Boeing 737-400 - Installation of Enhanced Mode S Transponder.CHANGE BULLETIN Document No....

CHANGE BULLETIN Document No.

MOD-11350-00001 Issue 4.

Title Boeing 737-400 - Installation of Enhanced Mode S Transponder.

Change No. MOD-11350-00001.

This document contains proprietary designs, data, information and technical material that are the sole property of Aviation Traders Ltd (ATL). The information shall be considered to be confidential by the recipient and may not be shown or disclosed to any other organisation or persons.

© 2018 - ATL, 11-12 ASHLEY HEATH INDUSTRIAL ESTATE, RINGWOOD ROAD, THREE LEGGED CROSS, WIMBORNE,

DORSET, BH21 6UZ. UK. Form AS520 Issue 14. ISO 9001:2008 EASA.21J.016 UK.MAA.DAOS.0011 of 51.

1 Revision History

Issue Date Raised Issue Details Sheet(s) Affected

1 01/08/2017 Initial Issue. All

2 29/09/2017 Sect 4: MSN 29201, 29202, 29203 added to Effectivity Table.

Para 7.2: Added for equipment off (MSN 29201, 29202, 29203).

Para 10.5: MSN 29201, 29202, 29203 and ATL11350-803 added.

Para 10.25: MSN 29201, 29202, 29203 and ATL11350-803 added.

Para 10.49 References for MSN 29201, 29202, 29203 included.

Sect 11 Weight and Balance updated and split into two aircraft groups (MSN 28885 and MSN 29201, 29202, 29203).

Sect 12 ELA updated and split into two aircraft groups (MSN 28885 and MSN 29201, 29202, 29203).

Para 13.1.2 Updated to include Boeing document references for MSN 29201, 29202, 29203.



4

5

6

9

13

15-16

16-18

19

19

19

3 24/11/2017 Header Job Number was 11350-004.

Para 4. Mod issue was 1.

Para 7.1 MSN was 38885.







Para 13.1.2 MSN was 38885.

Para 13.2.3 MSN was 38885.

Para 13.4.2 MSN was 38885.

1

4

5

13

15

16

16

17

18

20

20

20

4 25/01/2018 Header Job Number was 11350-005.

Para 4: Aircraft MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 5.5 “Baro Alt. Rate” and “True Airspeed” added. Added text “(Inertial)” to Vertical Rate and text “Rate” to Track Angle .

Para 7.1 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 8.1 Ref to 822-1338-005/EASA SIB 2011-20R1 added.

Para 10.5 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 10.25 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 10.33 IST.G7490-() was Revision: 04; Dated: 01/06/2006.

Para 10.49 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

1

5

6

6

6

7

10

11

15

17


MOD-11350-00001 Issue 4.






Issue Date Raised Issue Details Sheet(s) Affected

Para 11.1 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 11.4 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 12.1 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 12.3 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 12.5 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 13.1.2 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 13.2.3 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

Para 13.4.2 MSN’s 28886, 28892, 28893, 29270, & 25097 added.

17

18

19

20

21

21

21

2 Distribution

Holder

ATL Files.

Customer.


MOD-11350-00001 Issue 4.






3 Contents

1 Revision History ............................................................................................................................................... 2

2 Distribution ....................................................................................................................................................... 3

3 Contents ............................................................................................................................................................ 4

4 Effectivity .......................................................................................................................................................... 5

5 Description of Change ..................................................................................................................................... 5

6 Concurrent Requirements ............................................................................................................................... 6

7 Parts Removed ................................................................................................................................................. 6

8 Parts Required .................................................................................................................................................. 6

9 Interchangeability of Parts .............................................................................................................................. 7

10 Accomplishment Instructions ..................................................................................................................... 7

11 Weight and Balance ................................................................................................................................... 17

12 Electrical Load Analysis ............................................................................................................................ 18

13 Publications affected ................................................................................................................................. 20

14 Instructions for Continued Airworthiness ............................................................................................... 23

15 Airworthiness Limitations ......................................................................................................................... 26

16 Conditions affecting this Approval .......................................................................................................... 26

17 Post Embodiment Actions ........................................................................................................................ 26

18 Design Occurrence Reports ...................................................................................................................... 27

19 Design Queries ........................................................................................................................................... 27

Appendix A Design Occurrence Report Template ....................................................................................... 28

Appendix B Design Query Note Template .................................................................................................... 30

Appendix C EMC Test Schedule. ................................................................................................................... 31

Appendix D TIC TR-220 Tests ........................................................................................................................ 39


MOD-11350-00001 Issue 4.






4 Effectivity

Model Registration* Serial No. Manufacturers Manual

Effectivity Code* Applicable MOD Issue

Boeing 737-490 - 28885 PJ601/023 3

Boeing 737-490 - 28886 PJ602/024 4

Boeing 737-490 - 28892 PJ608/030 4

Boeing 737-490 - 28893 PJ610/032 4

Boeing 737-490 - 29270 PJ609/031 4

Boeing 737-4Q8 - 25097 PW233/003 4

Boeing 737-4M0 - 29201 PW441/001 2

Boeing 737-4M0 - 29202 PW442/002 2

Boeing 737-4M0 - 29203 PW443/003 2

*If known

5 Description of Change

5.1 This design change replaces the existing L-3 Communications/ACSS XS-950 Transponder #1 and #2 and

associated Gables Controller G6992-45 with a pair of Rockwell Collins TPR-901 Transponders and Gables

G7490-30 Controller to introduce Elementary and Enhanced Mode ‘S’ functionality in accordance with the

requirements of EASA CS-ACNS Subpart D Sections 2 and 3.

5.2 This design change introduces the aircraft tabulated in Section 4, to the effectivity of ATL modification

ATL/737/M556, which was originally approved under EASA STC No. EASA.A.S.02817 (re-numbered by

EASA as STC No. 10014660 Revision 1).

5.3 This design change approves minor deviations from the STC approved design configuration, including

aircraft specific wiring diagram changes for the SSR Mode ‘S’ Elementary and Enhanced Surveillance

Transponder System.

5.4 The following deviations and variations from the STC approved design configuration have been identified:

Deviations are limited to connector contact ident differences between MSN’s.

The installation declares compliance against CS ACNS.D.EHS in lieu of JAA NPA 20-12a/AMC 20-13.

The P/Ns of the Transponders being removed are different from those originally removed by the STC.

5.5 The Transponder systems are modified to accept Flight ID and have the capability to down-link aircraft

derived parameters to Air Traffic Controllers (ATC).

The transponders will transmit additional data, which will be displayed to the ATC.


MOD-11350-00001 Issue 4.






The additional data will be:

Magnetic Heading.

Indicated Airspeed.

Mach Number.

Roll Angle.

Barometric Altitude Rate

Vertical Rate (Inertial).

True Airspeed.

Track Angle Rate.

True Track Angle.

Ground Speed.

Selected Altitude.

6 Concurrent Requirements

6.1 None.

7 Parts Removed

7.1 The major pieces of equipment and the quantities being removed from the aircraft are shown within the

table below (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only):

Part No. Description Qty Remarks/manufacturer

7517800-10002 Transponder XS-950 2 L-3/ACSS

G6992-45 Controller 1 Gables

7.2 The major pieces of equipment and the quantities being removed from the aircraft are shown within the

table below (MSN’s 29201, 29202, 29203 only):


622-7878-201 Transponder TPR-720 2 Rockwell Collins

622-8974-016 Controller TTC-920 1 Rockwell Collins

8 Parts Required

8.1 The major pieces of equipment and the quantities being installed onto the aircraft are shown within the

table below.


822-1338-003 or

822-1338-005

Transponder TPR-901 2 Rockwell Collins

G7490-30 Control Panel 1 Gables

8.2 All additional parts required (brackets, doublers, AGS etc.) are shown within the appropriate ATL drawings.


MOD-11350-00001 Issue 4.






8.3 There are no special tooling requirements to accomplish the embodiment of this change.

9 Interchangeability of Parts

9.1 The parts introduced by this change are not direct replacements for the originally installed parts and are not

interchangeable with the original fitted item.

9.2 The original parts removed may not be reinstalled post embodiment of this change.

10 Accomplishment Instructions

10.1 The following instructions are derived from ATL engineering Order ATL/737/E556.

Operation Description Operator Inspection

PREPARATION

10.2 Identify and comply with all warnings and cautions given in the specified and referenced manuals and instructions.

10.3 Comply with all Health and Safety and protective equipment requirements.

10.4 Isolate all electrical power to the transponder system and associated equipment.

10.5 Manufacture of Wiring Harnesses

Aircraft Serial Number Wiring Diagram Number

28885, 28886, 28892, ATL11350-802

28893, 29270, 25097

29201, 29202, 29203 ATL11350-803

With reference to wiring diagrams, prepare wire harnesses and identify in accordance with the wiring diagram. Manufacture harnesses using “BMS 13-60, Type 34, Class 2, 24 AWG for multi-core wires” and “BMS 13-60, Type 1, Class 1, 24 AWG for single core wires”.

REMOVAL / INSTALLATION OF EQUIPMENT


MOD-11350-00001 Issue 4.







10.6 Gain access to the Electronic Load Circuit Breaker Panel (P6-1).

10.7 Open circuit breaker “EFIS SYM GEN - R” identified as ‘C1114’.

Open circuit breaker “INSTRUMENT XFMR-2” identified as ‘C50’.

Open circuit breaker “WEATHER RADAR R/T” identified as ‘C120’.

Open circuit breaker “STALL WARNING NO. 2 (DC)” identified as ‘C460’.

Open circuit breaker “STALL WARNING NO. 2 (AC)” identified as ‘C461’.

Open circuit breaker “F/O - VSI” identified as ‘C687’.

Open circuit breaker “IRS NO. 2 AC” identified as ‘C1008’.

Open circuit breaker “IRS NO. 2 DC” identified as ‘C1010.

Open circuit breaker “ATC-2” identified as ‘C188.

10.8 Obtain access to the Electronic Load Circuit Breaker Panel (P6-2).

10.9 Open circuit breaker “ANCDU NO. 2” identified as ‘C1050’.

Open circuit breaker “B – FCC DC” identified as ‘C1046’.

Open circuit breaker “AFDS MCP CRS 2 DC” identified as ‘C1047’


10.11 Open circuit breaker “TCAS” identified as ‘C9030’.

Open circuit breaker “GROUND PROX WARNING” identified as ‘C629’.

Open circuit breaker “AUTOTHROTTLE AC” identified as ‘C720’.

Open circuit breaker “AUTOTHROTTLE DC” identified as ‘C721’.

Open circuit breaker “A – FCC DC” identified as ‘C1045’.

Open circuit breaker “MCP DC” identified as ‘C1044’.

Open circuit breaker “ATC-1” identified as ‘C186.



MOD-11350-00001 Issue 4.







10.13 Open circuit breaker “EFIS SYM GEN - L” identified as ‘C1110’.

Open circuit breaker “FLT REC AC” identified as ‘C109’.

Open circuit breaker “INSTRUMENT XFMR-1” identified as ‘C49’.

Open circuit breaker “IRS 1-AC” identified as ‘C1007’.

Open circuit breaker “IRS 1-DC” identified as ‘C1009’.

Open circuit breaker “ANCDU NO. 1” identified as ‘C1018’.

Open circuit breaker “STALL WARNING NO. 1 (DC)” identified as ‘C350’.

Open circuit breaker “STALL WARNING NO. 1 (AC)” identified as ‘C351’

Open circuit breaker “FMCS CMPTR” identified as ‘C1017’.

Open circuit breaker “CAPTS - VSI” identified as ‘C686’.

REMOVAL OF TRANSPONDERS

10.14 Obtain access to the E2-2 Electronic Shelf, location: Main Equipment Centre, left hand side STA 352.3.

10.15 Remove “ATC-1 Transponder” identified as ‘M163’ from its mounting tray as follows:

a) Remove any safety wire and loosen the knurled hold-down knobs securing the transponder to the tray.

b) Carefully pull the transponder forward until it is disconnected from the tray mating connector.

Refer to paragraph 7.1 for part number of Transponder.

10.16 Obtain access to the E2-4 Electronic Shelf, location: Main Equipment Centre, right hand side STA 352.3.

10.17 Remove “ATC-2 Transponder” identified as ‘M381’ from mounting tray as follows:

a) Remove any safety wire and loosen the knurled hold-down knobs securing the transponder to the tray.

b) Carefully pull the transponder forward until it is disconnected from the tray mating connector.

Refer to paragraph 7.1 for part number of Transponder.


MOD-11350-00001 Issue 4.







10.18 Label and return Transponders to stores.

REMOVAL OF ATC CONTROL PANEL

10.19 Obtain access to the P8 Electronic Panel – Aft, location: Flight Deck.

10.20 Undo the four fasteners on the front panel.

10.21 Remove locking devices (if installed) from connectors D211/J1 and D519/J2.

10.22 Remove “Transponder Control Panel” identified as ‘P8-29’ from the P8 Electronic Panel

10.23 Refer to paragraph 7.1 for part number of ATC Controller.

10.24 Label and return Controller to stores.

INSTALLATION AND TERMINATION OF WIRING HARNESS AND SUNDRY PARTS

10.25 Install new wiring in accordance with the following wiring diagrams and Boeing Standard Wiring Practices Manual Chapter: 20-10-19. Where parts are not identified on the wiring diagrams use standard parts from the aircraft IPC.

Aircraft Serial Number Wiring Diagram Number

28885, 28886, 28892, ATL11350-802

28893, 29270, 25097

29201, 29202, 29203 ATL11350-803

10.26 Carry out continuity and insulation check on all new terminated wiring.

INSTALLATION OF NEW TRANSPONDERS

10.27 Obtain two new Mode ‘S’ Transponders from kit of parts; refer to paragraph 8.1 for part numbers. Note EASA SIB 2011-20R1.


MOD-11350-00001 Issue 4.







10.28 Obtain access to the E2-2 Electronic Shelf, location: Main Equipment Centre, left hand side STA 352.3.

10.29 Install “ATC-1 Transponder” identified as ‘M163’ into mounting rack in accordance with Rockwell Collins TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70; Dated: Apr 27, 2006; Revision: 17; Page: 421; Paragraph: 2. F (1). Refer to paragraph 8.1 for part number of Transponder.

10.30 Obtain access to the E2-4 Electronic Shelf, location: Main Equipment Centre, right hand side STA 352.3.

10.31 Install “ATC-2 Transponder” identified as ‘M381’ into mounting rack in accordance with Rockwell Collins TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70; Dated: Apr 27, 2006; Revision: 17; Page: 421; Paragraph: 2. F (1). Refer to paragraph 8.1 for part number of Transponder.

INSTALLATION OF NEW ATC CONTROL PANEL

10.32 Obtain access to the P8 Electronic Panel – Aft, location: Flight Deck.

10.33 Install “Transponder Control Panel” identified as ‘P8-29’ into the P8 Electronic Panel – Aft in accordance with Gables Installation Manual for Flight ID / ATC / TCAS Control Panel – Document: IST.G7490-(); Revision: 07; Dated: 04 September 2009; Page: 201; Paragraph: 2.B. Refer to paragraph 8.1 for part number of ATC Control Panel.

PREPARATION OF AIRCRAFT FOR TESTING

10.34 Check all disturbed electrical harnesses, connectors, back-shells, terminal modules for security and non-obstruction of aircraft components.

10.35 Bonding tests to be carried out between the newly installed or moved components and aircraft structure (maximum value of 0.01 Ohms) and figures recorded.


MOD-11350-00001 Issue 4.







10.36 Check working area for integrity of disturbed units, wires and panels.

10.37 Re-install any panels and items removed for installation purposes in accordance with the Aircraft Maintenance Manual.

10.38 Prepare aircraft to carry out system check.

GROUND TESTS

10.39 Close Circuit Breakers as follows:

Obtain access to the Electronic Load Circuit Breaker Panel (P6-1).

Close circuit breaker “EFIS SYM GEN - R” identified as ‘C1114’. Close circuit breaker “INSTRUMENT XFMR-2” identified as ‘C50’. Close circuit breaker “WEATHER RADAR R/T” identified as ‘C120’. Close circuit breaker “STALL WARNING NO. 2 (DC)” identified as ‘C460’. Close circuit breaker “STALL WARNING NO. 2 (AC)” identified as ‘C461’ Close circuit breaker “F/O - VSI” identified as ‘C687’. Close circuit breaker “IRS NO. 2 AC” identified as ‘C1008’. Close circuit breaker “IRS NO. 2 DC” identified as ‘C1010. Close circuit breaker “ATC-2” identified as ‘C188.


Close circuit breaker “ANCDU NO. 2” identified as ‘C1050’. Close circuit breaker “B – FCC DC” identified as ‘C1046’. Close circuit breaker “AFDS MCP CRS 2 DC” identified as ‘C1047’.


Close circuit breaker “TCAS” identified as ‘C9030’. Close circuit breaker “GROUND PROX WARNING” identified as ‘C629’. Close circuit breaker “AUTOTHROTTLE AC” identified as ‘C720’. Close circuit breaker “AUTOTHROTTLE DC” identified as ‘C721’. Close circuit breaker “A – FCC DC” identified as ‘C1045’. Close circuit breaker “MCP DC” identified as ‘C1044’. Close circuit breaker “ATC-1” identified as ‘C186’.


MOD-11350-00001 Issue 4.








Close circuit breaker “EFIS SYM GEN - L” identified as ‘C1110’. Close circuit breaker “FLT REC AC” identified as ‘C109’. Close circuit breaker “INSTRUMENT XFMR-1” identified as ‘C49’. Close circuit breaker “IRS 1-AC” identified as ‘C1007’. Close circuit breaker “IRS 1-DC” identified as ‘C1009’. Close circuit breaker “ANCDU NO. 1” identified as ‘C1018’. Close circuit breaker “STALL WARNING NO. 1 (DC)” identified as ‘C350’. Close circuit breaker “STALL WARNING NO. 1 (AC)” identified as ‘C351’ Close circuit breaker “FMCS CMPTR” identified as ‘C1017’. Close circuit breaker “CAPTS - VSI” identified as ‘C686’.

FUNCTION TESTING

10.43 In accordance with Rockwell Collins TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70; Dated: Apr 27, 2006; Revision: 17, perform the following test procedure:

a) Adjustment / Test Section, Page: 506; Paragraph: 2. D, Transponder Self-Test.

10.44 In accordance with Gables Installation Manual for Flight ID / ATC / TCAS Control Panel – Document: IST.G7490-(); Revision: 04; Dated: 01 June 2006 or IST.G7492-(); Revision: 03; Dated: 01 June 2006; perform the following test procedure:

a) Post Installation Check, Page: 301; Paragraph: 3.B, Procedures.

b) Note: For Gables P/N G7490-40, it is not required that step 3.B.(2), step 3.B.(7), step 3.B.(8), or 3.B.(9) be performed. For P/N G7490-40 perform the following additional steps instead:

1. Verify that pressing the “ALT” key causes the Altitude source selection to toggle between altitude source 1 (ADC1) and altitude source 2 (ADC2).

2. Verify that after approximately five seconds have passed after step 1 that an ATC or Flight ID code is shown in the display.


MOD-11350-00001 Issue 4.







10.45 In accordance with TIC TR-220 Multifunction Test Set, document no. 90008088-1, Revision D, 01 July 2005, perform the following procedures to test the operation of the transponders in Appendix D:

a) Paragraph 2.12, Transponder Manual Sequence of Tests.

b) Paragraph 2.14, Testing a Transponders ‘IDENT’ Function, and

c) Paragraph 2.17, Mode S Enhanced Surveillance

Enter the results on the Test Results pages which can be found in Appendix ‘D’ of this document.

Copy of Appendix ‘D’ results pages to be sent to ATL.

10.46 ALTERNATIVE TEST SET

In accordance with Aeroflex IFR 6000 Test Set; Document No: 1002-5800-2PO; Revision: 4; Dated: Jan 2006, perform the following procedures to test the operation of the transponders:

a) Section 1 - Description

Paragraph 2.2 General Set-up

Paragraph 2.3 Transponder Set-up - Antenna

Paragraph 2.4 Transponder Set-up – Direct Connect

Paragraph 2.5 Transponder Testing

b) Section 2 - Operation

Paragraph 4.3 Transponder

Note: Aeroflex ATC-601-2 Ramp Test Set with software version 3.0 or later; Document No: 1002-8106-200; Issue: 3; Dated: November 2004 may be used as an alternative to the IFR 6000 Test Set.

10.47 Ensure that the Enhanced Mode ‘S’ ATC Transponders do not transmit whilst aircraft is on the ground.

10.48 The above function tests ensure correct operation of the Enhanced Mode ‘S’ ATC Transponder System.

ADDITIONAL FUNCTION TESTING


MOD-11350-00001 Issue 4.







10.49 Perform operational tests for the following systems in accordance with the Aircraft Maintenance Manual to check the integrity of any disturbed systems after completion of the Enhanced Mode ‘S’ ATC Transponder wiring connections, using the following documents:

Boeing AMM: D6-37584; Dated: 30 May 2017; Temporary Revision: 34-1009; (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only); D6-39033; Dated Sep 25/2016 (MSN’s 29201, 29202, 29203 only).

Boeing Aircraft Wiring Diagram Manual: D6-9125Y; Dated: 07 Dec 2016; Revision: 52; (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only); D6-9129R; Dated: Mar 09/2012 (MSN’s 29201, 29202, 29203 only).

Equipment System ATA Pages Paragraphs Configuration

Reference Reference Chapter

M196 Digital Air Data

Computer 1

22-06-10 102 3 - M368 Digital Air Data

Computer 2

M1506 Stall Management

Computer 1

22-06-10 102 5 - M1507 Stall Management

Computer 2

M198 DFCS Mode

Control Panel

22-11-34 501 -502 1.2.A-C -

M924 Flight Control

Computer “A”

22-11-01 501-513 1-2 A-K - M923 Flight Control

Computer “B”

M917 Autothrottle

Computer

22-31-10 501-503 1-2 -

M1161 Inertial Reference

Unit 1

34-28-01 501-510 1-2 - M1162 Inertial Reference

Unit 2

M1319 Left Electronic

Flight Instrument

System Symbol

Generator

34-22-00 501-535 1-4 -

M1321 Right Electronic

Flight Instrument


MOD-11350-00001 Issue 4.







System Symbol

Generator

M675 Digital Flight Data

Acquisition Unit

31-24-05 501-503 1-2

N75 Captain’s

Vertical Speed

Indicator

34-28-91 402-403 3.C. (3) – (6) - N76 First Officer’s

Vertical Speed

Indicator

M1175 Flight Management

Computer 1

34-62-01 501-526 1-3 - M1632 Flight Management

Computer 2

M1163 Digital / Analogue

Adaptor 1

34-28-41 405-408 3.C. (3) – (14) - M1164 Digital / Analogue

Adaptor 2

M652 Ground Proximity

Computer

34-42-01 501-508 1-3

-

M101 Weather Radar

Receiver /

Transmitter

34-41-02 501-514 1-4 -

M1485 TCAS 34-45-00 501-527 1-6 2

M1854 HGS Computer (if

installed/activated)

Ensure no flags or failure indications

10.50 Perform EMC Tests in accordance with the procedures in Appendix ‘C’ to check there is no interference between the new equipment installation and existing systems. The EMC test is only required to be carried out on the first of a particular model of aircraft in an Operator's fleet.

Enter the results on the Test Results pages which can be found in Appendix ‘C’ of this document.

Copy of Appendix ‘C’ results pages to be sent to the ATL design office.


MOD-11350-00001 Issue 4.







10.51 Carry out checks to ensure that all tooling and unused/removed parts are accounted for and removed from the aircraft at the completion of the change.

11 Weight and Balance

11.1 The major equipment/parts removed by the embodiment of this change has the following effect on the

aircraft weight and balance (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only):

Part Number Qty Weight (lb) Station (in) Moment (lb in)

Remarks

7517800-10002 2 -11.5 352.3 -4051.45

G6992-45 1 -2.0 210.0 -420.0

Total -25.0 - -8522.90

11.2 The major equipment/parts removed by the embodiment of this change has the following effect on the

aircraft weight and balance (MSN’s 29201, 29202, 29203 only):


Remarks

622-7878-201 2 -12.0 352.3 -4227.6

622-8974-016 1 -2.0 210.0 -420.0

Total -26.0 - -8875.2

11.3 The major equipment/parts installed by the embodiment of this change has the following effect on the

aircraft weight and balance (all aircraft):


Remarks

822-1338-003 2 +13.8 352.3 4861.74

G7490-30 1 +2.5 210.0 525.0

Total +30.1 - 10248.48

11.4 The major equipment/parts removed and installed by the embodiment of this change has the following

overall effect on the aircraft weight and balance (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097

only):

Weight (lb) Station (in) Moment (lb in)

Remarks

+5.1 338.35 +1725.58 Increase


MOD-11350-00001 Issue 4.






11.5 The major equipment/parts removed and installed by the embodiment of this change has the following

overall effect on the aircraft weight and balance (MSN’s 29201, 29202, 29203 only):

Weight (lb) Station (in) Moment (lb in)

Remarks

+4.1 334.95 +1373.28 Increase

11.6 The above total weight and balance change calculations may be affected other miscellaneous items

detailed in paragraphs 7 and 8 of this document.

11.7 It is the responsibility of the operator to ensure that the aircraft weight and balance schedule is

updated to include the changes introduced by the embodiment of this aircraft change.

12 Electrical Load Analysis

12.1 The following electrical loads are removed from circuit breakers and electrical buses by the embodiment of

this change (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only):

CB No. Description Bus Load (A)

Remarks

C186 7517800-10002 115V AC ELEX PWR-1 0.74 XS-950

C188 7517800-10002 115V AC ELEX PWR-2 0.74 XS-950

C186 G6992-45 115V AC ELEX PWR-1 0.02 Controller (D211 input)


Totals 115V AC ELEX PWR-1 0.76 removed

115V AC ELEX PWR-2 0.76 removed


MOD-11350-00001 Issue 4.






12.2 The following electrical loads are removed from circuit breakers and electrical buses by the embodiment of

this change (MSN’s 29201, 29202, 29203 only):


Remarks

C186 622-7878-201 115V AC STBY BUS 0.32 TPR-720

C188 622-7878-201 115V AC ELEX BUS 2 0.32 TPR-720

C186 622-8974-016 115V AC STBY BUS 0.02 TTC-920 (D211 input)

C188 622-8974-016 115V AC ELEX BUS 2 0.02 TTC-920 (D519 input)

Totals 115V AC STBY BUS 0.34 removed

115V AC ELEX BUS 2 0.34 removed

12.3 The following electrical loads are added to circuit breakers and electrical buses by the embodiment of this

change (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only):


Remarks

C186 822-1338-003 115V AC ELEX PWR-1 0.43 TPR-901

C188 822-1338-003 115V AC ELEX PWR-2 0.43 TPR-901



Totals 115V AC ELEX PWR-1 0.45 added

115V AC ELEX PWR-2 0.45 added

12.4 The following electrical loads are added to circuit breakers and electrical buses by the embodiment of this

change (MSN’s 29201, 29202, 29203 only):


Remarks

C186 822-1338-003 115V AC STBY BUS 0.43 TPR-901

C188 822-1338-003 115V AC ELEX BUS 2 0.43 TPR-901

C186 G7490-30 115V AC STBY BUS 0.02 Controller (D211 input)

C188 G7490-30 115V AC ELEX BUS 2 0.02 Controller (D519 input)

Totals 115V AC STBY BUS 0.45 added

115V AC ELEX BUS 2 0.45 added


MOD-11350-00001 Issue 4.






12.5 The load change to aircraft electrical buses is calculated as being (MSN’s 28885, 28886, 28892, 28893,

29270, & 25097 only):

Bus Load (A)

Remarks

115V AC ELEX PWR-1 -0.31 Decrease

115V AC ELEX PWR-2 -0.31 Decrease

12.6 The load change to aircraft electrical buses is calculated as being (MSN’s 29201, 29202, 29203 only):

Bus Load (A)

Remarks

115V AC STBY BUS +0.11 Increase

115V AC ELEX BUS 2 +0.11 Increase

12.7 The effect of this change on the aircraft’s electrical generating and power supply system is considered to

be negligible.

12.8 It is the responsibility of the operator to ensure that the Electrical Load Analysis is updated to

include the changes introduced by this change.

13 Publications affected

The following documents are assessed as being affected by the embodiment of this design change:

Document Reference

Title Paragraph and Page Reference

ATL Document Reference

Aircraft Flight Manual (AFM) 13.1

Illustrated Parts Catalogue (IPC) 13.3

Minimum Equipment List (MEL) 13.6

Weight and Balance Manual (WBM) 11

Electrical Load Analysis (ELA) 12

Documents within ICA (Refer to FAA Order 8110.54A)

Aircraft Maintenance Manual (AMM) 13.2

Wiring Diagram Manual (WDM) 13.4

Maintenance Schedule 13.5

13.1 Aircraft Flight Manual

13.1.1 ATL AFM Supplement No. 11350-AFM-00001, (SSR Mode ‘S’ Elementary and Enhanced Surveillance) to

be inserted in the Aircraft Flight Manual for Boeing 737-400.


MOD-11350-00001 Issue 4.






13.1.2 Boeing Document Reference: D6-8734.490; Rev 34; Dated: 12-05-16 (MSN’s 28885, 28886, 28892,

28893, 29270, & 25097 only); D6-8734.4M02 dated 03-23-16 (MSN’s 29201, 29202, 29203 only).

13.1.3 It is the operator’s responsibility to ensure that the AFM Supplement is inserted into the appropriate AFM

and the relevant record pages amended.

13.2 Aircraft Maintenance Manual

13.2.1 Information that is required for the update of the AMM is contained in Section 14 of this document and is

provided to the operator to enable the compilation of a supplement to the existing AMM. Supplements

produced for the AMM must be provided to ATL for verification and approval prior to issue into the

manual. Pending the availability of the supplementary data, this document may be placed into the AMM

as an appendix until the manual is updated.

13.2.2 The transponders and control panel are considered on-condition units and no additional maintenance is

required with the exception of those called up in paragraphs, 13.5 - Maintenance Schedule, and 14.0 -

Continued Airworthiness for Inclusion into the Aircraft Maintenance Manual.

13.2.3 Boeing Document Reference: D6-37584 (MSN’s 28885, 28886, 28892, 28893, 29270, & 25097 only); D6-

39033 (MSN’s 29201, 29202, 29203 only).

13.3 Illustrated Parts Catalogue

13.3.1 It is the operator’s responsibility to ensure that the IPC Supplement is updated and added to the aircraft

documentation, using information contained in paragraphs 7.1 and 8.1.

13.4 Wiring Diagram Manual

13.4.1 Wiring diagrams called up by this modification action to be inserted in the respective Aircraft Wiring

diagram Manual.

13.4.2 Boeing Document Reference: D6-9125Y; Rev 52; Dated: 07 Dec 2016 (MSN’s 28885, 28886, 28892,

28893, 29270, & 25097 only); D6-9129R Dated: Mar 09/2012 (MSN’s 29201, 29202, 29203 only).

13.5 Maintenance Schedule

13.5.1 Information that is required for the update of the Maintenance Schedule is contained in paragraph 14. A

revision to the existing Maintenance Schedule shall be produced by the operator. Alternatively this

document may be placed into the Maintenance Schedule as an appendix until the document is updated.

13.6 Minimum Equipment List

13.6.1 The following is to be incorporated in the Boeing 737-400 MEL at latest revision (XX); Page 34-(YY) to

replace the existing entry.


MOD-11350-00001 Issue 4.






AIRCRAFT Revision No XX Page

Boeing B737-400 Date dd/mm/yy 34-(YY)

(1) System and Sequence Numbers (2) Rectification Interval

Item (3) Number installed

(4) Number required for despatch

(5) Remarks or exceptions

34 NAVIGATION

-18 ATC Transponders and Automatic Altitude Reporting Systems.

D 2 1 Any in excess of one may be inoperative.

-18-1 Elementary Surveillance Capability.

A - 0 May be inoperative for one flight provided permission is obtained from the Air Navigation Service Provider(s) to fly in the airspace when Elementary Surveillance capability is required for the intended route.

Note 1: A serviceable Mode ‘S’ Transponder providing at least Elementary Surveillance is required for TCAS operation. Refer to item 34-40 below for dispatch with TCAS inoperative.

Note 2: At least Elementary Surveillance capability is required (to provide altimetry data) for flight into RVSM airspace.

-18-2 Enhanced Surveillance Capability.

C - 0 One or more Down-linked Aircraft Parameters (DAPs), which provide Enhanced Surveillance, may be unserviceable, provided that:

a) Operations do not specifically require their use.

Note 1: A serviceable Mode ‘S’ Transponder providing at least Elementary Surveillance is required for TCAS operation. Refer to item 34-40 below for dispatch with TCAS inoperative.

Note 2: At least Elementary Surveillance capability is required (to provide altimetry data) for flight into RVSM airspace.


MOD-11350-00001 Issue 4.






13.7 It is the operator’s responsibility to ensure that aircraft manuals affected by this modification are amended

as appropriate.

13.8 All approved manual amendments/changes made as a result of data contained in this modification must be

verified by ATL.

14 Instructions for Continued Airworthiness

14.1 Introduction

14.1.1 The influence of the modification on Airworthiness Directive, Service Bulletin eligibility and other data

must be considered and the publications monitored accordingly. The maintenance schedule for the

aircraft should include reference to this material in addition to the original design. Coordination is the

responsibility of the operator.

14.2 Overview

14.2.1 This section establishes compliance with CS 25.1529, and CS 25 Appendix H (Instructions for Continued

Airworthiness) for the introduction of Elementary and Enhanced Mode ‘S’ on the subject Boeing 737

series aircraft. The maintenance instructions set out in this section are to be incorporated by the operator

into the respective aircraft maintenance manuals, and scheduled maintenance programs.

14.3 Aeroplane Maintenance Manual

14.3.1 Refer to Rockwell Collins TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70;

Dated: Apr 27, 2006; Revision: 17

14.3.2 Refer to Document number: CPN 523-0805869; Dated: July 10, 2004; Revision: 10, Declaration of

Design and Performance TPR-901 ATCRBS / Mode ‘S’ Transponder.

14.3.3 Refer to Gables Engineering Installation Manual for Flight ID/ATC/TCAS Control Panel, Document

IST.G7490-( ), Revision 01, 28 June 2004.

14.3.4 Refer to Test Equipment Manual TIC TR-220 Multifunction Test Set, Document No. 90008088-1,

Revision D, 01 July 2005 or Alternative Test Sets – Aeroflex IFR 6000 Test Set; Document No: 1002-

5800-2PO; Revision: 4; Dated: Jan 2006 or Aeroflex ATC-601-2 Ramp Test Set with software version 3.0

or later; Document No: 1002-8106-200; Issue: 3; Dated: November 2004.

14.3.5 Installation of the Transponder on the aircraft by Supplemental Type Certificate (STC) obligates the

aircraft Operator to include the maintenance information supplied by the above manual/s in the operator’s

Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.

14.3.6 Extracting appropriate data from the above manuals, the Operator shall insert information and data to the

extent necessary for maintenance or preventive maintenance. This shall include the following:


MOD-11350-00001 Issue 4.






14.3.6.1 An introduction to the new Transponder system’s features/components.

14.3.6.2 A description of the new Transponder system’s features including Basic control and operation

information describing how the new components and systems are controlled and how they operate,

including any special procedures and limitations that apply.

14.3.6.3 Maintenance and testing instructions, as detailed in the following paragraph.

14.4 Maintenance Instructions

14.4.1 Amend Chapter 34-53-02; Page 517; Task 34-53-00-730-804; paragraph 6 of the Aircraft Maintenance

Manual with the additional information provided in the manufacturer’s manuals as listed in the table

below.

AMM Section Refer to

Rockwell

Collins TCAS II

(TPR-901)

Manual

Refer to TIC-

220 Test

Equipment

Manual

Refer to IFR

6000 Test

Equipment

Manual

Refer to

Aeroflex

ATC-601-2

Test Equip-

ment Manual

ATC System –

Description

and Operation

Para 4.1.2.2.3.3

Pages 4-6

through 4-11

N/A Section 1;

Para 1; 2.1; 2.2;

2.3; 2.4 and 2.5

Section 2:

Para 1; 2; 3;

4.1; 4.2 and 4.3

Section 1 Para 2.2 Para 2.3 Para 2.4 Para 2.5

ATC System –

Trouble-

shooting

Para 5.3

Pages 5-30

through 5-47

N/A N/A N/A

ATC System –

System Test

Para 5.2

Pages 5-1

through 5-30

Para 2.11 page

2-13;

Para 2.12 page

2-14;

Para 2.12.1

page 2-14;

Para 2.12.2

page 2-1;

Para 2.13 page

2-23;

Para 2.13.1

page 2-23;

Para 2.13.2

page 2-25;

Para 2.14 page

2-27;

Para 2.17 page

2-42.

Section 1; Para

1; 2.1; 2.2; 2.3;

2.4 and 2.5

Section 2: Para

1; 2; 3; 4.1; 4.2

and 4.3

N/A


MOD-11350-00001 Issue 4.






14.4.2 The Transponder is considered as an on-condition unit, additional maintenance is required as a check for

security and operation at normal inspection intervals, as detailed above.

14.4.3 Transponder system LRU’s can only be repaired at a factory authorised repair centre.

14.4.4 Once LRU is repaired, reinstall the LRU in to the aircraft in accordance with the approved data or

installation instructions. A ‘return to service’ test of the system is required and approval for ‘return to

service’.

14.5 Scheduled Maintenance

14.5.1 The influence of the modification on Airworthiness Directive, Service Bulletin eligibility and other data

must be considered and the publications monitored accordingly. The maintenance schedule for the

aircraft should include reference to this material in addition to the original design. Coordination is the

responsibility of the operator.

14.5.2 The following Mode ‘S’ Transponder procedures are to be incorporated in the Maintenance Schedule for

the aircraft:

14.5.3 The Transponders have been designed as on-condition units and no additional maintenance is required.

14.5.4 The Control Panels have been designed as on-condition units and no additional maintenance is required.

14.5.5 Pre-flight operation of the manual self-test function is to be performed, to confirm operation of the

Transponders.

14.5.6 Perform maintenance test to check the ICAO 24 bit airframe address, in the event of a change of state of

registration of the aircraft.

14.5.7 After major aircraft maintenance check, whenever the system wiring and / or connections have been

disturbed; the operation of the Transponders should be checked using suitable ramp test equipment. In

accordance with Boeing Standard Practices, confirm that the transponders perform according to the

Operator's Approved Maintenance Program. Refer to Boeing AMM; Chapter 34-53-02; Page: 501 et seq.

14.5.8 Perform maintenance tests every 2 years to verify aircraft derived data including the ICAO 24 bit airframe

address, elementary parameters and enhanced surveillance parameters using suitable ramp test

equipment.

14.5.9 Perform annual maintenance inspection checks of the Transponders to ensure there is no damage to the

external surfaces, the units are properly installed, retaining mechanisms are securely fastened and that

all connections to the mounting trays are properly mounted and secured.

14.5.10 All Approved Manual amendments/changes made as a result of data contained in this modification must

be verified by ATL.

14.6 Electrical Wiring Interconnection System (EWIS)

14.6.1 An EWIS assessment has been conducted by ATL, and the results of the assessment have been

compared with the latest revision of the Boeing Maintenance Review Board Report, Boeing 737, Revision

July 2010 and applicable Maintenance Schedule tasks and intervals.


MOD-11350-00001 Issue 4.






14.6.2 From the above assessment, the following EWIS Maintenance Tasks have been identified as being

applicable in the affected zone.

MRB

ITEM

NUMBER

TASK TASK DESCRIPTION INTERVAL

20-028 RST Restore (Clean) the Electronic Compartment (EZAP). 1D

20-030 DET Inspect (Detailed) the EWIS behind the electronic

equipment racks. (EZAP).

1D

20-095 GVI Inspect (General Visual) all visible EWIS in the

Electrical Compartment (EZAP).

1D

14.6.3 Since the frequency of the existing EWIS ICA tasks either matches or exceeds the findings of ATL’s

EWIS assessment, it has been concluded that the tasks in the Electrical Wiring Interconnection Systems

(EWIS) Instructions for Continued Airworthiness (ICA) documents for the subject Boeing 737 ensures that

the EWIS components or wiring introduced by this design change will be inspected sufficiently to ensure

continuous airworthiness.

15 Airworthiness Limitations

15.1 This section must set forth each mandatory replacement time, structural inspection interval, and related

structural inspection procedure approved under CS 25.571, and any mandatory replacement time of EWIS

components as defined in CS 25.1701.

15.2 There are no new airworthiness limitations introduced by this change and no existing airworthiness

limitations affected by this change.

15.3 The Airworthiness Limitations Section is approved and variations must also be approved.

16 Conditions affecting this Approval

16.1 The compatibility of this Change with other previously approved changes or repairs installed on the effective aircraft has been assessed by ATL during the design process. However, where the potential for interactions between modifications exists the installer must seek the advice of the Design Organisation, the National Authority or EASA.

16.2 In addition to the actions required by the procedures for release to service following maintenance or modification, all actions and ground test procedures specified by the accomplishment instructions must be completed, prior to signing the Certificate of Release to Service.

17 Post Embodiment Actions

17.1 Record the accomplishment of this change in the Aircraft Modification Records.


MOD-11350-00001 Issue 4.






18 Design Occurrence Reports

18.1 Any failure, malfunction, defect or other occurrence related to this change, which has resulted in or may

result in an unsafe or hazardous condition must be communicated to the ATL design organisation. A

confirmation of receipt shall be requested. Notification shall be provided to ATL using the template shown

at Appendix A as soon as possible after the condition has been identified. Initial notification may be made

by phone, e-mail or similar means if the completed template document is unable to be sent immediately.

19 Design Queries

19.1 Any queries related to this change must be communicated to the ATL design organisation. Notification shall

be provided to ATL using the template shown at Appendix B as soon as possible after the Query has been

identified.


MOD-11350-00001 Issue 4.






Appendix A Design Occurrence Report Template


MOD-11350-00001 Issue 4.







MOD-11350-00001 Issue 4.






Appendix B Design Query Note Template


MOD-11350-00001 Issue 4.






Appendix C EMC Test Schedule.

1. INTRODUCTION:

This Test Schedules details EMC tests to be carried out on newly installed Transponders and Control

Panel.

The tests that follow are:

a) Exported EMC tests, (New Emitter versus Susceptors) that ensure other aircraft systems are not adversely affected by operation of newly installed equipment. See Table 2.

b) Imported EMC tests, (Emitters versus New Susceptors) that ensure newly equipment is not adversely affected by operation of other aircraft system. See Table 3.

2. SAFETY PROCEDURES

Observe aircraft and electrical precautions at all times as detailed in the Aircraft Maintenance Manual.

3. EXPORTED EMC TEST:

a) Before performing these tests all aircraft access panels must be closed and the ground power unit available. Ensure that the aircraft is positioned away from personnel and buildings. Note: certain tests will require engine runs.

b) Carry out this test for the following new emitters:

i. Elementary and Enhanced Mode ‘S’ Left Transponder System.

ii. Elementary and Enhanced Mode ‘S’ Right Transponder System.

c) Enter all results on the relevant test result sheet (Table 2).

4. IMPORTED EMC TEST:

a) Before performing these tests all aircraft access panels must be closed and the ground power unit available. Ensure that the aircraft is positioned away from personnel and buildings.

b) Carry out this test for the following new susceptors:

a. Elementary and Enhanced Mode ‘S’ Left Transponder System.

b. Elementary and Enhanced Mode ‘S’ Right Transponder System.

c) Enter all results on the relevant test result sheet (Table 3).

5. HOW TO USE THE EMC MATRICES

1. Follow the setup procedure page at the beginning of each table. Carry out the tests in an order that suits minimal observation, re-tuning/adjusting of test sets and systems.

2. For the newly installed Emitter, complete Table 1 and record the results of the test. Delete all the systems that are not installed in the aircraft under test by inserting “N/A” in the Frequency / Mode column. Add to the table any systems not listed. If necessary seek advice from ATL Design Office as to necessity and operation / frequencies etc.


MOD-11350-00001 Issue 4.






3. Monitor the system(s) for interference. Insert in table a dash if there is no interference. If there is interference, indicate as precisely as possible the amount of movement of indicators, noise on the audio or corruption of data by recording on a separate sheet.

4. If there is any interference found, contact ATL Design Office for a decision on the acceptability of the specific case.

6. COMPLETION

1. Remove power from the systems and return aircraft to operational status.

2. A copy of the completed test schedule should be attached to the relevant aircraft documentation.

3. Following satisfactory completion of all tests, return a copy of the test schedule to ATL Design Office.

SETUP PROCEDURE FOR NEW EMITTERS VERSUS SUSCEPTORS

Susceptors are here grouped under types for the purpose of defining set-up procedures.

TYPE A SUSCEPTOR

Set-Up Tune system to a free/unused frequency within the required band and select the

relevant audio on the pilot’s or co-pilot’s audio selector panel.

Tune system to a used frequency within the required band and select the relevant

audio on the pilot’s or co-pilot’s audio selector panel.

During test disable squelch by either:

i) Adjusting squelch control

ii) Pressing test button

iii) Using an RF signal generator connected to an aerial to lift the squelch. Set

signal level to approx. 3dB above squelch threshold.

Monitoring Listen to the audio signal for any interference imposed by the emitter.

TYPE B SUSCEPTOR

Set-Up Tune the system to the frequency required, select all indications on the relevant

instruments and if applicable select the relevant audio on the pilot’s or co-pilot’s

audio selector panel.

Energise the system using the relevant test equipment.

Monitoring Monitor all indications and audio for any deviations/interference caused by the

emitter.

TYPE C SUSCEPTOR

Set-Up Activate system into normal operational mode and if applicable select the relevant

audio on the pilot’s or co-pilot’s audio selector panel.

Monitoring Monitor all indications for any deviations caused by the emitter.


MOD-11350-00001 Issue 4.






TYPE D SUSCEPTOR

Set-Up Activate system into normal operational mode.

For FDR recordings to be achieved, the aircraft Air/Ground switch must be set to

“Air”, and at least one engine is running. It is recommended that in order for a

suitable duration of recording to be obtained, that an FDR System. The FDR

recording is to be downloaded and sent for analysis.

Monitoring Analyse CVR and FDR recordings for interference.

TYPE E SUSCEPTOR

Set-Up Start main engines and APU, bring generators on-line.

Monitoring Monitor all indications for any deviations caused by the emitter.

NOTES 1) The transmissions frequencies to be used in Table 2 shall be chosen from the

following ranges LOW, MID and UPP, as specified in Table 1. A free/unused

frequency shall be chosen.

a. Enter the actual frequency used in the FREQ/MODE column.

SETUP PROCEDURE FOR EXISTING EMITTERS VERSUS NEW SUSCEPTORS

Emitters are grouped under types for the purpose of defining set-up procedures.

TYPE A EMITTER

Set-Up Tune system to free/unused frequency within the required band and select the

relevant system for transmission on an audio selector panel. Monitor the frequency

to ensure that it is clear and then transmit a test call. Ensure that the duty cycle of

the transmitter is not exceeded.

TYPE B EMITTER

Set-Up Key the system at an audio selector panel and speak into the microphone.

TYPE C EMITTER

Set-Up Tune the system to the frequency required and energise the system if necessary

using the relevant test set.

TYPE D EMITTER

Set-Up Operate/switch the system ON and OFF.

MONITORING Monitor the indications and data of the new susceptor for interference caused by the

existing aircraft emitters.


MOD-11350-00001 Issue 4.






TABLE 1 – TRANSMISSION FREQUENCY RANGES

TX SYSTEM LOW MIDDLE UPPER

VHF RX 119-121 MHz 126-128 MHz 134-136 MHz

HF RX 3-5 MHz 14-16 MHz 25-27MHz

UHF RX 238-242 MHz 306-310 MHz 384-388 MHz

TABLE 2 – EXPORTED EMC TEST

AIRCRAFT SUSCEPTOR NEWLY INSTALLED EMITTER(S)

DESCRIPTION FREQ/MODE TYPE Mode ‘S’ No. 1 Mode ‘S’ No. 2

VHF1 RX LOW MHz A.1

VHF1 RX MID MHz A.1

VHF1 RX UPP MHz A.1

VHF2 RX LOW MHz A.1

VHF2 RX MID MHz A.1

VHF2 RX UPP MHz A.1

HF1 RX LOW MHz A.1

HF1 RX MID MHz A.1

HF1 RX UPP MHz A.1

HF2 RX LOW MHz A.1

HF2 RX MID MHz A.1

HF2 RX UPP MHz A.1

UHF1 RX LOW MHz A.1

UHF1 RX MID MHz A.1

UHF 1 RX UPP MHz A.1

UHF 2 RX LOW MHz A.1

UHF 2 RX MID MHz A.1


VHF1 RX LOW MHz A.2

VHF1 RX MID MHz A.2

VHF1 RX UPP MHz A.2

VHF2 RX LOW MHz A.2


MOD-11350-00001 Issue 4.








VHF2 RX MID MHz A.2

VHF2 RX UPP MHz A.2

HF1 RX LOW MHz A.2

HF1 RX MID MHz A.2

HF1 RX UPP MHz A.2

HF2 RX LOW MHz A.2

HF2 RX MID MHz A.2

HF2 RX UPP MHz A.2

UHF1 RX LOW MHz A.2

UHF1 RX MID MHz A.2





DME 1 108.40 MHz B

DME 1 113.75 MHz B

DME 1 116.90 MHz B

DME 2 108.40 MHz B

DME 2 113.75 MHz B

DME 2 116.90 MHz B

NAV 1 (ILS) 108.50 MHz B






ADF 1 LOW FREQ C

ADF 1 MID FREQ C

ADF 1 HI FREQ C

ADF 2 LOW FREQ C

ADF 2 MID FREQ C


MOD-11350-00001 Issue 4.








ADF 2 HI FREQ C

MARKER 1 HIGH B

MARKER 2 HIGH B

FMS GPS 1 INDICATION C

FMS GPS 2 INDICATION C

FLT DIRECTOR 1 HEADING C

FLT DIRECTOR 1 VOR B

FLT DIRECTOR 1 LOC/GS B

FLT DIRECTOR 2 HEADING C

FLT DIRECTOR 2 VOR B

FLT DIRECTOR 2 LOC/GS B

STANDBY COMPASS INDICATION C

AUTO-PILOT/YAW DAMPER INDICATION C

PILOT AUDIO INTERCOM A

CO-PILOT AUDIO INTERCOM A

CABIN AUDIO INTERCOM A

CABIN PA AUDIO C

WEATHER RDR INDICATIONS C

MODE S ATC/IFF CODE B

CVR RECORDING D

FDR RECORDING D

FLIGHT INSTRUMENTS INDICATION C

SECONDARY INTRUMENTS INDICATION C

RAD ALT INDICATIONS C

EGPWS INDICATIONS C

FUEL FLOW IND INDICATIONS E

N1 RPM IND INDICATIONS E

N2 RPM IND INDICATIONS E

EPR IND INDICATIONS E

EGT IND INDICATIONS E

FUEL QTY IND INDICATIONS E


MOD-11350-00001 Issue 4.








ELEC SYSTEM IND INDICATIONS E

HYDRAULIC SYSTEM IND INDICATIONS E

TABLE 3 – IMPORTED EMC TEST


AIRCRAFT EMITTER NEWLY INSTALLED SUSCEPTOR(S)


VHF1 TX LOW MHz A.1

VHF1 TX MID MHz A.1

VHF1 TX UPP MHz A.1

VHF2 TX LOW MHz A.1

VHF2 TX MID MHz A.1

VHF2 TX UPP MHz A.1

HF1 TX LOW MHz A.1

HF1 TX MID MHz A.1

HF1 TX UPP MHz A.1

HF2 TX LOW MHz A.1

HF2 TX MID MHz A.1

HF2 TX UPP MHz A.1

UHF1 RX LOW MHz A.1

UHF1 RX MID MHz A.1






MOD-11350-00001 Issue 4.







AIRCRAFT EMITTER NEWLY INSTALLED SUSCEPTOR(S)


DME 1 108.40 MHz A.1

DME 1 113.75 MHz A.1

DME 1 116.90 MHz A.1

DME 2 108.40 MHz B

DME 2 113.75 MHz B

DME 2 116.90 MHz B

MARKER 1 HIGH C

MARKER 2 HIGH C

PILOT AUDIO INTERCOM B

Co-Pilot AUDIO INTERCOM B

CABIN AUDIO INTERCOM B

CABIN PA AUDIO B

IFE SYSTEM AUDIO/VIDEO D

TCAS OPERATE D

MODE S ATC CODE C

RAD ALT OPERATE D

WEATHER RADAR OPERATE D

CONDITIONING SYSTEM OPERATE D

NAV LIGHTS OPERATE D

STROBE LIGHTS OPERATE D

HYDRAULICS OPERATE D

PNEUMATICS OPERATE D

FUEL PUMPS OPERATE D

ELECTRICAL SYSTEM OPERATE D


MOD-11350-00001 Issue 4.






Appendix D TIC TR-220 Tests

Mode ‘S’ Tests

The following Tests are an extract of the applicable pages from the TIC TR-220 Multifunction Test Set,

document no. 90008088-1, Revision D, 01 July 2005, Operating and Maintenance Manual, Software

Revision 3.40 and Later.

Note: The following Test Sets may be used as an alternative to the TIC TR-220 Multifunction Test Set.

i) Aeroflex IFR 6000 Test Set; Document No: 1002-5800-2PO; Revision: 4; Dated: Jan 2006. ii) Aeroflex ATC-601-2 Ramp Test Set with software version 3.0 or later; Document No: 1002-8106-

200; Issue: 3; Dated: November 2004.

2.12 Transponder Manual Sequence of Tests

NOTE

When conducting tests in the MANUAL sequence, the operator initializes the sequence by toggling the AUTO /

TEST / MANUAL switch to the MANUAL position. The Test Set then commences a series of tests and displays

the individual results of each test ending in the POWER, RECEIVER EFFICIENCY and FREQUENCY page.

After each test is completed, the operator must toggle the MANUAL switch to advance to the next test in the

series.

The “IDENT” feature of a transponder can only be tested during the MANUAL sequence of tests.

See paragraph 2-14 for detailed instructions.

2.12.2 Mode S Manual Testing

Test

No. Operation

Test Set

Screen Display Results

1 Turn the Test Set “ON” by toggling the

ON/OFF switch to the ON position.

Ensure the green LED illuminates.

NOTE Utilize the procedures as outlined in the TR-220 Test Set Operating and Maintenance

Manual, Software Revision 3.40 and Later, paragraph 2.9 to select the preferred

antenna method for the following tests:

2 The Test Set commences the Self

Test. “PASS” is displayed briefly if no

failures are detected.

Self Test

PASS


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


3 Turn the UUT FUNCTION switch to the

XPDR position.

The Test Set will automatically

determine the transponder capability

as being Mode S capable and display

the appropriate start page with the

COMM A, B, C, & D capabilities also

listed. The Test Set will display if the

transponder reports it is capable of

Enhanced Surveillance (EHS). The

Test Set will display the Vertical Status

(Air/Ground) and display the results of

an Interrogation Identifier (14) test.

Capab Comm AB EHS

Air Press A/M II:14

4 Toggle the AUTO/TEST/MANUAL

switch to the MANUAL position to

begin the sequence:

Mode A Test Initialised M A /

Testing

Test Complete. Display indicates the

UUT 4096 Octal Code (1234),

Receiver Efficiency as a percentage

(100%), Transponder Framing Pulse

widths (0.45) and separation measured

in .05 µs increments (20.35 µs).

M A 1234 100%

0.45–20.35– 0.45 PASS

5 To advance, toggle the AUTO / TEST /

MANUAL switch to MANUAL. The

next test in sequence will commence:

Mode C Test initialized M C /

Testing . . .

Test Complete. Display indicates the

UUT Altitude Gray Code (6520=1000’),

Rcvr.

Efficiency as a percentage (100%),

Transponder Framing Pulse widths

(0.45) and separation measured in .05

µs increments (20.35 µs).

M C 6520 10000’ 100%

0.45-20.35-0.45 PASS


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set





Mode A SLS tests are initiated. The

test set makes alternating

interrogations with and without the SLS

pulse.

Mode A SLS /

Testing . . .

When P1>P2 (SLS pulse at P1 - 9dB)

the transponder reply efficiency should

be greater than 99%. For P1=P3

(SLS).

The transponder reply efficiency

should be less than 1%.

SLS P1>P2 100% PASS

P1=P2 0% PASS




Mode A All Call Test initialized.

Transmits an M A All Call.

M A All Call /

Testing . . .

Test Complete. Successful DF=11

reply will display the decoded aircraft

address in Hexadecimal (A02008) and


(100%).

M A All Call /

A02008 100%

8 Toggle the AUTO / TEST / MANUAL

switch to MANUAL to advance to the

next sequence:

Mode 3C All Call Test initialized.

Transmits a Mode 3C All Call.

M C All Call /

Testing . . .

Test Complete. Successful DF=11

reply will display the decoded aircraft

address in Hexadecimal (A02008) and


(100%).

M C All Call /

A02008 100%


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set




next sequence:

Mode A ONLY Test initialized.

Test Set transmits an ATCRBS ONLY

All-Call.

M A Only /

Testing . . .

A Mode S transponder will not reply to

an ATCRBS Only All-Call. A “PASS”

signifies the Mode S transponder did

not respond.

M A Only /

PASS



next sequence:

Mode 3C ONLY Test initialized. Test

Set transmits an ATCRBS ONLY All-

Call.

M C Only /

Testing . . .

A Mode S transponder will not reply to

an ATCRBS Only All-Call. A “PASS”

signifies the Mode S transponder did

not respond.

M C Only /

PASS



next sequence:

SI Lockout /

Testing . . .

The Test Set issues a SI Lockout

command (37) and verifies that UUT

will not respond for minimum of 3

seconds and maximum of 18 seconds.

SI Lockout

PASS 18 sec


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set




next sequence:

Mode S Surveillance Identity Test

initialized. Test Set will transmit an

UF=5 interrogation.

M S Surv ID /

Testing . . .

Test complete. A successful DF=5

Reply will display the aircraft 4096

Octal code (1234), Flight Status (Air),

and Receiver Efficiency as a

percentage.

M S Surv ID /

1234 FS: AIR 100%

NOTE Possible Flight Status Codes are AIR (Airborne), GND (Ground), AL / AR (Alert /

Airborne), AL / GND (Alert / Ground), AL / SP (Alert / SPI), and SPI.



next sequence:

Mode S Surveillance Altitude Test.

Test Set will transmit an UF=4

interrogation.

M S Surv Alt /

Testing . . .


Reply will display reported altitude

(10000’) and Receiver Efficiency as a

percentage (100%).

M S Surv Alt /

10000’ 100%



next sequence:

Mode S Short Air to Air Surveillance

Test.

Test Set transmits a special short

UF=0 interrogation.

M S Surv Srt /

Testing. . .

Test complete. A Mode S transponder

will reply in a DF=0 format. Alternating

display will indicate the Country code

(USA) and tail number, aircraft address

in Hexadecimal (A02008) and Octal

(50020010).

USA: N107PP /

A02008 VS:AIR 100%

USA: N107PP /

50020010 VS:AIR 100%

NOTE Appendix A list available country codes. If the Test Set cannot locate the country


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


algorithm, “??????” will be displayed.



next sequence:

Mode S Communication Identity Test.

Test Set will transmit a COMM A/B

transmission utilizing the UF=5/RR:18

field. This tests the transponders

communication and datalink

capabilities.

M S Comm Id /

Testing . . .


Reply will display 4096 code (1234),

Flight ID (yyyyyyyy) and Receiver

efficiency as a percentage (100%).

M S Comm Id /

1234 yyyyyyyy 100%



next sequence:

Mode S Communication Altitude Test.

Test Set will transmit a COMM A/B

transmission utilizing the UF=4/RR:18

format. This tests the transponders

communication and datalink

capabilities.

M S Comm Alt /

Testing . . .


Reply will display UUT Altitude

(10000’) and Receiver Efficiency as a

percentage.

M S Comm Alt /

10000’ 100%



next sequence:

Undesired Replies Test initialized. The

Test Set will make randomly

addressed interrogations.

Undesrd Rply /

Testing . . .


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


17

Cont.

Test complete. If the UUT replies to

any of the random interrogations,

“FAIL” will be displayed. A “PASS”

indicates the UUT did not reply as

required. The test set uses a minimum

of 3 random addresses to comply with

FAR 43 App F.

Undesrd Rply /

PASS



next sequence:

The Test Set will not transmit

interrogations but receive and process

DF=11 and DF=17 extended replies.

Squitter /

Testing . . .

Test complete. Upon detection of the

replies, the Test Set will display the

interval time of the messages (if

received) in milliseconds (900 ms). If

either a DF=11 or DF=17 extended

message is not acquired, NOT

DETECTED will be displayed.

ACQ: PASS 900 ms

ADD: A02008 II:0

EXT: NOT DETECTED

If and Extended Squitter “IS” detected,

the following display indicating the

interval time and address.

EXT: PASS 500 ms

ADD: A02008 II:0



next sequence:

Test Set verifies the UUT airspeed

code by transmitting an UF=0

interrogation.

Max True Spd /

Testing . . .

Test complete. The DF=0 will report

the aircraft maximum cruising airspeed

in the RI field of the DF=0 format.

Max True Spd /

GT 300 & LE 600 kts

NOTE Eight possible RI field codes are available.

1) NO Max airspeed data, 2) LE 75 knots , 3) GT 75 & LE 150 kts., 4) GT 150 &

LE 300 kts, 5) GT 300 & LE 600 kts, 6) GT 600 & LE 1200 kts, 7) GT 1200 kts,

8) Not Assigned.

GT denote “Greater Than”, LE denotes “Less than or Equal too”.




MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


next sequence:

Diversity Test initialized.

Diversity /

Testing . . .

Test complete. A PASS indicates that

isolation relative to the active antenna

is greater than 20 dB. and the actual

isolation figure is displayed.

Diversity A02008 /

PASS 26 dB Attn



next sequence:

UUT Receiver sensitivity tests (MTL)

for modes A and C are initiated.

Sensitivity /

Testing . . .

Test Completed. Display indicates the

UUT receiver sensitivity for mode A (-

73.9db), Mode C (-73.9dB) and Mode

S (-74.4dB).

PASS is displayed when Mode A/C/S

sensitivities are within 1dB.

A: -73.9dB C: -73.9dB

Mode S: -74.4 dB PASS



next sequence:

UUT Power and Frequency tests for

modes A and C are initiated.

Power, Frequency /

Testing

Test completed. UUT transmitter

power (54dBM) (shown in dBm or

WATTS as selected in Set-up Menu)

and UUT transmitter frequency in MHz.

Power, Frequency /

54 dBm 1090.0Mhz

END OF MODE S MANUAL TESTS


MOD-11350-00001 Issue 4.






2.14 Testing a Transponders “IDENT” Function

Test

No. Operation

Test Set


NOTE The “IDENT” function can only be tested in the Manual mode of Tests in both

(Mode A/C and Mode S).

1 To test the “IDENT” feature of a

transponder the operator may select

the Mode A or the M C Test for the

appropriate transponder (Mode A/C or

Mode S).

M A /

Testing . . .

2 Allow the Test Set to complete the

test.

M A 1234 100%

0.45–20.35– 0.45 PASS

3 Press the IDENT button or switch

located on the transponder control

panel or cockpit interface.

4 IDENT will be displayed for

approximately 20 seconds to verify the

receipt of the SPI pulse from the

transponder.

M A 1234 IDENT 100%

0.45 - Ÿ 20.35 - Ÿ 0.45

5 The operator may now continue

testing the transponder through the

remainder of the tests.

END OF TRANSPONDER TESTS


MOD-11350-00001 Issue 4.






2.17 Mode S Enhanced Surveillance

Test

No. Operation

Test Set


NOTE All illustrations shown are for demonstration purposes. Though the test results may be

typical, they are not meant to replace manufacturer recommendations or ACTUAL results.

The TR-220 is capable of testing Mode S Transponders with Enhanced surveillance

(EHS) capability. Access to the EHS menu is as follows:

If utilizing the Directional Antenna, select SETUP using the UUT FUNCTION switch and

complete the procedures in paragraph 2.9.1. Utilize paragraph 2.9.2 if using the

supplied direct connect cable.

1 Connect the antenna or direct connect

cable as appropriate.

2 Turn the Test Set “ON” by toggling the

ON / OFF switch to the ON position.

Ensure the green LED illuminates.

3 The Test Set commences the Self-

Test. “PASS” is displayed briefly if no

failures are detected.

Self Test

PASS

4 Turn the UUT FUNCTION switch to

the XPDR position. The Test Set will

automatically determine the

transponder capability as being Mode

S capable and display the appropriate

start page with the COMM A, B, C & D

capabilities also listed if applicable.

Capability COMM ABCD

Press AUTO/MANUAL

5 Press the TO / START-FROM / STOP

switch upwards to the TO position to

access the EHS menu.

Mode S Enh. Surv.

Using UF5/DF21 . . .

6 EHS testing can be carried out using 3

UF / DF combinations. Press the UP-

DOWN switch to the “UP” position to

select UF5 / DF21, UF21 / DF21, and

the UF0 / DF16 as applicable. The

results displayed will be the same for

each selection.

7 Press the AUTO / TEST / MANUAL

switch to continue. The Roll angle will

be displayed in degrees. Part of the

BDS5 Roll Angle

+90 D


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


BDS5 Track and Turn report.

8 Press AUTO / TEST / MANUAL to

move to the next test. The True track

angle will displayed in degrees and

the Track Angle rate will be displayed

in degrees per second. Part of the

BDS5 Track and Turn report.

BDS5 True Trk Angle

An E120 D Rt + 8 D/s


move to the next test. The True

Airspeed and Ground Speed will be

displayed in Knots. Part of the BDS5

Track and Turn report.

BDS5 Tru ASpd 600K

Gnd Speed 550K


move to the next test. The Indicated

Airspeed will be displayed in Knots,

the Heading in degrees and the Mach

number. Part of the BDS6 Heading

and Speed report.

BDS6 Ind Aspd 600K

Hdg E120 D Mch 1.000


move to the next test. The Barometric

Altitude Rate and Inertial Vertical

Velocity will be indicated in feet per

minute. Part of the BDS6 Heading and

Speed report.

BDS6 Balt +6000’/M

In VertVel +6000’/M


move to the next tests Subsequent

screens will display the values

contained in registers BDS 1,0; 1,7;

1,8; and 1,9. The decoded register

values are shown in Hexadecimal.

BDS 10 Datalink

10 00 00 80 E0 00 00

The TR-220 will decode and display

parameters contained in the BDS 1,0

register. The parameters include,

Mode S Subnet Network Number =

“Sub Net=0” (Decode and display IAW

with ICAO Annex X Volume 3 Sect.

5.2.9 (page 279) 0,1,2, 3, etc.);

Transponder enhanced protocol

indicator = “TC Lvl= 2-4” (Decode and

display 0=2-4 and 1=5); DTE Sub

address = “DTE= NO” (Decode and

display 0=NO, 1=YES).

BDS1 SubNet=1 A

TC Lvl= DTE=


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


Mode S Specific Services Capability =

“SPC SV CP=YES” (Decode and

display 0=NO, 1=YES); Continuous

Flag = “Cont Flg=NO” (Decode and

display 0=NO, 1=YES); Surveillance

Identifier = “SI=YES” (Decode and

display 0=NO and 1=YES).

BDS1 SPC SV CP=

Cont Flg= SI=

Aircraft Identification Capability = “Flt

ID=YES (Decode and display 0=NO

and 1=YES); Squitter Capability

Subfield = “Sq=YES” (Decode and

display 0=NO and 1=YES); Common

usage GICB capability = “COM

GICB=YES” (Decode and display

0=NO and 1=YES).

BDS1 Flt ID=

Sq= COM GICB=

Uplink UELM capability = “UELM=NO”

(0=NO, 1=1, 2=2, etc. ICAO Annex X

Volume 3 Sect. 5.2.9 page 280);

Downlink DELM capability

=“DELM=NO” (0=NO, 1=1, 2=2, etc.

ICAO Annex X Volume 3 Sect. 5.2.9

page 280).

BDS1 UELM=

DELM=

BDS 1,7 Co Use GICB

FA 81 01 00 00 00 00

BDS 1,8 MS Sp Sv GICB

00 00 00 81 C0 81 F0

BDS 1,9 MS Sp Sv GICB

00 00 80 00 80 00 80


move to the next test. The display will

indicate if TCAS has issued a

Resolution Advisory. BDS3 ACAS

Active Resolution Advisory.

NOTE A second TR-220 may be necessary to simulate a TCAS intruder in order to cause the

TCAS system to issue a Resolution Advisory

BDS Resolution Adv:

Active RA FFFFFF


MOD-11350-00001 Issue 4.






Test

No. Operation

Test Set


14 Press AUTO/TEST/MANUAL to move

to the next test. The display will

indicate the Selected Altitude in feet.

Part of the BDS4 Aircraft Intention

report.

BDS4 FMC Alt 25000’

MCP / FCU Alt

Barometric Pressure Setting = “Press

Set = 1015”.0; Target Altitude Source

= “Tgt Alt=UNK” (00=UNK, 01=ALT,

10=BOTH, 11=FMS); Status of Target

Alt Source Bits = “Src=NO” (0=NO and

1=YES);

BDS4 Press Set=800.1mb

Tgt Alt= UNK Src=No

NOTE For aircraft with DADC Smiths P/N 501FAD1-1 installed, the test set will display:

BDS4 Press Set=......

because this model of DADC does not output the Baro correction figure on its Arinc 429

data bus. Note, however, that it does output the Baro-corrected altitude.

VNAV Mode = “VNAV=NA” (0=NA,

1=ACT); ALT Hold Mode = “ALT

HD=NA

(0=NA, 1=ACT; Approach Mode =

“APRHL=NA” (0=NA and 1=ACT)

BDS4 VNAV = NA

Alt Hld= NA Appr= NA

END OF MODE S ENHANCED TESTS

Boeing 737-400 - Installation of Enhanced Mode S Transponder.CHANGE BULLETIN Document No....

Documents

Transcript of Boeing 737-400 - Installation of Enhanced Mode S Transponder.CHANGE BULLETIN Document No....