 1 NOTE: EXISTING IRU PART NO. S242T101-115, WILL BECOME S242T101-118 ONCE MODIFIED BY HONEYWELL SERVICE BULLETIN HG1050AE-34-0006 PER BOEING SERVICE LETTER 737-SL-34-177



34-53-21-01B 34-53-21 MOD 0057 Fig 1B FEB 01/11 Page 0


EQUIPMENT INSTL – ELECTRICAL RACKS (ATC TRANSPONDER ONLY)

Figure 1B


34-53-21-01B 34-53-21 MOD 0057 Fig 1B FEB 01/11 Page 1



CODE UNITS PER

ASSY 1234567

1B --1 MEO-0057-001 INSTL OF ELEMENTARY/ENHANCED MODE S SYSTEM 001001 RF

10 066-01127-1602 • TRANSPONDER - ATC 2 SUPPLIER CODE: V97896 ELECTRICAL EQUIPMENT NUMBER: M00163 M00381 MAINTENANCE MANUAL REF: 34-53-02 POST AERODEC MOD: MOD 0057


CHAPTER

OXYGEN




OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 2Z (SHEET 1 OF 2)




OXYGEN SYSTEM DISTRIBUTION – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 2Z (SHEET 1 OF 2)





CODE UNITS PER

ASSY 1234567


10 801307-00 • OXYGEN CYLINDER ASSY 120 69-46296-7 • BRACKET 130 65-53541-364 • TUBE ASSY 140 65-53541-397 • TUBE ASSY 150 65-53541-404 • TUBE ASSY 160 69-45719-1 • TUBE GUARD 1

--70 AN924-5D • TUBE NUT 1--80 NAS1149DN832H • WASHER 2--90 BACC10DK5 • TUBE CLAMP 5--100 BACE21AW0505L • ELBOW 1--110 BACN10GH3-12 • SPACER PLATE 1--120 BACR15BB3D4 • RIVET 2--130 BACT16AZ050505L • TEE 1--140 MS21902D5 • UNION 1--150 MS21908D5 • ELBOW 1--160 NAS1801-3-9 • SCREW 1--170 NAS1801-3-15 • SCREW 1--180 NAS1801-3-17 • SCREW 1--190 NAS1801-3-25 • SCREW 2--200 NAS42DD-6-32 • SPACER 3--210 NAS42DD-6-40 • SPACER 2--220 NAS602-7P • SCREW 2





OXYGEN SYSTEM INSTL – CONTROL CABIN (SECOND OBSERVER ONLY) Figure 20Z





CODE UNITS PER

ASSY 1234567


15 69-50982-12 • PANEL ASSY – SUPPORT 160 69-36613-2 • SHELF ASSY – OXY MASK 165 65-63685-5 • ANGLE 270 65-57439-3 • CLIP 275 69-50983-2 • ANGLE ASSY 180 69-50984-1 • ANGLE ASSY 185 69-74512-3 • BRACKET ASSY 193 69-50981-11 • CLOSURE PANEL ASSY 1105 69-45759-142 • FITTING ASSY 1

--110 AN960PD10L • WASHER 7--120 BACN10JC3 • NUT 15--130 BACN10JR3F • NUTPLATE 2--140 BACR15BA3A6 • RIVET 4--150 BACR15BB4D4 • RIVET 2--160 BACR15BB6D6 • RIVET 2--170 BACW10X4 • RETAINING RING 2--180 NAS1801-3-11 • SCREW 2--190 NAS514P1032-6 • SCREW 6--200 NAS514P632-7 • SCREW 4--210 NAS601-5P • SCREW 2--220 NAS601-8P • SCREW 2--230 NAS603-10P • SCREW 2--240 NAS603-6P • SCREW 3--250 NAS603-8P • SCREW 2--260 66-23277-2 • INSULATION PLATE 1--270 66-3044-1 • HEADPHONE HOOK 1


CHAPTER

AIRBORNE AUXILIARY

POWER




ENGINE ASSY – APU (INDICATING ONLY) FIGURE 2Z





CODE UNITS PER

ASSY 1234567

2Z --1 AGM10-B73E-0049 APU HOURMETER INSTALLATION 001001 RF

10 698788-2 • HOURMETER 120 LL54N40S4 • SCREW 230 NAS1149CN416R • WASHER 240 698431-1 • SHOCK MOUNT 150 QS200M24S • CLAMP 1


CHAPTER

FUSELAGE




ROD INSTL – NO.1 AND No.4B GALLEY POSITION TIE Figure 80Z





CODE UNITS PER

ASSY 1234567

80Z --5 69-50328-9 ROD INSTL – NO.1 GALLEY 001001 RF

18 MS20392-5C41 • PIN 119 MS20392-5C27 • PIN 125 AN960JD616 • WASHER 152 69-40791-1 • LUG ASSY - SPRT 1

ATTACHING PARTS --53 BACB30NF8 • BOLT 1--54 AN960-816 • WASHER AR--55 69235-820CD • NUT 1

- - - * - - - 56 BACB28B6-323P •• BUSHING 257 AN960C816 •• WASHER 258 69-40791-2 •• LUG 160 1042-6 • ROD ASSY 1

110 69-50329-11 ROD INSTL – NO.4B GALLEY RF115 BACB30NF6-18 • BOLT 2117 MS24665-304 • PIN 2118 MS20392-5C31 • PIN 1122 MS20392-5C31 • PIN 1125 AN960-616 • WASHER 2125 AN960JD616 • WASHER 2140 MS21042L6 • NUT 2150 1042-5 • ROD ASSY 1155 69-40791-1 • LUG ASSY - SPRT 1

ATTACHING PARTS --160 BACB30NF8 • BOLT 1--165 AN960-816 • WASHER 1--170 BMN4122AD3-8 • NUT 1--170 69235-820CD • NUT 1

- - - * - - - 175 BACB28B6-323P •• BUSHING 2180 AN960C816 •• WASHER 2185 69-40791-2 •• LUG 1

500 69-50329-12 ROD INSTL – NO.4B GALLEY RF505 MS24665-304 • PIN 4510 MS20392-5C31 • PIN 4513 MS20392-5C41 • PIN 2515 AN960JD616 • WASHER 4520 1042-5 • ROD ASSY 1522 1042-5 • ROD ASSY 1





ROD INSTL – NO.2 GALLEY POSITION TIE Figure 81Z





CODE UNITS PER

ASSY 1234567

81Z --5 69-50334-68 ROD INSTL – NO.2 GALLEY 001001 RF

15 MS24665-304 • PIN 216 MS20392-5C35 • PIN 118 MS20392-5C41 • PIN 130 AN96JD616 • WASHER 250 1042-5 • ROD ASSY - TIE 160 BACB30NF8 • BOLT 165 69-40794-1 • FILLER 170 AN960-816 • WASHER 175 69235-820CD • NUT 180 69-40791-1 • LUG ASSY 185 AN960C816 •• WASHER 290 BACB28B6-323P •• BUSHING 295 69-40791-2 •• LUG 1


AIRCRAFT

MAINTENANCE

MANUAL

Contents

AMM-CONTENTS Page 1


®




22-11-01 – DIGITAL FLIGHT CONTROL SYSTEM

PAGE BLOCK 501 – ADJUSTMENT/TEST


23-24-00 – EMERGENCY LOCATOR TRANSMITTER SYSTEM

PAGE BLOCK 1 – DESCRIPTION AND OPERATION

PAGE BLOCK 101 – FAULT ISOLATION

PAGE BLOCK 201 – MAINTENANCE PRACTICES


23-24-11 – EMERGENCY LOCATOR TRANSMITTER ANTENNA

PAGE BLOCK 401 – REMOVAL AND INSTALLATION

23-71-00 – VOICE RECORDER SYSTEM




25-11-11 – FLIGHT COMPARTMENT EQUIPMENT




Chapter 28 FUEL




31-24-24 – QUICK ACCESS RECORDER (MINI)



Chapter 33 LIGHTS


34-22-00 – ELECTRONIC FLIGHT INSTRUMENT SYSTEM – EFIS DISPLAY MODES TEST


AMM-CONTENTS Page 2


®

34-49-03 – GROUND PROXIMITY WARNING SYSTEM


34-53-02 – ATC SYSTEM

PAGE BLOCK 1 – DESCRIPTION AND OPERATION


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


Chapter 35 OXYGEN




49-72-11 – ELAPSED TIME INDICATOR

PAGE BLOCK 401 – REMOVAL/INSTALLATION

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

CHAPTER

AUTO FLIGHT

B737-300/400/500 AIRCRAFT MAINTENANCE MANUAL

EFFECTIVITY

22-11-01001 Page 501 MOD 1093 JAN 01/12


DIGITAL FLIGHT CONTROL SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry an Option Pin Check of the Digital Flight Control System. The Option Pin Check is part of the System Test.

B. Any other test associated with the Digital Flight Control System in accordance with

22-11-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. System Test – DFCS – Option Pin Check Only

A. Location Zones

Zone Area

101 Control Cabin - Left 102 Control Cabin - Right

B. Prepare for the System Test

SUBTASK 22-11-01-845-129

(1) Do the preparation for the DFCS BITE test in this task: "Operational Test - Digital Flight Control System".

C. Option Pin Check

SUBTASK 22-11-01-745-020

(1) Do the Option Pin Check:

(a) Open the AFCS B FCC DC circuit breaker on P6-2 Circuit Breaker Panel.

(b) [If POST SB 737-34-1593] Set the FMC transfer switch to NORMAL position.

(c) Push the INIT/REF key on the CDU keyboard to show the POS INIT page or PERF INIT page.

(d) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page.

(e) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page.

(f) Push the LSK adjacent to <DFCS to show the DFCS BITE TEST LINE MAINT

1/2 page.

(g) [If POST SB 737-34-1593] Ignore the message "MOVE FMC TRANSFER SWITCH TO BOTH ON L" shows on the CDU and keep the position of the FMC transfer switch in the NORMAL position.

(h) Stop for approximately 15 seconds.

(i) Push the LSK adjacent to <PUSH IF NO RESPONSE.

(j) Push the LSK adjacent to <CONTINUE.


EFFECTIVITY

22-11-01001 Page 502 MOD 1093 JAN 01/12


(k) Push the NEXT PAGE key on the CDU to show the DFCS BITE TEST OVERNIGHT MAINT 2/2 page.

(l) Push the LSK adjacent to <SENSOR VALUES to show the Sensor Values Test

Index page.

(m) Push the LSK adjacent to <OPTIONS (SOP) to show the first page of the standard options.

(n) Push the LSK adjacent to <CONTINUE to show the second page of the

standard options.

(o) For AERODEC MOD-1093, Make sure that the following options on Table 502 are displayed or not displayed on the CDU display.

Table 502

SOP – A/S WARNING NOT DISPLAYED

SOP – PARITY CLOSED DISPLAYED

(p) Close the AFCS B FCC DC circuit breaker on the P6-2 Circuit Breaker

Panel.

(q) Open the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.

(2) Do the steps in the Option Pin Check again for the channel B.

(3) Close the AFCS A FCC DC circuit breaker on the P18-1 Circuit Breaker Panel.

(4) Push the INIT/REF key on the CDU keyboard to get out of the BITE.

D. If required, continue testing in accordance with 22-11-01 Page Block 501 of the

appropriate AMM, or Put the Airplane Back to Its Initial Condition in accordance with 22-11-01 Page Block 501.

CHAPTER

COMMUNICATIONS


EFFECTIVITY

23-24-00AIRPLANES WITH ARTEX C406-1 ELT Page 1 MOD 0889 SEP 01/13


EMERGENCY LOCATOR TRANSMITTER SYSTEM - DESCRIPTION AND OPERATION

1. General Note: For the current description and operation please refer to Emteq AMM Supplement

Document No. 2-22566-908


EFFECTIVITY



EMERGENCY LOCATOR TRANSMITTER SYSTEM

- FAULT ISOLATION 1. General Note: For the current Fault Isolation processes please refer to Emteq AMM Supplement



EFFECTIVITY



EMERGENCY LOCATOR TRANSMITTER SYSTEM - MAINTENANCE PRACTICES

1. General Note: For the current Maintenance Practices please refer to Emteq AMM Supplement



EFFECTIVITY



EMERGENCY LOCATOR TRANSMITTER SYSTEM

- ADJUSTMENT & TEST 1. General Note: For the current testing processes please refer to Emteq AMM Supplement



EFFECTIVITY



EMERGENCY LOCATOR TRANSMITTER SYSTEM - REMOVAL AND INSTALLATION

1. General Note: For the Removal and Installation processes please refer to Emteq AMM Supplement



EFFECTIVITY

23-71-00AIRCRAFT WITH CVR SWITCH Page 501 MOD 0916 APR 01/13

Page produced by Aerospace Design and Engineering Consultants (AeroDECTM) Limited, UK. Copyright ©. See Manual Supplement Introduction pages for information.


EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY



H. AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Voice Recorder AUTO/ON Switch Test

(1) TEST WITHOUT ENGINES RUNNING

NOTE: Additional relays are added to tum the CVR "on" when either engine is running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.

(a) Close all applicable circuit breakers to the CVR system.

(b) At the P5 overhead panel, at the cockpit voice recorder (CVR) control panel,

connect a 600 ohm headset to the CVR monitor jack.

(c) Make sure the CVR AUTO/ON switch is in the AUTO position.

(d) Make sure ambient cockpit audio is not heard over the headset. The CVR is OFF.

(e) On the CVR P5 control panel; AIRPLANES WITH VOICE RECORDER CONTROL PANEL

WITH METER; Make sure that the voice recorder control panel meter needle does not move while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light does not come on while you push the TEST switch.

(f) Make sure the CVR AUTO/ON switch is in the ON position.

(g) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(h) On the P5 control panel and make sure that; AIRPLANES WITH VOICE RECORDER

CONTROL PANEL WITH METER; Make sure that the voice recorder control panel meter needle moves and stays in the green area while you push the TEST switch. AIRPLANES WITH VOICE RECORDER CONTROL PANEL WITH TEST LIGHT; Make sure that the TEST light comes on while you push the TEST switch.

(i) At the P18-2 panel, open circuit breaker (C9500) VOICE RECORDER RELAY.

(j) Make sure the CVR Auto/On switch automatically switches to the AUTO position.

(k) Make sure you cannot hear flight deck conversation in the headset. The CVR

is OFF.

(l) Close circuit breaker (C9500) VOICE RECORDER RELAY.


EFFECTIVITY



(2) TEST WITH ENGINES RUNNING

NOTE: Additional relays are added to tum the CVR "on" when either engine is

running, and to have a 5 minute time delay in turn off after the engine(s) are shut down. Therefore, the CVR will function approx. 5 minutes upon power up and immediately following engine shut down. This is normal operation.

(a) Make sure the CVR AUTO/ON switch is in the AUTO position.

(b) Start No. 1 Engine Per AMM 71-00-00/201, ensure the No. 1 Eng N2 Gauge is

>46.33%.

(c) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(d) Shut down No.1 Eng Per AMM 71-00-00/201.

(e) Wait six minutes.

NOTE: The CVR switch circuit relay R9500 will tum the CVR off after five minutes.

(f) Make sure you cannot hear flight deck conversation in the headset. The CVR

is OFF.

(g) Start No. 2 Engine Per AMM 71-00-00/201, ensure the No. 2 Eng N2 Gauge is >46.33%.

(h) Make sure you hear flight deck conversation in the headset. The CVR is ON.

(i) Shut down No.2 Eng Per AMM 71-00-00/201.

(j) Wait six minutes.

NOTE: The CVR switch circuit relay R9500 will turn the CVR off after five

minutes.

(k) Make sure you cannot hear flight deck conversation in the headset. The CVR is OFF.

I. Put the Airplane Back to the Usual Condition S 085-015 (1) Remove the headphone from the control panel.

S 865-036

(2) AIRPLANES WITH VOICE RECORDER AUTO/ON SWITCH; Set the voice recorder AUTO/ON switch to the AUTO position. S 865-016 (3) Remove electrical power if it is not necessary (AMM 24-22-00/201)

CHAPTER

EQUIPMENT/

FURNISHINGS


EFFECTIVITY

25-11-11AIRPLANES WITH SECOND OBSERVER’S SEAT Page 201 MOD 0948 MAR 01/11



EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY




EFFECTIVITY



CHAPTER


SYSTEM


EFFECTIVITY

31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 201 MOD 0952 FEB 01/11


QUICK ACCESS RECORDER (MINI) – MAINTENANCE PRACTICES 1. General A. This procedure has this task: 1) The return to service test of the mini Quick Access Recorder (QAR). 2. Return to Service Test A. Test Equipment and Material

Reference Description 802-0208 RSU II Kit or functionally equivalent computer with USB port. 700-0179 miniQAR MKII HS USB I/F Software (included with 805-0005) 605-0177 Portable Test Interface (PTI) Cable 805-0005 miniQAR MKII, HS USB I/F KIT Includes PTI cable (605-0177)

and software (700-0179) B. Test Setup

1) Connect PTI cable P/N 605-0177 to the UUT DB9 connector.

NOTE: Do not Connect the USB connector of the PTI cable P/N 605-0177.

C. Procedures

1) Turn-on the PC or RSU II and allow it to boot.

2) If the RSU Menu is displayed, select File, Exit to Windows (refer to the RSU II Operations Manual, Part Number 900-0208 – included in the RSU II Kit.)

3) On the Windows toolbar, select Start, Programs, Avionica, and MiniQAR Support

Util.

4) Connect the USB connector of the PTI cable P/N 605-0177 to the USB Port of the PC or RSU II.

5) Make sure that the BIT LED of the Unit Under Test is illuminated.

6) Select “Tools”.

7) A “Return to service” prompt appears. Select “Yes”

8) A message “Return To Service In-Progress Please Wait” will be displayed.

9) The “Please Wait” will be replaced by a Results screen. Make sure all results

indicate PASSED.

10) Select “Continue”.

11) Verify that the miniQAR LED is blinking.


EFFECTIVITY

31-24-24AIRPLANES WITH AVIONICA MINI QAR Page 202 MOD 0952 FEB 01/11


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

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

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

of the PC or RSU tablet first.

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

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

CHAPTER

NAVIGATION


EFFECTIVITY

34-22-00001 (PV301) Page 501 MOD 0861 APR 01/11


ELECTRONIC FLIGHT INSTRUMENT SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry An EFIS Display Modes Test of the EFIS System. The EFIS Display Modes Test is part of the Operation Test of the EFIS System

B. Any other test associated with the EFIS System in accordance with 34-22-00 Page

Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

C. EFIS Display Modes Test

SUBTASK 34-22-00-865-028-001

(1) Make sure the EFI transfer switch is in the NORMAL position.

SUBTASK 34-22-00-865-149-001

WARNING: DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS ADDED OR REMOVED IN AREA 200 FEET OR LESS OF THE ANTENNA. THIS CAN CAUSE AN EXPLOSION.

DO NOT OPERATE THE WEATHER RADAR WHILE THE AIRPLANE IS IN A HANGAR OR OTHER ENCLOSURE. MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET OR LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN CAUSE INJURY TO PERSONS.

(2) On the two EFIS control panels, set the controls as follows:

(a) The RANGE switch to the 80 position.

(b) The map mode display switches to the on position.

(c) The WXR ON switch to the on position.

SUBTASK 34-22-00-745-030-001

(3) Push the INIT/REF key on the FMCS CDU.

SUBTASK 34-22-00-745-031-001 (4) Push the line select key (LSK) 6L (<INDEX) on the FMCS CDU.

SUBTASK 34-22-00-745-032-001

(5) Push the LSK 6R (MAINT>).

(a) Make sure the FMCS CDU display shows the MAINT BITE INDEX 1/1 page.

SUBTASK 34-22-00-745-033-001 (6) Push the LSK 5L (<EFIS).

(a) Make sure the FMCS CDU display shows the EFIS BITE TEST page.

SUBTASK 34-22-00-745-034-001

(7) Push the LSK 3L (<SELF TEST).


EFFECTIVITY

34-22-00001 (PV301) Page 502 MOD 0861 APR 01/11


SUBTASK 34-22-00-755-189-001

(8) AIRPLANES WITH EFIS SYMBOL GENERATOR P/N S242T404-413 AND ON; Make sure the hex code lines on the bottom right of the two EADIs show as follows:

Table 501/34-22-00-993-804-001

FA391B0 87BE000 C080000

SUBTASK 34-22-00-865-035-001

(9) On the left and right EFIS control panels, set the mode switches to the positions as follows:

(a) FULL NAV (b) EXP NAV (c) FULL VOR/ILS

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

VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.

(d) EXP VOR/ILS

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

VHF NAV control panel; a test value of 116.80 will, however, be shown on the EHSI. To show the ILS mode, an ILS frequency (108.10) must be set on the VHF NAV control panel; a test value of 110.10 will, however, be shown on the EHSI.

(e) MAP (f) CTR MAP (g) PLAN

SUBTASK 34-22-00-755-036-001

(10) For each mode on the left EFIS control panel, make sure the applicable test patterns show on the left display units.

SUBTASK 34-22-00-755-037-001

(11) For each mode on the right EFIS control panel, make sure the applicable test patterns show on the right display units.

SUBTASK 34-22-00-755-038-001

(12) For each mode on the two EFIS control panels, make sure the test patterns are the same on the two EADIs and the two EHSIs.


EFFECTIVITY

34-49-03AIRPLANES WITH ENHANCED GROUND PROMXITY WARNING Page 501 MOD 0865 Feb 01/11


GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST 1. General

A. This section carries out an operational test of the Enhanced Ground Proximity Warning System (EGPWS) to support the continuous operation of AeroDEC Modification MOD-0865.

2. Enhanced Ground Proximity Warning System - Operational Test

A. References

Reference Title

24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER)

B. Location Zones

Zone Area

101 Control Cabin - Left 102 Control Cabin - Right 205 Electronic Compartment

C. Prepare for the Test

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

(2) Make sure this circuit breaker is closed:

(a) P18 Circuit Breaker Panel

1) TERRAIN DISPLAY 2) ENHANCED GND PROX

D. Operational Test

(1) Carry out a Level 1 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system:

AURAL WARNING LIGHTS EADI

"Minimums" "1000" "500" "100" "50" "40" "30" "20" "10"


EFFECTIVITY

34-49-03AIRPLANES WITH ENHANCED GROUND PROMXITY WARNING Page 502 MOD 0865 Feb 01/11


(2) Carry out a Level 2 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI

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

(3) Carry out a Level 3 Self Test of the EGPWS and ensure that the following Altitude Callouts are enunciated over the flight deck audio system: AURAL WARNING LIGHTS EADI

“ALTITUDE CALLOUT MENU 91”

E. Put the Airplane Back to Its Usual Condition

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

------------------------- END OF TASK ---------------------------


EFFECTIVITY

34-53-02AIRPLANES WITH ENHANCED MODE S Page 1 MOD 0090 FEB 01/11


ATC SYSTEM - DESCRIPTION AND OPERATION 1. General (Fig. 1)

A. The Air Traffic Control Radar Beacon System, (ATC system), provides airplane tracking, altitude and

identification information to an ATC ground station. The ATC transponder responds to an interrogation from an ATC ground station. The ATC system responds to ground station interrogations in one of three different modes: mode-A, mode-C and mode-S. Mode-A and Mode-C provide identification and altitude information. Mode-S provides selective airplane identification and data link capabilities. After a ground station interrogation, the transponder automatically transmits a pulse coded reply signal in one of the above modes. The mode of reply is determined by the mode of interrogation.

B. Two ATC systems are installed on the airplane, each with its own transponder. Only one transponder operates at

a time. A dual ATC control panel provides independent and isolated control for both systems. Control information is sent to either transponder by signal discretes and an ARINC 429, 572, 718, or 730 bus.

C. There are two ATC antennas on the airplane. The antennas are shared by the two transponders. Two rf relays

switch both antennas from one transponder to the other.

D. Each transponder receives altitude data from both air data computers (ADCs). The altitude data is sent to the transponders by an ARINC data bus.

E. The airplane’s Flight ID information is provided from data relayed by the Flight Management System (FMS).

F. The ATC and DME systems operate in the same L-band frequency range. A suppression circuit is connected

between the ATC transponders and the DME interrogators to prevent simultaneous transmissions.

G. The ATC system operates in three different modes: Mode-A, mode-C and mode-S. The mode of operation is determined by the mode of interrogation from a ground station and the current configuration of the altitude reporting function.

H. The No. 1 ATC system receives 115 volt, 400 Hz ac power from the electronics power bus No. 1. Power is

supplied through the ATC-1 circuit breaker located on the left load control center circuit breaker panel P18.

I. The No. 2 ATC system receives 115 volt, 400Hz ac power from the electronics power No. 2 bus. Power is supplied through the ATC No. 2 circuit breaker which is located on the right load control center circuit breaker panel P6.

2. ATC Control Panel (Fig. 1)

A. The ATC control panel is located on the aft electronic control panel (P8). The control panel contains switches and controls which provide reply codes and mode selection for two ATC/Mode S transponders.


EFFECTIVITY



ATC System Component Location Figure 1


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3. ATC Transponder (Fig. 1)

A. The ATC transponders are located on the E2 electronic equipment rack. B. The active ATC transponder transmits a coded reply when it is interrogated by an ATC ground station.

(1) Both transponders are identical to each other. Each transponder and the following switches and indicators:

(a) A green TPR indicator light which comes on when a transponder self-test is successful.

(b) A red TPR indicator light which comes on when a transponder self-test detects a failure.

(c) A red ALT indicator light which comes on when the altitude input source indicates a barometric altitude

failure.

(d) A red DATA IN indicator light which comes on if an error is detected in the ARINC 429 control word from the control panel.

(e) A red TOP indicator light which comes during a self-test when the upper antenna impedance is incorrect.

(f) A red BOT indicator light which comes during a self-test when the lower antenna impedance is incorrect.

(g) A TEST switch which starts a transponder self-test.

4. ATC Antenna

A. Two ATC antennas are installed in the airplane. The antennas are on the top and the bottom of the airplane. Two rf switching relays connect both antennas to the active transponder. The top antenna is located on the centerline of the fuselage at station 430.25. The bottom antenna is located on the centerline of the fuselage at station 355. The antennas are omnidirectional L-blade type antennas. Each antenna can transmit and receive signals for the active transponder. The active transponder automatically uses the antenna with the greatest signal strength.

5. Operation

A. Mode-A and Mode-C

(1) There is no power switch on the ATC control panel. Power is applied to the system when the ATC-1 and ATC-2 circuit breakers on the P6-1 and P18-1 panels (fig. 2) are closed. On systems with two antennas, power is aplied to both ANTENNA TRANSFER RELAYs when the ATC ANTENNA SW circuit breaker on the P6-1 panel (fig. 2) is closed.

(2) The desired ATC system (No. 1 or No. 2) is set with the transponder select switch. The '1' position causes

the control panel to send an 'ON' discrete to transponder No. 1 if the AIR/GND RELAY is in AIR mode and the altitude reporting switch is set to ALT OFF or ALT ON. The '2' position causes the control panel to send an 'ON' discrete to transponder No. 2 if the AIR/GND RELAY is in AIR mode and the altitude reporting switch is set to ALT OFF or ALT ON.


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ATC System Block Interface Schematic Figure 2


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(3) The desired 4-digit ATC code is set by pressing the FCN key to highlight the ATC code entry within the ATC

Control Panel window. Entry of the desired code is carried out by pressing the relevant alpha/numeric keys. (4) The altitude reporting switch is set to ALT OFF or ALT ON to set the desired altitude reporting function. (5) If the altitude reporting function is on, then the ATC system will reply to mode-A and mode-C ground station

interrogations. If the altitude reporting function is off, then system will reply to mode-A interrogations. Mode-S replies are not affected by the condition of the mode switch.

(6) The Flight identity code and mode configuration information is sent to the transponders through ARINC

busses and discretes. The 4-digit code identifies the airplane to the ground station for mode-A and mode-C interrogations.

(7) When the airplane leaves the ground, the AIR/GND relay is set to AIR. This sends a discrete signal to the

control panel. The control panel then sends an 'ON' discrete to the selected transponder. At this point, the system will respond to ground station interrogations.

B. Mode-S Operation

(1) Mode-S functions operate on an airplane if the mode-S programming plug is configured with a unique mode-

S address. If all the programming pins are grounded (they have a bit value of one), then there is no unique address and the mode-S functions do not operate. The mode-S code is hard wired on mode-S equiped airplanes. The identity code set on the ATC control panel has no effect on the mode-S address code of the airplane. Mode-S functions in the airplane are automatic and are not configured by the pilot.

C. Self-Test Operation

(1) Both ATC transponders have Built-In Test Equipment (BITE). A BITE test can be started if the transponder

to be tested has power. The BITE test is started when the TEST switch on the transponder face is pushed. The BITE test does the following:

⎯ Does a checksum of internal ROM contents. ⎯ Tests the transponder RAM. ⎯ simulates noise sources and monitors the results. ⎯ Tests the antenna impedance. ⎯ Simulates a Mode-S All-Call interrogation and reply. ⎯ Samples the internal power supply monitor. ⎯ Checks the operation of the serial busses connected to the transponder

(2) The green TPR indicator light will come on if no errors were detected during the BITE test. The red TPR

indicator light will come on if any part of the BITE test fails. (3) The BITE monitor continuously tests transponder functions while the ATC system operates normally (not in

test mode). If a failure is detected, the red TPR indicator light will come on and a TRANSPONDER FAIL DISCRETE will be sent to the control panel. If the altitude input from the ADC is in error, the red ALT indicator light will come on.


EFFECTIVITY



MODE-S Programming Pin Locations for ATC-1 and ATC-2 Transponders Figure 3


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ATC System Pulse Codes Figure 4


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ATC System Reply Pulse Codes Figure 5


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ARINC 429 Data Control Word Format Figure 6


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ATC SYSTEM - ADJUSTMENT/TEST 1. General

A. The ATC system adjustment/test procedure contain two tasks. One is an operational test; the other is a system test. The operational test is a fast check of the ATC system and no test equipment is needed. The system test first does the operational test. Then it uses test equipment to examine the ATC code reception, altitude reporting, transponder sensitivity, side lobe suppression and transmitter frequency.

B. The system test uses the Instrument Flight Research 601 ATC ramp test set.

C. Because the ATC transponder responds to signals from the antenna with the strongest signal strength, it is necessary to put the test set antenna close to the airplanes antenna to do a proper test. The test set antenna should be put near the bottom ATC antenna on the airplane to examine the bottom transponder circuitry and the same for the top ATC antenna.

TASK 34-53-02-715-003

2. Operational Test - ATC System

A. General

(1) The operational test is a fast check of the ATC system. It uses only the system's BITE function. No special test or ground equipment is necessary.

(2) The ATC transponder internal BITE circuitry do a self-test on all internal circuitry. This includes the injection

of Mode S signals into the receiver unit to examine if the signals are processed properly. If the Mode S function fails, the red TPR FAIL LED indicator comes on.

B. References

(1) AMM 24-22-00/201, Manual Control

C. Access

(1) Location Zones

101/102 Flight Compartment 205 Electronic Compartment

(2) Access Panel

1201 Electronics Equipment Access Door

D. Prepare for the Operation Test

S 865-004 (1) Supply electrical power (AMM 24-22-00/201).

S 865-005

(2) Close these circuit breakers.

(a) P18 Load Control Center – Left 1) ATC 1


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(b) P6 Load Control Center – Right 1) ATC 2

E. Procedure

S 865-236

(1) On the ATC control panel, set the transponder select switch to the applicable system.

(a) Start the self test on the front of the transponder.

(b) Make sure the LEDs sequence that follow occurs:

1) All LEDs come on for about three seconds

2) All LEDs go off for about two seconds 3) The green LED comes back on.

(c) Release the TEST switch. S 865-253

(2) Set the ATC system to STBY.

TASK 34-53-02-735-049 3. System Test - ATC System for Airplanes with Elementary Surveillance (With the IFR ATC-601 Test Set with

Software Version 3 or later)

A. General

(1) This system test is a more complete check of the ATC system. The system test first does the ATC - Operational Test. Then it uses ground test equipment to examine the left and right ATC systems.

(2) The IFR 601 test set is used to test the functionality of the mode S transponder. All twenty tests can be run

automatically in the AUTO mode or individually in single test mode. Results from the last test are shown on each test page. The PASSED/FAILED indication is shown on top of the page. To do a single test, use the select keys to get to the desired test and push the RUN/STOP key.

B. Special Tools and Equipment

(1) ATC Transponder Ramp Test Set IFR ATC-601

C. References

(1) AMM 24-22-00/201, Manual Control

(2) AMM 34-12-01/501, Air Data Computer System


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D. Access

(1) Location Zones 101/102 Flight Compartment 205 Electronic Compartment

E. Prepare for the System Test

S 845-050

CAUTION: DO NOT PLACE THE REMOTE TEST SET ANTENNA CLOSER THAN 15 INCHES (0.40

METERS) TO THE AIRCRAFT ANTENNA WITH THE TEST SET ON. THIS WILL CAUSE DAMAGE TO THE TEST SET.

(1) Put the test set antenna approximately 30 feet from the ATC antenna for the related system.

Note: The test set antenna must be within the line of sight of the ATC antenna.

S 845-051

(2) Put the test set antenna in position towards the aircraft antenna.

S 845-052 (3) Connect the coax cable from the remote test set antenna to the test set.

S 865-053

(4) Close these circuit breakers:

(a) P18 Load Control Center - Left 1) ATC 1

(b) P6 Load Control Center - Right

1) ATC 2

S 715-154 (5) Do the ATC Operational Test.

S 865-054

(6) Set the PWR switch on the test set to the ON position.

Note: The test set is a source of interference for radio and L-band radar equipment operating on the airplane and located near the test set. Turn the test set off as soon as the test is completed or when you must perform other radio checks on the airplane.

S 865-055

(7) Push the SETUP key to enter the SETUP menu.

Note: For information regarding the battery test, timing and recharging refer to the operation section of the test set operators manual.

S 865-155

(8) Push the SELF TEST key on the test set.


EFFECTIVITY



S 865-156 (9) Push the RUN/STOP key to start the self test.

(a) Make sure the test set display shows PASSED.

S 865-157

(10) Push the SETUP key to enter the SETUP menu.

S 865-056 (11) Enter 30 feet in the RANGE field for the TOP and BOTTOM antenna.

S 865-158

(12) Enter 17 feet for the HEIGHT field for the TOP antenna and 3 feet for the BOTTOM antenna.

S 865-159 (13) Choose the bottom antenna on the SELECTED field.

(a) Use the SLEW keys to change the values. (b) Use the SELECT keys to change the items.

(c) Use the SELECT keys to select the antenna which you must test.

S 865-267

(14) Enter the gain listed on the test set antenna into the GAIN_1030 and GAIN_1090 field.

S 865-231 (15) Enter the cable loss listed on the cable in the LOSS field.

S 865-160

(16) Open these circuit breaker.

(a) P6 Circuit breaker Panel

1) AIR/GND RLY and LTS 2) NOSE GEAR AIR/GND

S 865-161

(17) Set the captain's and first officer's altimeter to1013.25mb

F. ATC System Test

S 865-162

CAUTION: DO NOT USE CODES 7500, 7600-7677, AND 7700-7777. THESE ARE EMERGENCY CODES.

(1) Set the code switches on the ATC control panel to a desired ATC ID code.

(2) Using the FMC MCDU Select FMC, press the RTE Key and enter a Flight ID Code into the Flt No. field.


EFFECTIVITY



Note: The Flight ID code to be entered can be any combination of letters or numbers and up to eight

characters in length. As the same keypad keys are used to enter alpha/numeric characters, you may have to press the keypad keys numerous times to enter your selected numbers/letters. Typical Flight ID – ABC123

S 865-163

(3) Set the transponder select switch on the ATC control panel to the left or No. 1 system.

S 865-168 (4) Set the altitude reporting switch on the ATC control panel to ALT ON.

S865-057

(5) Push the AUTO TEST key on the test set.

(6) Using the Pitot-Static test set compare altitude readings to the altitude reported in the replies to the IFR ATC-601 test set at altitudes from ground level to 40,000 feet at 5,000 feet intervals. The reported altitude should be within 100ft of the captains indicated altitude.

(7) On the ATC control panel, select Altitude Reporting ‘OFF’. Ensure that no altitude is displayed on the IFR

ATC-601 test set. (8) On the ATC control panel, select the ‘ALT ON’ mode of operation.

S 865-187

(9) Use the RUN/STOP key to start or stop individual test.

S865-170 (10) Use the SELECT key to select each individual test.

(11) On the ATC Control panel, momentarily press the IDENT pushbutton. Ensure that the IFR ATC-601 test set

displays the IDENT indication for 15 to 20 seconds S 735-058

(12) Do a check of the REPLY DELAY TEST.

(a) Make sure the reply delay is 3.00us (±0.50us) for ATCRBS mode.

S 735-059 (13) Do a check of the REPLY JITTER TEST.

(a) Make sure the reply jitter is < 0.06us for all call. (b) Make sure the reply jitter is < 0.1us for ATCRBS modes.

S 735-060

(14) Do a check of the ATCRBS REPLY TEST.

(a) Make sure the spacing of the F1 to F2 pulse is 20.3us (±0.10us)

(b) Make sure the duration of the F1, F2 pulse is 0.45us (±0.10us).


EFFECTIVITY



S 735-061 (15) Do a check of the SLS LEVEL TEST.

(a) Make sure the reply is received when the SLS pulse is -9dB and no reply is received when the SLS

pulse is 0dB.

Note: Run the SLS level test in less than 95 feet (28.96 meters) of the UUT antenna.

S 735-062 (16) Do a check of the ATC ONLY ALL-CALL TEST.

(a) Make sure the mode S transponder did not reply to the interrogation (PASSED TEST).

S 735-063

(17) Do a check of the MODE S ALL CALL TEST.

(a) Make sure the test set shows PASSED and the airplane's mode S address.

S 735-064 (18) Do a check of the INVALID MODE S ADDRESS TEST.

(a) Make sure the mode S transponder did not reply (PASSED TEST). S 735-065

(19) Do a check of the SPR ON/OFF TEST.

(a) Make sure a reply is receive when SPR is ON and no reply is receive when SPR is OFF.

S 735-066 (20) Do a check of the MODE S UF0 TEST.

(a) Make sure (Down-link format) DF=0, AC=(airplane's altitude) and ADDRESS=(airplane's mode S

address) (WDM 34-53-12).

Note: Make sure the reported altitude is within ±125 feet of the local field elevation altitude shown on captain's and first officer's altimeter (applicable for all altitude reporting check).

S 735-067

(21) Do a check of the MODE S UF4 TEST.

(a) Make sure DF=4, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).


(a) Make sure DF=5, ID=(selected ATC ID code on the ATC control panel) and ADDRESS=(airplane's

mode S address).


EFFECTIVITY




(a) Make sure DF=11 and AA = Aircraft Address

S 735-070

(24) Do a check of the MODE S UF16 TEST. (a) Make sure DF=16, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).

Note: No reply to the UF16 test is not a failure of the ATC system.

S 735-071

(25) Do a check of the MODE S UF20 TEST.

(a) Make sure DF=20, AC=(airplane's altitude) and ADDRESS=(airplane's mode S address).

Note: No reply to the UF20 test is not a failure of the ATC system.


(a) Make sure DF=21, ID=(selected ATC ID code on the ATC control panel) and ADDRESS=(airplane's

mode S address). Note: No reply to the UF21 test is not a failure of the ATC system.

S 735-073

(27) Do a check of the SQUITTER TEST.

(a) Make sure the squitter's period is between 0.8 to 1.2 seconds.

S 735-074 (28) Do a check of the FREQUENCY TEST.

(a) Make sure the reply frequency of the transponder is 1090 MHz ±1MHz.

(29) Do a check of the FLIGHT ID BDS 2.0 TEST

(a) Make sure the down-link format DF = 20, and the Flight ID field = selected Flight ID code on FMC CDU.

(30) Do a check of the MODE S UELM TEST (uplink extended length message). Ensure that the display shows passed.

(31) Do a check of the MODE S DELM TEST (downlink extended length message). Ensure that the display

shows passed.


EFFECTIVITY



S 735-075 (32) Do a check of the DIVERSITY TEST.

(a) Make sure the power level difference is > 20dB between 'ON' antenna squitters and 'OFF' antenna

squitters.

Note: To make sure the dynamic range is 20dB, a diversity test must be run at a distance of less than 50 feet (15.2 meters) from the airplane antenna.

S 735-076

(33) Do a check of the MTL DIFFERENCE TEST.

(a) Make sure the Minimum Threshold Level (MTL) difference between mode A and mode C is <1.0dBm. (34) Do a check of the SELECTED VERTICAL INTENT REPORT BDS 4.0 Parts 1 and 2.

(a) On the Mode Control Panel (MCP) select an altitude of 30,000ft and if the MCP will allow it, VNAV Mode to ‘ON’ and APPR Mode to ‘OFF’.

(b) Ensure that the display shows Passed and that the MCP/FCU SEL ALT = 30,000ft, and the AA =

Aircraft Address. (c) Ensure that FMS SEL ALT = N/A, SOURCE INFO = NO and TARGET ALT = UNKNOWN.

(d) Ensure that BARO PRES SET = 1013.25mb abd that VNAV MODE, APPR MODE, ALT MODE are either ACTIVE or N/ACTIVE, dependant on selection on MCP.

(35) Do a check of the DATA LINK CAPABILITY REPORT BDS 1,0 PART 1 (a) Ensure that the display shows PASSED, SUBNET VER VBR = 000 and XPDR LEVEL = 2-4.

(b) Ensure that the display shows SPECIFUIC SER CAP REP FIELD = YES, DTE = NO, UELM SEG CAP = NO UELM and CONT FLAG = NO.

(c) Ensure that the display shows DELM SEG CAP = NO DELM, AIRCRAFT ID CAP = YES, SI CAP =

YES and SQUITTER CAP = YES (36) Do a check of Track and Turn Report BDS 5,0

(a) Ensure that the display shows PASSED, AA = Aircraft Address, ROLL ANGLE = 0.0 (±2.0) degrees and GND SPEED = 0 (±2.0) kts.

(b) Ensure that the display shows T_TRACK ANGLE = N/A and RATE = N/A.

(37) Do a check of the HEADING & SPEED REPORT BDS 6,0

(a) Set the Pitot-static test set to simulate an indicated airspeed of 250kts and a rate of climb of 1000 fpm. (b) Ensure that the display shows PASSED, AA = Aircraft Address, IND AIR SPEED = Flight Deck

indicated airspeed (±10%), BARA ALT RATE = Flight Deck indicated vertical speed, MAG HDG = Current Aircraft Heading (±2.0 degrees) and I_V_VEL = Current A/C Rate of Climb (±200 ft/min)


EFFECTIVITY



(c) Release all Pitot-Static pressure from the Pitot-Static system.

S 715-184

(38) Do the system test again for the right or No. 2 ATC system and use the right or No. 2 air data source.

Note: On the test set, select the TOP ATC antenna.

G. Put the Airplane Back to Its Usual Condition

S 845-185 (1) Remove the ATC ramp test set and antenna shield.

S 865-186

(2) Close these circuit breaker.

(a) P6 Circuit Breaker Panel: 1) AIR/GND and LTS 2) NOSE GEAR AIR/GND

S 865-256

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


EFFECTIVITY

34-62-01001 (PV301) Page 501 MOD 0857 FEB 01/11


FLIGHT MANAGEMENT COMPUTER SYSTEM – ADJUSTMENT/TEST 1. General

A. This procedure has one task, to carry a Program Pin Verification of the Flight Management Computer System. The Program Pin Verification is part of the System Test – Analogue Discretes.

B. Any other test associated with the Flight Management Computer System in

accordance with 34-62-01 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.

2. System Test - FMCS

A. General

(1) The system test fully examines the FMCS. The system test procedure includes the tests shown below: (a) Operational Test (par. 2) (b) Analog Discretes. (c) Performance Code/Performance Factors - Verification/Adjustment

Note: For all other tests, other than the Program Pin Verification (detailed

below), please refer to the associated AMM.

B. References

Reference Title

24-22-00 P/B 201 MANUAL CONTROL - MAINTENANCE PRACTICES (APPLY POWER) 34-28-01 P/B 201 INERTIAL REFERENCE SYSTEM - MAINTENANCE PRACTICES

C. Location Zones

Zone Area

101 Control Cabin - Left 102 Control Cabin - Right

D. Analog Discretes

(1) Do the prepare for test (34-62-01 – associated AMM): "Operational Test -

FMCS" if it is necessary.

(2) Make sure that the CDU display shows the FMCS BITE 1/1 page.

(3) If the CDU does not show the FMCS BITE 1/1 page, do these steps: (a) Push the INIT REF key on the CDU front panel to show the POS INIT or

PERF INIT page. (b) Push the LSK adjacent to <INDEX to show the INIT REF INDEX 1/1 page. (c) Push the LSK adjacent to MAINT> to show the MAINT BITE INDEX 1/1 page. (d) Push the LSK adjacent to <FMCS to show the FMCS BITE 1/1 page.


EFFECTIVITY

34-62-01001 (PV301) Page 502 MOD 0857 FEB 01/11


(4) Do the Program Pin Verification: (a) Push the PREV PAGE key on CDU to show the FMCS ANALOG DISC 2/4 page.

(b) Make sure the outputs on the CDU display are the same as the outputs

shown below:

Table 514

ASSUMED TEMP ENABLE

CAA FLT RULES DISABLE

CAA FLT RULES ENABLE

KILOGRAM OPTION DISABLE

MAG/TRUE MAG

OMEGA OFF

ALL AIRCRAFT PRE SB 737-34-1593 SRCE/DEST IDENT LEFT

ALL AIRCRAFT POST SB 737-34-1593 SRCE/DEST IDENT RIGHT

ALL AIRCRAFT ASPIRATED TAT DISABLE

FRQ SCAN DME DISABLE

FRQ SCAN DME ENABLE

°C/°F DEFAULT °C

EFIS INSTALLED ON

ALL AIRCRAFT; AIRPLANES WITH SOFTWARE U7.0 AND ON

NOTE: OMEGA is removed and PERF CODE 1 is added.

ALL AIRCRAFT POST SB 737-34-1593

NOTE: The SOURCE/DEST IDENT line will show RIGHT when you do a test of

the right FMC.

ALL AIRCRAFT

(c) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 3/4 page.

(d) Make sure the outputs on the CDU display are the same as the outputs

shown below: Table 515

VMO/MMO 340/.82

MAINT TEST DISABLE

ALL AIRCRAFT POST SB 737-34-1593 FMC SOURCE SEL *[1] NORMAL

ALL AIRCRAFT

*[1] The FMC SOURCE SEL line will read BOTH-ON-L when the FMC SOURCE SELECT switch is in the BOTH ON L position and BOTH-ON-R in the BOTH ON R position


EFFECTIVITY

34-62-01001 (PV301) Page 503 MOD 0857 FEB 01/11


NOTE: AIRPLANES WITH SOFTWARE UPDATE 7.X, 8.X or 10.X; MAINT TEST is removed.

NOTE: AIRPLANES WITH SOFTWARE UPDATE 10.X;

VMO/MMO is removed.

(e) Push the NEXT PAGE key on the CDU front panel to show the FMCS ANALOG DISC 4/4 page.

(f) Make sure the outputs on the CDU display are the same as the outputs

shown below:

Table 516

VOR INHIBIT DISABLE

FLIGHT NUMBER DISABLE

TOGA RW POS UPD ENABLE

TAKEOFF PROFILE DISABLE

FAA/CAA QRH SPD DISABLE

FAA/CAA QRH SPD ENABLE

TAKEOFF SPEEDS DISABLE

NAVAID SUPPRESS DISABLE

SEL CRS INHIBIT DISABLE

ACARS INSTALLED OFF

(5) Push the line select key (LSK) adjacent to <INDEX (6L) to show FMCS BITE 1/1 page.

(6) Refer to the associated AMM to continue testing, or put aircraft back to to

its usual condition.

CHAPTER

AIRBORNE AUXILIARY

POWER


EFFECTIVITY

49-72-11AIRPLANES WITH APU ELAPSED TIME INDICATOR INSTALLED Page 401 MOD 0949 FEB 01/11


ELAPSED TIME INDICATOR - REMOVAL/INSTALLATION

1. General

A. This procedure contains the removal and installation tasks for the elapsed time indicator.

B. The elapsed time indicator is installed on the left side of the oil cooler.

2. Elapsed Time Indicator Removal (Figure 401)

A. Location Zones

Zone Area

101 Control Cabin - Left 205 Electronic Compartment 703 APU Compartment

B. Access Panels

Number Name/Location

1201 Electronic Equipment Access Door 3804 APU Cowl Door - Left

C. Procedure

(1) Open this access panel:


1201 Electronic Equipment Access Door

(2) Set the switch and the circuit breaker:

(a) Set the APU master switch on the P5 forward overhead panel to the OFF

position and attach a DO-NOT-OPERATE tag.

(b) Open this circuit breaker and attach a DO-NOT-CLOSE tag:

1) E3-3 Electrical Shelf, APU Control Unit

(3) Open the APU cowl door:

(a) Open the latches for the APU cowl door.

(b) Open this access panel:


3804 APU Cowl Door - Left

(c) Connect the door support rods.


EFFECTIVITY



(4) Remove the lower shroud:

(a) Hold the lower shroud and open the shroud latches.

(b) Remove the lower shroud.

(5) Remove the elapsed time indicator:

(a) Disconnect the electrical connector from the indicator.

(b) Loosen the clamp that attaches the indicator to the bracket on the oil cooler.

1) Remove the indicator and the shockmount.

(c) Remove the screws and washers that attach the indicator to the

shockmount.

------------------------- END OF TASK ---------------------------


EFFECTIVITY



Elapsed Time Indicator Installation Figure 401


EFFECTIVITY



3. Elapsed Time Indicator Installation (Figure 401)

A. Location Zones

Zone Area

101 Control Cabin - Left 205 Electronic Compartment 703 APU Compartment

B. Access Panels


1201 Electronic Equipment Access Door 3804 APU Cowl Door - Left

C. Procedure

(1) Install the elapsed time indicator:

(a) Put the indicator in the shockmount and install the screws and washers.

(b) Put the assembled indicator in the shockmount bracket.

1) Tighten the clamp that attaches the indicator.

(c) Connect the electrical connector to the indicator.

CAUTION: KEEP A MINIMUM CLEARANCE OF 0.18 INCHES (5 MM) BETWEEN THE

ENGINE, FIRE DETECTOR, CLAMPS, AND LOWER SHROUD. BE CAREFUL WHEN YOU MOVE THE LOWER SHROUD. DAMAGE TO THE SHROUD CAN OCCUR.

(2) Install the lower shroud:

(a) Hold the lower shroud against the upper shroud.

(b) Close the shroud latches.

(3) Close the APU cowl door:

(a) Disconnect the door support rods.

(b) Put the door support rods in the clips on the APU cowl door.

(c) Close this access panel:


3804 APU Cowl Door - Left

(d) Close the latches for the APU cowl door.


EFFECTIVITY



(4) Set the circuit breaker and the switch:

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

1) E3-3 Electrical Shelf, APU Control Unit

(b) Remove the DO-NOT-OPERATE tag from the APU master switch on the P5

forward overhead panel.

(5) Close this access panel: Number Name/Location

1201 Electronic Equipment Access Door

------------------------- END OF TASK ---------------------------

Document No. AMS-737-345-28881 AIRCRAFT MANUAL … · 2017-06-16 · Document No. AMS-737-345-28881 Produced by Aerospace Design and Engineering Consultants (AeroDEC ®) Limited,

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