AS457 ISSUE 15 - me.aslairlines.bePara 5.4.1, added item u) ref to WD ATL11350-801 and item v) ref...

AS457 ISSUE 15

MODIFICATION SUMMARY CONTINUATION SHEET

MODIFICATION No.

ATL/737/M556 SHEET 2 Issue 9

1 Revision History

Issue Date Raised Issue Details Sheet(s) Affected

1 09 Oct 2006 Initial Issue All

2 16 Feb 2007 Job No: “10266” added. STC No “EASA.A.S.02818” added. Para 3.4.1: “Boeing Document Reference: D6-8022L; Revision: 8; Dated: 14 Jul

2005” added. Para 3.5.1: did read “…aircraft SE-RCO; SE-RCP; EC-JTV; EC-IOR and D-ACIN”. Para 4: “OE-ITA; SE-RCR; SE-RCS and TC-TJA” added. Para 5.2: Table expanded to include new aircraft OE-ITA; SE-RCR; SE-RCS and TC-TJA. Notes ‘1 and 2’ added. Para 5.3: Table expanded to include new aircraft OE-ITA; SE-RCR; SE-RCS and TC-TJA. Para 5.4.1: “ATL10030-806; -807; -808 and -809” added. Para 5.4.2: did read “…Dated: Sep 17, 2003; Revision: 14”. Para 5.4.4 b): added. Paras 7.1.2 & 7.1.3: added. Para 9.1.2 thru 9.1.4 added. Para 13.1: did read ”Refer to Test Equipment Manual TIC TR-220 Multifunction Test Set, Document No. 90008088-1, Revision D, 01 July 2005”. Table expanded to include IFR 6000 Test Set.

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10

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12 27 30

3 30 Mar 2007 Mod transferred onto new template AS457 @ issue 9

Job No: “10364” added. STC No: did read “EASA.A.S.02818”. Para 3.4.1: “D6-9118G” added. Para 3.5.1: “JY-JAD” added. Para 4: MSN “24662” added. Para 5.2: “JY-JAD” added. Para 5.3: Part No: “622-8974-004 – D-ACIN” added. “JY-JAD” and Part No: “622–8974–304” added. “G6990-51” did read “G7112-10”. “G6990-30 – TC-TJA” deleted. “622-8974-008 – TC-TJA” added. Para 5.4: “ATL10030-810” added. Para 5.4.4: “Note” added. Para 6.1.1: “… Revision 39, Dated: 15 Nov 2006 …” did read “… Revision 35, Dated: 10 May 2004 …”. Para 7.1.3: “… Revision 39, Dated: 15 Nov 2006 …” did read “… Revision 35, Dated: 10 May 2004 …”. Para 9.1.1: “D-ACIN & TC-TJA” removed. Para 9.1.2: “G6990-51” did read “G7112-10”. Para 9.1.4: “D-ACIN; TC-TJA and JY-JAD” added. Para 9.2.1: “JY-JAD” added. Para 9.3.1: “JY-JAD” added. Para 13: “…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” added.

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11

13

28

29

31

4 18 Apr 2007 Job No: “10404” added. Para 3.2.1: did read “Boeing Document Reference: D6-37547; Revision: 57; Dated: 12 Jul 2006”. “D6-37571 & D6-37528” added. Para 3.3.1: did read “Boeing Document Reference: D6-38550; Revision: 51; Dated: 12 Jul 2005”. Para 3.4.1: did read “Boeing Document Reference: D6-9118F; Revision: 22; Dated: 29 Jun 2006”. “D6-9122L; D6-9118C & D6-8022L” added. Para 3.5.1: “YR-BAA; YR-BAB; YR-BAC and OM-AAD” added. “The Control Panels have been designed as on-condition units and no additional maintenance is required” added. “In accordance with Boeing Standard Practices …” added. Para 4: MSN “27267; 24785; 23653 & 23636” added. Para 5.2: “YR-BAA; YR-BAB; YR-BAC & OM-AAD” added. TC-TJA: “See Note 4” added. ‘Notes 3 & 4’ added. Para 5.3: “YR-BAA; YR-BAB; YR-BAC & OM-AAD” added. TC-TJA: “See Paragraph 5.2, Note 4” added. SE-RCS Control Panel Part No. did read “622-8594-121. Para 5.4.1: “ATL10030-811; -812; -813 & -814” added. Para 5.4.3 c) & d): added. Para 9.1.4 thru 9.1.7: expanded. Para 9.1.8 thru 9.1.11: added. Para 9.2: expanded. Para 9.2.2 & 9.2.3 added. Para 9.3.1: “YR-BAA and YR-BAB” added. Para 9.3.2 & 9.3.3: added.

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AS457 ISSUE 15


MODIFICATION No.


5 06 August 2007 Document reformatted onto ATL Form AS457 Issue 12. Para 5.2: G7490-30 Remarks column: “TC-TJA (See Note4)” deleted; G7492-05 line added; Note 4 did read ”…G7490-30 …”. Para 5.4.3: e) added. Para 7.1.3: “Subpart J – Auxiliary Power Unit Installations” added. Para 9.2.1: “…TC-TJA …” deleted. Para 9.2.4: added.

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6 18 April 2008 Job No’s. “10665” and “10888” added to front sheet. Added text: “which is now superseded by EASA AMC 20-13”. Para 3.2.2, AMM D6-37552 added for EC-KDY. YR-TIB was OE-ITA. Para 3.3.2, IPC D6-38550-AWW-0118 added. Para 3.4.1 AWM D6-9118R added. Para 3.5.2, EC-KDY added. I-AIGL was OM-AAD. YR-TIB was OE-ITA. Para 4, EC-KDY added. I-AIGL was OM-AAD. YR-TIB was OE-ITA. Para 5.2, EC-KDY added. I-AIGL was OM-AAD in 2 places. YR-TIB was OE-ITA in 2 places. Para 5.2, Notes 5 to 8 added. Para 5.3, YR-TIB was OE-ITA in 2 places. Added additional P/Ns req’d for aircraft JY-JAD and I-AIGL. Para 5.3, EC-KDY added. I-AIGL was OM-AAD in 3 places. Added “Mode-C Transponder Tray” to parts removal list for I-AIGL. Par 5.4.1, item c), EC-KDY added. At item h), YR-TIB was OE-ITA. At item p), I-AIGL was OM-AAD. Added new item s), drawing ATL10888-001, and item t), drawing 10404-001. Para 6.2.2, added text:” which is now superseded by EASA AMC 20-13”. Para 7.1.2, was CS-25 at amendment 2, dated 2 October 2006. Para 7.2.2, added text: “which is now superseded by EASA AMC 20-13”, and added text: “In accordance with EASA’s Letter to Industry reference Mode-S ELS and EHS Certification Requirements, issue 2, dated 02 March 2007, no further compliance demonstration is required with EASA AMC 20-13, if compliance with JAA NPA 20-12a has already been demonstrated.” Para 9.1.2, YR-TIB was OE-ITA. Para 9.1.11, I-AIGL was OM-AAD. Para 9.1.12 added Para 9.2.2, YR-TIB was OE-ITA. Para 9.2.3, I-AIGL was OM-AAD. Para 9.2.5 added for EC-KDY. Para 9.3.1, EC-KDY added, and YR-TIB was OE-ITA. Para 9.3.3, I-AIGL was OM-AAD.

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7 02 June 2008 Job No “10998” added to front sheet. Registrations substituted by MSN Numbers. Para 3.2.2, added Doc reference for a/c MSN 24059. Para 3.3.2, deleted a/c registration. Text “aircraft” was “A/C”. Added Para 3.3.3 for a/c MSN 24059. Old para 3.3.3 now 3.3.4. Para 3.4.1, added WDM reference for a/c MSN 24059. Para 3.5.2, deleted individual aircraft registrations and added text: “the” before “aircraft”. Para 4, Effectivity, aircraft MSN 24059 added. Para 5.2, Parts Required, added text: “Aircraft” in heading, deleted text: “Aircraft Reg:” in each remarks block, and added MSN 24059 in 2 places. Para 5.3, Parts Removed, added text: “Aircraft” in heading, deleted text: “Aircraft Reg:” in each remarks block, and added parts removed for MSN 24059 (2 places). Para 5.4.1, added MSN 24059 to drawing ATL10030-801 effectivity. Added para 9.1.13 for a/c MSN 24059. Para 9.2.2 deleted, subsequent paragraphs re-numbered. A/c MSN 27924 and MSN 24059 added to new Para 9.2.2. MSN 24059 added to Para 9.3.1.

1 throughout

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36

AS457 ISSUE 15


MODIFICATION No.


8 30 April 2009 Updated document format to ATL template number AS457 issue 15. Job No “11350” added to front sheet. Aircraft type was “737-300 / -500” Added Paragraphs 3.1.3 and 3.1.3.1. Para 3.2.2, added AMM reference for B737-400 MSN 25429. Added Para 3.3.4, IPC reference for B737-400 MSN 25429. Para 3.4.1, added WDM reference for B737-400 MSN 25429. Added Para 3.6.3, M.E.L details for B737-400 aircraft. Para 4, added B737-400 aircraft MSN 25429 to effectivity table. “Variable number” was “Block Number”. Added column for “Applicable Mod Issue”. Added Paragraphs 5.1.1 and 5.1.2. Para 5.1.3 was 5.1.1. Para 5.2, added parts required for B737-400 aircraft MSN 25429. Para 5.2 , Co-axial assemblies P/Ns for aircraft MSN 23636 were stated as “CUSTOM-X”; P/Ns now detailed as per effective WD ATL10030-814. Added P/Ns for Suppression Cable Assy, C/B, controller connectors, and shorting connectors. Added Para 5.2 notes 9 and 10. Para 5.3, added parts removed from B737-400 aircraft MSN 25429. Para 5.4.1, added item u) ref to WD ATL11350-801 and item v) ref to AFM for B737-400 aircraft MSN 25429. Added new Para 5.4.3, subsequent paragraphs re-numbered. Para 6.1.1, Certification Basis changed from FAA Type Certificate A16WE reference to EASA Type Certificate Data Sheet TCDS IM.A.120 reference. Para 6.4.1 EU OPS was JAR OPS, and added text “paragraphs pertaining to”. Para 7.1.3, in CS 25 Matrix, FAA Type Certificate A16WE reference changed to EASA Type Certificate Data Sheet TCDS IM.A.120 reference. 25.2 deleted. At para 25.581 and 25.613, “Boeing 737” was “Boeing 737-300/-500”. At para 25.869, “CS-25” was “JAR-25”. At para 25.1301, added WD ref ATL11350-801. At para 25.1353, added WD ref ATL11350-801. At para 25.1581, added AFMS ref 11350-AFM-00001 for B737-400. At para 7.4.1, “EU OPS” was “JAR OPS”. Added para’s 7.6.1 and 7.6.2. Subsequent para renumbered to 7.6.3. Added para 9.1.14, Equipment Removed for aircraft MSN 25429. Added para 9.2.5, Equipment Added for aircraft MSN 25429. Para’s 9.3.1, 9.3.2, and 9.3.3, added Station numbers to totals. Added para 9.3.4, Total Weight & Balance Change for aircraft MSN 25429. Para 13.3.1, updated reference to Revision: 17; Dated: Apr 27, 2006 . Added para’s 13.3.3 and 13.3.4 as ref for for Honeywell TRA-67A equipment. Added para 13.3.5 as reference for Gables equipment. Para 13.3.6 was 13.3.3 and 13.3.7 was 13.3.4. Added para 13.3.8 and sub-paragraphs. Updated para 13.4.1 with Honeywell TRA-67A info. Para 13.5 info was previously in para 3.4.

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48 50

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53 54

9 19/09/2012 Para 3.4.1, added MSNs 24440, 24446, 26961 and 24433. Para 4, added MSNs 24440, 24446, 26961 and 24433. Para 5.2, added part no’s. 822-1338-021 and G7490-01. Para 5.3, added MSNs 24440, 24446, 26961 and 24433 to part no’s. 622-7878-201 and G6990-51. Para 5.4.1, added MSNs 24440, 24446, 26961 and 24433. Para 6.1.1, EASA Type Certificate Data Sheet updated. Para 6.1.2, CS-25 Amendment updated. Para 7.1.2, CS-25 Amendment updated. Para 7.1.3, at para 25.1, EASA Type Certificate Data Sheet updated. Para 7.1.3, Subpart H added. Para 9.1.15 added. Para 9.2.6 added. Para 9.3.1, added MSNs 24440, 24446, 26961 and 24433.

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AS457 ISSUE 15


MODIFICATION No.


2 Contents

1 Revision History ............................................................................................................. 2 2 Contents ......................................................................................................................... 5 3 Documents Affected ...................................................................................................... 6 3.1 Aircraft Flight Manual ....................................................................................................... 6 3.2 Aircraft Maintenance Manual ............................................................................................ 6 3.3 Illustrated Parts Catalogue ............................................................................................... 7 3.4 Wiring Diagram Manual .................................................................................................... 7 3.5 Maintenance Schedule ..................................................................................................... 8 3.6 Minimum Equipment List .................................................................................................. 9 3.7 Flight Operation Manual ................................................................................................. 12 3.8 Overhaul Manual ............................................................................................................ 12 3.9 Repair Manual ................................................................................................................ 12 3.10 Crew Manual .................................................................................................................. 12 3.11 Configuration Manual ..................................................................................................... 12 4 Aircraft Effectivity ........................................................................................................ 12 5 Modification Details ..................................................................................................... 13 5.1 Introduction .................................................................................................................... 13 5.2 Major Parts Required Per Aircraft ................................................................................... 13 5.3 Major Parts Removed Per Aircraft .................................................................................. 16 5.4 Documents and Drawings Required ............................................................................... 17 5.5 Instructions ..................................................................................................................... 18 6 Basis of Approval ......................................................................................................... 18 6.1 Certification Basis .......................................................................................................... 18 6.2 Additional Advisory Data ................................................................................................ 18 6.3 Environmental Requirements ......................................................................................... 18 6.4 Operational Approvals .................................................................................................... 19 6.5 Other Airworthiness Approvals ....................................................................................... 19 6.6 Equipment Approval ....................................................................................................... 19 6.7 Additional Requirements ................................................................................................ 19 7 Compliance with Requirement .................................................................................... 19 7.1 Certification Basis .......................................................................................................... 19 7.2 Additional Advisory Data ................................................................................................ 49 7.3 Environmental Requirements ......................................................................................... 50 7.4 Operational Approvals .................................................................................................... 50 7.5 Other Airworthiness Approvals ....................................................................................... 50 7.6 Equipment Approval ....................................................................................................... 50 7.7 Additional Requirements ................................................................................................ 50 8 Checks .......................................................................................................................... 51 8.1 Ground Checks .............................................................................................................. 51 8.2 Flight Checks ................................................................................................................. 51 9 Weight and Balance ..................................................................................................... 51 9.1 Equipment Removed ...................................................................................................... 51 9.2 Equipment Added ........................................................................................................... 55 10 Electrical Load Analysis .............................................................................................. 58 10.1 Equipment Removed (All Aircraft) .................................................................................. 58 10.2 Equipment Added (All Aircraft) ....................................................................................... 58 10.3 Load Change (All Aircraft) .............................................................................................. 58 11 Associated Reports...................................................................................................... 58 12 Limitations/Concession ............................................................................................... 59 13 Continued Airworthiness ............................................................................................. 59 13.1 Introduction .................................................................................................................... 59 13.2 Overview ........................................................................................................................ 59 13.3 Aeroplane Maintenance Manual ..................................................................................... 59 13.4 Maintenance Instructions ............................................................................................... 60 13.5 Scheduled Maintenance ................................................................................................. 61 13.6 Airworthiness Limitations ................................................................................................ 61 14 Conditions Affecting this Approval ............................................................................ 61 15 Authorisation for Release to Service .......................................................................... 62

AS457 ISSUE 15


MODIFICATION No.


16 Post Modification Action ............................................................................................. 62 3 Documents Affected

Document Document number / Action

Type Certificate Data Sheet See paragraph 6.1 No Aircraft Flight Manual See paragraph 3.1 Yes Aircraft Maintenance Manual See paragraph 3.2 Yes

Illustrated Parts Catalogue See paragraph 3.3 Yes Wiring Diagram Manual See paragraph 3.4 Yes Maintenance Schedule See paragraph 3.5, 13.4 Yes

Minimum Equipment List See paragraph 3.6 Yes Flight Operation Manual See paragraph 3.7 No

Overhaul Manual See paragraph 3.8 No Repair Manual See paragraph 3.9 No

Crew Manual See paragraph 3.10 No Weight & Balance Schedule See paragraph 9 Yes Electrical Load Analysis See paragraph 10 Yes

Configuration Manual See paragraph 3.11 No Aircraft Modification Record See paragraph 16.1 Yes

3.1 Aircraft Flight Manual

3.1.1 ATL, AFM Supplement No. 48, (SSR Mode ‘S’ Elementary and Enhanced Surveillance) to be inserted in the Aircraft Flight Manual for Boeing 737-300.

3.1.1.1 Boeing Document Reference: D6-8730.33A3; Dated: 06-06-06.

3.1.2 ATL AFM Supplement No. 51, (SSR Mode ‘S’ Elementary and Enhanced Surveillance) to be inserted in the Aircraft Flight Manual for Boeing 737-500.

3.1.2.1 Boeing Document Reference: D6-8735.53C; Dated: 22-08-05.

3.1.3 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.

3.1.3.1 Boeing Document Reference: D6-8734.4C9; Rev 14; Dated: 12-03-09.

3.1.4 It is the operator’s responsibility to ensure that the AFM Supplement is inserted into the appropriate AFM and the relevant record pages amended.

3.2 Aircraft Maintenance Manual

3.2.1 Information that is required for the update of the AMM is contained in section 13 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.

3.2.2 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, 3.5 - Maintenance Schedule, and 13.0 - Continued Airworthiness for Inclusion into the Aircraft Maintenance Manual.

Boeing Document Reference: D6-37547; Revision: 58; Dated: 12 Jan 2007 (-300 Series)

Boeing Document Reference: D6-37571; Revision: 51; Dated: 12 Jul 2006. (-500 Series)

AS457 ISSUE 15


MODIFICATION No.


Boeing Document Reference: D6-37528; Revision: 62; Dated: 12 Jan 2007. (MSN 27924 only)

Boeing Document Reference: D6-37552; Revision: 57; Dated: 12 Jul 2007. (MSN 23811 only)

Boeing Document Reference: D6-37549; Revision: 58; Dated: 12 Jul 2007. (MSN 24059 only)

Boeing Document Reference: D6-37581; Revision: 41; Dated: 12 July 2006. (B737-400 MSN 25429 only)

3.3 Illustrated Parts Catalogue

3.3.1 Information that is required for the update of the IPC, Boeing Document Reference: D6-38550; Revision: 54; Dated: Jan 12, 2007, is contained in paragraph 5.2, to allow the operator to compile a supplement to this manual. Any supplementary information produced must be supplied to ATL for verification and approval. Alternatively, this document may be placed into the IPC as an appendix until the document is updated.

3.3.2 For aircraft MSN 23811; Boeing Document Reference: D6-38550-AWW-0118; Revision: 55; Dated: Jul 12, 2007.

3.3.3 For aircraft MSN 24059; D6-38550; Revision: 9; Dated: 12 July 2007.

3.3.4 For B737-400 aircraft MSN 25429; D6-38550; Revision: 1; Dated: 25 September 2008.

3.3.5 It is the operator’s responsibility to ensure that the IPC Supplement is inserted into the appropriate IPC and the relevant record pages amended.

3.4 Wiring Diagram Manual

3.4.1 Wiring diagrams called up by this modification action to be inserted in the respective Aircraft Wiring diagram Manual.

Boeing Document Reference: D6-9118F; Revision: 23; Dated: 28 Feb 2007

Boeing Document Reference: D6-9118U; Revision: 21; Dated: 21 Nov 2005

Boeing Document Reference: D6-9122K; Revision: 1; Dated: 08 Oct 2001

Boeing Document Reference: D6-9118G; Revision: 16; Dated: 04 Jan 2007

Boeing Document Reference: D6-9122L; Revision: 9; Dated: 12 Jan 2006

Boeing Document Reference: D6-9118C; Revision: 16; Dated: 04 Jan 2007

Boeing Document Reference: D6-8022L; Revision: 8; Dated: 14 Jul 2005

Boeing Document Reference: D6-9118R; Revision: 5; Dated: 21 Dec 2005

Boeing Document Reference: D6-9118J; Revision: 13; Dated: 11 Jul 2007 (MSN 24059)

Boeing Document Reference: D6-9125P; Revision: 4; Dated: 17 Jan 2006 (B737-400 MSN 25429 only).

Boeing Document Reference: D6-8022W; Dated: 03 Aug 2011 (B737-400 MSNs 24440, 24446, 26961 and 24433.

AS457 ISSUE 15


MODIFICATION No.


3.5 Maintenance Schedule

3.5.1 Information that is required for the update of the Maintenance Schedule is contained in paragraph 13. 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.

AS457 ISSUE 15


MODIFICATION No.


3.6 Minimum Equipment List

3.6.1 The following is to be incorporated in the Boeing 737-300 aircraft MEL at Chapter 34 – 18; Revision: 12; to replace the existing entry.

AIRCRAFT Revision No XX Page

Boeing B737-300 Date dd/mm/yy 34-( )

(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 - 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.



AS457 ISSUE 15


MODIFICATION No.

ATL/737/M556 SHEET 10

Issue 9

3.6.2 The following is to be incorporated in the Boeing 737-500 aircraft MEL at Chapter 34 – 18; Revision: Original; to replace the existing entry.


Boeing B737-500 Date dd/mm/yy 34-( )





34 NAVIGATION


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






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



AS457 ISSUE 15


MODIFICATION No.


Issue 9

3.6.3 The following is to be incorporated in the B737-400 MEL at latest revision (XX); Page 34-(YY) to replace the existing entry.


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





34 NAVIGATION


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






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.



AS457 ISSUE 15


MODIFICATION No.


Issue 9

3.7 Flight Operation Manual

3.7.1 Not affected.

3.8 Overhaul Manual

3.8.1 Not affected.

3.9 Repair Manual

3.9.1 Not affected.

3.10 Crew Manual

3.10.1 Not affected.

3.11 Configuration Manual

3.11.1 Not affected.

3.12 It is the operator’s responsibility to ensure that aircraft manuals affected by this modification are amended as appropriate.

3.13 All approved manual amendments/changes made as a result of data contained in this modification must be verified by ATL.

4 Aircraft Effectivity

Registration Model Serial No Variable Number

Line Number

Effectivity Applicable Mod Issue

SE-RCO B737-300 23635 PP902 1436 015 1

SE-RCP B737-300 24025 PP910 1556 019 1

EC-JTV B737-300 24027 PP912 1597 021 1

EC-IOR B737-300 24449 PQ304 1857 374 1

D-ACIN B737-500 24825 PT146 1894 501 3

YR-TIB B737-300 27924 PS862 2760 072 6

SE-RCR B737-300 24026 PP911 1595 020 2

SE-RCS B737-300 24299 PP393 1598 053 2

TC-TJA B737-300 24699 PQ286 1886 356 5

JY-JAD B737-300 24662 PQ187 1862 087 6

YR-BAA B737-300 27267 PS618 2600 057 4

YR-BAB B737-500 24785 PT211 1882 511 4

YR-BAC B737-300 23653 PQ026 1260 051 4

I-AIGL B737-300 23636 PP903 1438 012 8

EC-KDY B737-300 23811 PP948 1445 103 6

I-AIGN B737-300 24059 PP935 1517 005 7

YR-BAD B737-4C9 25429 PW741 2215 001 8

EI-STB B737-476 24440 PW541 2324 061 9

AS457 ISSUE 15


MODIFICATION No.


Issue 9

Registration Model Serial No Variable Number

Line Number

Effectivity Applicable Mod Issue

B737-476 24446 PW547 2569 067 9

B737-4L7 26961 PW557 2517 071 9

B737-476 24433 PW534 1881 054 9

5 Modification Details

5.1 Introduction

5.1.1 This modification introduces new Elementary and Enhanced Mode ‘S’ Transponder systems on B737 Classic type aircraft, for Operator requirements to comply with JAA TGL No 13 and JAA NPA 20-12a, which is now superseded by EASA AMC 20-13.

5.1.2 A full description of the modification is contained within the associated Engineering Order document number ATL/737/E556.

5.1.3 The technical content of this document is approved under the authority of DOA N° EASA.21J.016.

5.2 Major Parts Required Per Aircraft

Part No. Description Qty Remarks/manufacturer/

Aircraft

822-1338-003 Rockwell Collins

Transponder (TPR-901) 2

MSN 24825 MSN 24449 MSN 24027 MSN 27924 MSN 23635

MSN 24025 (See Note 2) MSN 24026 MSN 24299 MSN 24699 MSN 24662 MSN 27267 MSN 24785

MSN 23653 (See Note 3) MSN 23636 MSN 23811 MSN 24059



MSN 24440 MSN 24446 MSN 26961 MSN 24433

066-01127-1602 Honeywell TRA-67A

Transponder 2 MSN 25429 (See Note 9)

G7490-30 Gables Control Panel 1

MSN 24825 (See Note 1) MSN 24449 MSN 24027 MSN 23635 MSN 24025 MSN 24026 MSN 24299 MSN 24662

AS457 ISSUE 15


MODIFICATION No.


Issue 9


Aircraft


MSN 27924 MSN 27267 MSN 24785

MSN 23653 (see Note 7) MSN 23636

MSN 25429 (See Note 10)

G7490-04 Gables Control Panel 1 MSN 24825 (See Note 1)

G7492-05 Gables Control Panel 1 MSN 24699 (See Note 4)

G7490-39, Or Alt P/N, G7490-40 Gables Control Panel 1

MSN 23811 MSN 24059 (See Note 5)

ATL0000-109 Relay Bracket 1 MSN 24662 only.

Manufactured.

M12883/45-01 Relay Socket 1 MSN 24662 only. Any. Alt P/N SO-1064-001

X-D4N-300M 28V DC Coil Relay 1 MSN 24662 only. Leach. Any supplier.

BACC18Z02R Circuit Breaker, 2 Amp 1 MSN 24662 only.

Boeing. Alt Klixon P/N 2TC6-2

402-167 Co-Axial Switch (Relay) 2 MSN 23636 only

Dow-Key Microwave (See Note 6)

ATL10404-001/1 Relay Bracket 1 MSN 23636 only. Manufactured.

95580-1 Transponder Rack

(complete with ARINC 718A Connector & contacts)

1 MSN 23636 only.

Barry Controls (Stop-choc), or Rockwell Collins alt P/N.

159AB-241 Pre-terminated

Co-Axial Cable Assy 1

MSN 23636 only. ECS.










159AB-255 Suppression Cable Assy 1 MSN 23636 only.

ECS.

BACC18Z5R 5 AMP Circuit Breaker 1 MSN 23636 only. Boeing.

Or Klixon P/N 2TC2-5

M83723-75R16247 Connector (Mates W. J1

on Control Panel) 1

MSN 23636 only. Any Supplier.

M83723-75R16248 Connector (Mates W. J2

on Control Panel) 1

MSN 23636 only. Any Supplier.

MS24266R22B55SN Shorting Plug (D9182) 1 MSN 23636 only.

Any Supplier.

280T1003-1 Shorting Receptacle (M9182) 1 MSN 23636 only.

Any Supplier.

KPSE06F10-6S Connector (for S901) 1 MSN 23636 only.

Any Supplier.

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MODIFICATION No.


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Aircraft

G7490-01, Or Alt P/Ns, G7490-30 or


MSN 24440 MSN 24446 MSN 26961 MSN 24433

Notes:

1. Gables Control Panel G7490-04 may be installed as an interim measure.

Gables Control Panel G7490-30 to be installed when available at earliest maintenance input.

2. Rockwell Collins Transponder TPR-720 (part no: 622-7878-2010) may be re-installed as an interim measure.

Rockwell Collins Transponder TPR-901 (part no: 822-1338-003) to be installed when available at earliest maintenance input

3. Rockwell Collins Transponder TPR-901 (part no: 822-1338-003) already installed in aircraft MSN 23653

4. Rockwell Collins Control Panel TTC-920 (part no: 622-8974-008) may be installed as an interim measure.

Gables Control Panel G7492-05 to be installed when available at earliest maintenance input.

5. Gables control Panels P/N G7490-39 and Alternative P/N G7490-40 are identical, except that P/N G7490-40 has an additional function switch for the ABV/N/BLW function. “ABV” and “BLW” sets the altitude range that the cockpit VSI/TCAS display will show traffic. The altitude range that is available can be programmed from -2700 feet to +9900 feet.

6. Qty 2 of Co-axial switch Relay P/N 402-167 are required, one for new Co-axial switch Relay S901 and one to replace existing Co-axial switch Relay S900. P/N 402-166-3 may be used as an Alternate P/N. Note that the two Co-axial switch Relays must be of the same P/N.

7. Preferred Gables Control Panel P/N for aircraft MSN 23653 is G-7490-32. P/N G7490-40 is an approved alternative P/N for this aircraft.

8. For all undefined parts (splices, contacts, sleeves, etc.) use ‘standard parts’ from the Aircraft SWPM Chapter 20 or the AIPC.

9. Original Honeywell TRA-67A Transponders P/N 066-01127-1301 may be re-installed on aircraft MSN 25429 as an interim measure (ship-set only), but the aircraft will not be compliant with the intent of this Modification Summary document.

Honeywell TRA-67A Transponders (P/N 066-01127-1602) are to be installed on aircraft MSN 25429 when available at earliest maintenance input.

10. Original Honeywell Control Panel P/N 071-01503-2601 may be re-installed on aircraft MSN 25429 as an interim measure if the TRA-67A P/N 066-01127-1301 transponders are being re-installed, but the aircraft will not be compliant with the intent of this Modification Summary document.

11. Gables Control Panel P/N G-7490-40 is to be installed on aircraft MSN 25429 when available at earliest maintenance input.

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5.3 Major Parts Removed Per Aircraft

Part No. Description Qty Remarks/manufacturer/ Aircraft

622-7878-201 Rockwell Collins Transponder (TPR-720)

2


MSN 24299 (No: 2 ATC) MSN 24662 MSN 24699 MSN 27267 MSN 24785 MSN 24440 MSN 24446 MSN 26961 MSN 24433


MSN 24449 MSN 24027 MSN 23635 MSN 24025

822-0336-001

Rockwell Collins Transponder (TPR-900)

2 MSN 27924

MSN 24299 (No: 1 ATC)



066-1123-00 Bendix Transponder 2 MSN 24026

204 1600-6503 Control Panel 1 MSN 24026


Control Panel 1 MSN 24299


Control Panel 1 MSN 24825

622–8974–304 Rockwell Collins

Control Panel (TTC-920) 1 MSN 24662


Control Panel (TTC-920)1

MSN 24699 (See Paragraph 5.2, Note 4)

G6992-19 Gables Control Panel 1 MSN 27267

071-01477-0001 Honeywell Control Panel

(CTA-81A) 1 MSN 24785

G6992-18 Gables Control Panel 1 MSN 23653



MSN 23636 (No. 1 Transponder)

622-2224-001 Rockwell Collins Mode-C Transponder (621A-6A)

1 MSN 23636 (No. 2

Transponder)


Control Panel (TTC-920A) 1 MSN 23636

As installed Mode-C Transponder Tray 1 MSN 23636

(No. 2 Transponder Tray)

622-7878-301 Rockwell Collins Transponder (TPR-720)

2 MSN 23811

G6992-( ) Gables Control panel 1 MSN 23811

4061400-905 L3 model XS-910 2 MSN 24059

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Part No. Description Qty Remarks/manufacturer/ Aircraft


Control Panel (TTC-920) 1 MSN 24059

066-01127-1301 Honeywell TRA-67A

Transponders 2

MSN 25429 (See Para 5.2 Note 9)

071-01503-2601 Honeywell Control Panel 1 MSN 25429

(See Para 5.2 Note 11)

5.4 Documents and Drawings Required

5.4.1 ATL Documents

a) ATL/737/M556 Modification Summary Sheet b) ATL/737/E556 Engineering Order c) ATL10030-801 Wiring Diagram - Enhanced Mode ‘S’ (MSN 23635, MSN 23811, MSN 24059) d) ATL10030-802 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24025) e) ATL10030-803 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24027) f) ATL10030-804 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24449) g) ATL10030-805 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24825) h) ATL10030-806 Wiring Diagram - Enhanced Mode ‘S’ (MSN 27924) i) ATL10030-807 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24026) j) ATL10030-808 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24299) k) ATL10030-809 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24699) l) ATL10030-810 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24662) m) ATL10030-811 Wiring Diagram - Enhanced Mode ‘S’ (MSN 27267) n) ATL10030-812 Wiring Diagram - Enhanced Mode ‘S’ (MSN 24785) o) ATL10030-813 Wiring Diagram - Enhanced Mode ‘S’ (MSN 23653) p) ATL10030-814 Wiring Diagram - Enhanced Mode ‘S’ (MSN 23636) q) ATL AFM Supplement No. 48 SSR Mode ‘S’ Elementary and Enhanced Surveillance (Boeing 737-300) r) ATL AFM Supplement No. 51 SSR Mode ‘S’ Elementary and Enhanced Surveillance (Boeing 737-500) s) ATL10888-001 Installation – Relay Bracket (MSN 24662 only). t) ATL10404-001 Installation – Antenna Co-axial Relay (MSN 23636 only) u) ATL11350-801 Wiring Diagram - Enhanced Mode ‘S’ (MSN 25429, 24440, 24446, 26961 & 24433) v) AFM Supp No.11350-AFM-00001 for SSR Mode ‘S’ Elementary and Enhanced Surveillance (Boeing 737-400)

5.4.2 Rockwell Collins Documents

Document number: TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70; Dated: Apr 27, 2006; Revision: 17.

Document number: CPN 523-0805869; Dated: July 10, 2004; Revision: 10

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

5.4.3 Honeywell Documents

Honeywell Maintenance Manual for TRA-67 Mode S ATC Link Transponder System, 34-54-11, Revision 10; Dated: 12 September 2003.

Honeywell TRA-67A Declaration of Design and Performance document number 176.

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5.4.4 Gables Engineering Documents

a) Installation Manual for Flight ID/ATC/TCAS Control Panel, IST.G7490-( ), Revision 01, 28 June 2004.

b) Declaration of Design & Performance Model G7490-30, GD-DDP-G7490-30, Revision 01, June 28, 2006.

c) Declaration of Design & Performance Model G7490-39, GD-DDP-G7490-39, Revision 01, January 24, 2005.

d) Declaration of Design & Performance Model G7490-40, GD-DDP-G7490-40, Revision 01, April, 2007.

e) Installation Manual for Flight ID/ATC/TCAS Control Panel, IST.G7492-( ), Revision 03, 01 June 2006.

5.4.5 Test Equipment Document

a) TIC TR-220 Multifunction Test Set; Document No: 90008088-1; Revision: D; Dated: 01 July 2005.

b) Alternative Test Set – Aeroflex IFR 6000 Test Set; Document No: 1002-5800-2PO; Revision: 4; Dated: Jan 2006.

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.

5.5 Instructions

5.5.1 Refer to Engineering Order ATL/737/E556.

6 Basis of Approval

6.1 Certification Basis

6.1.1 The certification basis applied to the approval of this modification is unchanged from that applied to the EASA Type Certificate Data Sheet TCDS IM.A.120, Issue 09 dated 12 July 2012, for Boeing 737 aircraft type.

6.1.2 In accordance with European Union Commission Regulation No. 1702/2003, Part 21a.101, Designation of Applicable Certification Specifications and Environmental Protection Requirements, the Certification Specification determined for this modification is CS-25 Amendment 12, dated 13 July 2012.

6.2 Additional Advisory Data

6.2.1 JAA Administrative and Guidance Material Section One: General Part 3: Temporary Guidance Leaflet (TGL) No. 13 “Certification of Mode ‘S’ Transponder Systems for Elementary Surveillance”.

6.2.2 JAA Notice of Proposed Amendment (NPA) 20-12a, 10 March 2004, ACJ 20X11 “Certification of Mode ’S’ Transponder Systems for Enhanced Surveillance”, which is now superseded by EASA AMC 20-13.

6.3 Environmental Requirements

6.3.1 The units installed by this modification shall have no effect on noise or environmental pollution.

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MODIFICATION No.


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6.4 Operational Approvals

6.4.1 EU OPS 1 paragraphs pertaining to Transponder System.

6.5 Other Airworthiness Approvals

6.5.1 None Applicable.

6.6 Equipment Approval

6.6.1 An appropriate assessment will be carried out to determine that the equipment is safe and fit for purpose, to show compliance with CS 25.1301 and 1309 as a minimum.

6.7 Additional Requirements

6.7.1 None Applicable.

7 Compliance with Requirement

7.1 Certification Basis

7.1.1 The certification basis as defined in paragraph 6.1 of this document is unaffected by the introduction of this modification.

7.1.2 For guidance on the means employed to show compliance with the requirements of CS 25, use the following chart. In accordance with European Union Commission Regulation No. 1702/2003, Part 21a.101, Designation of Applicable Certification Specifications and Environmental Protection Requirements, the Certification Specification determined for this modification is CS-25 at amendment 12, dated 13 July 2012.

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MODIFICATION No.


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Type of Compliance Means of Compliance Associated Compliance

Documents

Engineering Evaluation

MC0 : Compliance statement reference to Type

Design document election of methods,

factors, etc. definitions

Type Design Documents Recorded Statements

MC1 : Design review Description, drawings

MC2 : Calculations/Analysis Substantiation Reports

MC3 : Safety Assessment Safety Analysis

Test

MC4 : Laboratory Test

Test Programmes Test Reports Test Interpretations

MC5 : Ground Test on related

Product

MC6 : Flight Tests

MC8 : Simulation

Inspection MC7 : Design Inspection Inspection Reports

Equipment Qualification MC9 : Equipment Qualification Note: Equipment qualification is a process which may include all previous means of compliance.

7.1.3 The following requirements of EASA Certification Specification CS25 for Large Transport Aircraft have been considered:

CS 25 Airworthiness Requirements Means of

Compliance Drawings / Reports / Remarks

SUBPART A - GENERAL

.1 Applicability MC1 The certification basis applied to the approval of this modification is unchanged from that applied to the original EASA Type Certificate Data Sheet TCDS IM.A.120, Issue 09 dated 12 July 2012, for Boeing 737 aircraft type.

SUBPART B - FLIGHT

GENERAL

.20 Scope MC0 The requirements of this Subpart B apply to aircraft powered by turbine engines.

.21 Proof of Compliance MC0 The aircraft flight characteristics are not affected by this modification.

.23 Load distribution limits MC1 For change in weight refer to paragraph 9 of this document.

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.25 Weight limits MC1 For change in weight refer to paragraph 9 of this document.

.27 Centre of gravity limits MC1 For change in weight refer to paragraph 9 of this document.

.29 Empty weight and corresponding centre of gravity

MC1 Changes to the aircraft Weight & Balance manual are detailed in paragraph 9 of this document.

.31 Removable Ballast. MC0 No removable ballast is added or deleted by this modification.

.33 Propeller speed and pitch limits

MC0 No changes to the engine / propulsion systems are incorporated.

PERFORMANCE

.101 General

MC0 The aircraft performance is not affected by this modification.

.103 Stall speed

.105 Take-off

.107 Take-off speeds

.109 Accelerate-stop distance

.111 Take-off path

.113 Take-off distance and take-off run

.115 Take-off flight path

.117 Climb: general

.119 Landing climb: all-engines operating

.121 Climb: one-engine-inoperative

.123 En-route flight paths

.125 Landing

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MODIFICATION No.


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CONTROLLABILITY AND MANOEUVRABILITY

.143 General

MC0 The controllability and manoeuvrability of the aircraft are not affected by this modification.

.145 Longitudinal control

.147 Directional and lateral control

.149 Minimum control speed

TRIM

.161 Trim MC0 Functions of the aircraft trimming system are not affected by this modification.

STABILITY

.171 General

MC0 Functions of the aircraft stability system are not affected by this modification.

.173 Static longitudinal stability

.175 Demonstration of static longitudinal stability

.177 Static directional and lateral stability

.181 Dynamic stability

STALLS

.201 Stall demonstration

MC0 Aircraft stall characteristics are not affected by this modification.

.203 Stall characteristics

.207 Stall warning

GROUND HANDLING CHARACTERISTICS

.231 Longitudinal stability and control

MC0 Aircraft ground handling characteristics are not affected by this modification.

.233 Directional stability and control

.235 Taxiing condition

.237 Wind velocities

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MISCELLANEOUS FLIGHT REQUIREMENTS

.251 Vibration and buffeting

MC0 Aircraft flight controls are not affected by this modification.

.253 High-speed characteristics

.255 Out-of-trim characteristics

SUBPART C – STRUCTURE

GENERAL

.301 Loads

MC0 Aircraft Structure is not affected by this modification.

.302 Interaction of systems and structures

.303 Factor of safety

.305 Strength and deformation

.307 Proof of structure MC0 Methods used in the structural analysis will be in keeping with those proven with experience to be reliable. No static or dynamic structural tests are carried out as part of this modification.

FLIGHT LOADS

.321 General MC0 The aircraft flight loads are not affected by this modification.

FLIGHT MANOEUVRE AND GUST CONDITIONS

.331 Symmetric manoeuvring conditions

MC0 Flight symmetric manoeuvre and gust condition limitations are not affected by this modification.

.333 Flight manoeuvring envelope

.335 Design airspeeds

.337 Limit manoeuvring load factors

.341 Gust and turbulence loads

.343 Design fuel and oil loads

.345 High lift devices

.349 Rolling conditions

.351 Yaw manoeuvre conditions

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SUPPLEMENTARY CONDITIONS

.361 Engine and APU torque

MC0 No supplementary conditions are applicable to this modification.

.363 Side load on engine and auxiliary power unit mounts

.365 Pressurised compartment loads

.367 Unsymmetrical loads due to engine failure

.371 Gyroscopic loads

.373 Speed control devices

CONTROL SURFACE AND SYSTEM LOADS

.391 Control surface loads: general

MC0 Loads on the aircraft aerodynamic control surfaces and control systems are not affected by this modification.

.393 Loads parallel to hinge line

.395 Control system

.397 Control system loads

.399 Dual control system

.405 Secondary control system

.407 Trim tab effects

.409 Tabs

.415 Ground gust conditions

.427 Unsymmetrical loads

.445 Outboard fins

.457 Wing-flaps

.459 Special devices

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GROUND LOADS

.471 General

MC0 Loads generated in all ground handling conditions are not affected by this modification.

.473 Landing load conditions and assumptions

.477 Landing gear arrangement

.479 Level landing conditions

.481 Tail-down landing conditions

.483 One-gear landing conditions

.485 Side load conditions

.487 Rebound landing condition

.489 Ground handling conditions

.491 Taxi, takeoff and landing roll

.493 Braked roll conditions

.495 Turning

.497 Tail-wheel yawing

.499 Nose-wheel yaw and steering

.503 Pivoting

.507 Reversed braking

.509 Towing Loads

.511 Ground load: unsymmetrical loads on multiple-wheel units

.519 Jacking and tie-down provisions

EMERGENCY LANDING CONDITIONS

.561 General MC2 The installations within the aircraft will remain attached at the ultimate inertia forces specified.

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.562 Emergency landing dynamic conditions

MC0 Emergency landing dynamic conditions are not affected by this modification.

.563 Structural ditching provisions

MC0 Structural ditching provisions are not affected by this modification.

FATIGUE EVALUATION

.571 Damage-tolerance and fatigue evaluation of structure

MC1 Failure of the installation in fatigue will not result in catastrophic failure in any critical structure. Installations do not attach to or affect any damage tolerant structure.

LIGHTNING PROTECTION

.581 Lightning protection MC1 Newly installed units replace existing parts in same internal locations using Boeing 737 aircraft bonding procedures to bond the components to the airframe; there is no risk of serious injury or damage to the aircraft in the event of a lightning strike.

SUBPART D – DESIGN AND CONSTRUCTION

GENERAL

.601 General MC1 All design features and details of this modification are of methods proven suitable for the intended purpose.

.603 Materials. MC1 All materials used in this modification conform to approved specifications or recognised vendor / industry standards.

.605 Fabrication methods MC0 No new fabrication methods are introduced in this modification.

.607 Fasteners MC0 Failure of any single fastener will not jeopardise continued safe operation of the aircraft.

.609 Protection of structure MC1 The modification incorporated introduces no weathering, corrosion, abrasion or moisture traps on the aircraft structure.

.611 Accessibility provisions MC1 The modification installation is fully accessible for periodic inspection. The location of the new equipment is the same as that of the removed equipment.

.613 Material strength properties and design values

MC1 Newly installed units replace existing parts in same internal locations. The mounting structures are installed in accordance with Boeing 737 designed method of installation.

.619 Special factors MC0 Special factors are not applicable for the incorporation of this modification.

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MODIFICATION No.


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.621 Casting factors MC0 No cast parts are incorporated in this modification.

.623 Bearing factors MC0 No bearing factors are applicable to this modification.

.625 Fitting factors MC0 No fitting factors are applicable to this modification.

.629 Aero-elastic stability requirements

MC0 Aero-elastic stability of the aircraft is not affected by this modification.

.631 Bird strike damage MC0 No part of this modification is subject to possible bird strike damage.

CONTROL SURFACES

.651 Proof of strength

MC0 Loads on the aircraft aerodynamic control surfaces and control systems are not affected by this modification.

.655 Installation

.657 Hinges

CONTROL SYSTEMS

.671 General

MC0

Each control and control system ability to operate with the ease, smoothness, and positiveness appropriate to its function has not been affected by this modification action.

.672 Stability augmentation and automatic and power operated systems

.675 Stops

.677 Trim systems

.679 Control system gust locks

.681 Limit load static tests

.683 Operation tests

.685 Control system details

.689 Cable systems

.693 Joints

.697 Lift and drag devices, controls

.699 Lift and drag device indicator

.701 Flap and slat interconnection

.703 Take-off warning system

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LANDING GEAR

.721 General

MC0 The aircraft landing gear is not affected by this modification.

.723 Shock absorption tests

.729 Retracting mechanism

.731 Wheels

.733 Tyres

.735 Brakes and braking systems

.745 Nose-wheel steering

PERSONNEL AND CARGO ACCOMMODATIONS

.771 Pilot compartment MC0 This modification will not affect personnel and Pilot compartment.

.772 Pilot compartment doors MC0 This modification will not affect personnel and Pilot compartment doors.

.773 Pilot compartment view MC0 This modification will not affect personnel and Pilot compartment views.

.775 Windshields and windows MC0 This modification will not affect windshields and windows.

.777 Cockpit controls MC0 This modification will not affect personnel and cargo accommodations

.779 Motion and effect of cockpit controls

MC0 This modification will not affect cockpit controls.

.781 Cockpit control knob shape

MC0 This modification will not affect cockpit controls knob shape.

.783 Doors MC0 This modification will not affect any doors.

.785 Seats, berths, safety belts and harnesses

MC0 This modification will not affect any seats, berths, safety belts, and harnesses.

.787 Stowage compartments MC0 This modification will not affect any stowage compartments.

.789 Retention of items of mass in passenger and crew compartments and galleys

MC0 This modification will not affect any retention of items of mass in passenger, crew compartments and galleys.

.791 Passenger information signs and placards

MC0 This modification will not affect any passenger information signs and placards.

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MODIFICATION No.


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.793 Floor surfaces MC0 This modification will not affect any floor surfaces.

.795 Security considerations MC0 This modification will not affect any security of the aircraft.

EMERGENCY PROVISIONS

.801 Ditching

MC0 This modification has no affect on the Emergency provisions of the aircraft.

.803 Emergency evacuation

.807 Emergency exits

.809 Emergency exit arrangement

.810 Emergency egress assist means and escape routes

.811 Emergency exit marking

.812 Emergency lighting

.813 Emergency exit access

.815 Width of aisle

.817 Maximum number of seats abreast

.819 Lower deck service compartments (including galleys)

VENTILATION AND HEATING

.831 Ventilation

MC0 This modification makes no changes to the aircraft ventilation and heating systems.

.832 Cabin ozone concentration

.833 Combustion heating system

PRESSURISATION

.841 Pressurised cabins MC0

This modification has no affect on cabin pressurisation.

.843 Tests for pressurised cabins

FIRE PROTECTION

.851 Fire extinguishers MC0 This modification makes no changes to the type, quantity or location of hand held fire extinguishers within the aircraft.

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MODIFICATION No.


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.853 Compartment interiors MC0 This modification makes no changes to the design or materials used in compartment interiors.

.854 Lavatory fire protection MC0 This modification does not affect the fire protection within lavatories.

.855 Cargo and baggage compartments

MC0 This modification makes no changes to any of the baggage compartments.

.857 Cargo compartment classification


.858 Cargo compartment fire detection systems


.859 Combustion heater fire protection

MC0 This modification does not affect the combustion heater system.

.863 Flammable fluid fire protection

MC0 This modification makes no changes to any flammable fluid fire protection systems.

.865 Fire protection of flight controls, engine mounts, and other flight structure

MC0 This modification makes no changes to any flight controls, engine mounts, and other flight structure.

.867 Fire protection: other components

MC0 This modification makes no changes in areas subject to heat from the nacelle area.

.869 Fire protection: systems MC0 All electrical wiring introduced conforms to BMS13-60 and meets the requirements of Part I, Appendix ‘F’ of CS-25. Wire to be used is “BMS 13-60, Type 34, Class 2, 24 AWG (or equivalent) for multi-core wires” and “BMS 13-60, Type 1, Class 1, 24 AWG (or equivalent) for single core wires”.

MISCELLANEOUS

.871 Levelling means

MC0 Not affected by this modification action. .875 Reinforcement near propellers

.899 Electrical bonding and protection against static electricity

MC1 The mounting structure for the new equipment is electrically bonded in accordance with the aircraft design and Maintenance Manual instructions. There is no perceived risk of serious injury to personnel, ignition of flammable vapours or interference with existing installed electrical / electronic equipment.

Bonding tests to be carried out between the new transponder and aircraft structure (maximum value of 0.01 Ohms) and figures recorded.

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SUBPART E – POWERPLANT

GENERAL

.901 Installation

MC0 This modification has no effect on the aircraft engine or propulsion systems.

.903 Engines

.904 Automatic Takeoff Thrust Control System (ATTCS)

.905 Propellers

.907 Propeller vibration

.925 Propeller clearance

.929 Propeller de-icing

.933 Reversing systems

.934 Turbo-jet engine thrust reverser system tests

.937 Turbo-propeller-drag limiting systems

.939 Turbine engine operating characteristics

.941 Inlet, engine, and exhaust compatibility

.943 Negative acceleration

.945 Thrust or power augmentation system

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FUEL SYSTEM

.951 General

MC0 This modification has no effect on the aircraft fuel systems.

.952 Fuel system analysis and test

.953 Fuel system independence

.954 Fuel system lightning protection

.955 Fuel flow

.957 Flow between interconnected tanks

.959 Unusable fuel supply

.961 Fuel system hot weather operation

.963 Fuel tanks: general

.965 Fuel tank tests

.967 Fuel tank installations

.969 Fuel tank expansion space

.971 Fuel tank sump

.973 Fuel tank filler connection

.975 Fuel tank vents

.977 Fuel tank outlet

.979 Pressure fuelling system

.981 Fuel tank ignition prevention.

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FUEL SYSTEM COMPONENTS

.991 Fuel pumps

MC0 This modification has no effect on the aircraft fuel system accessory components.

.993 Fuel system lines and fittings

.994 Fuel system components

.995 Fuel valves

.997 Fuel strainer or filter

.999 Fuel systems drains

.1001 Fuel jettisoning system

OIL SYSTEM

.1011 General

MC0 This modification has no effect on the aircraft oil system.

.1013 Oil tanks

.1015 Oil tank tests

.1017 Oil lines and fittings

.1019 Oil strainer or filter

.1021 Oil system drains

.1023 Oil radiators

.1025 Oil valves

.1027 Propeller feathering system

COOLING

.1041 General

MC0

This modification has no effect on the aircraft engine, propulsion, fuel, oil, cooling, induction, exhaust, controls, accessories, or fire protection systems.

.1043 Cooling tests

.1045 Cooling test procedures

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AIR INTAKE SYSTEM

.1091 Air intake

MC0 This modification has no effect on the aircraft air intake system.

.1093 Air intake system de-icing and anti-icing provisions

.1103 Air intake system ducts and air duct systems

EXHAUST SYSTEM

.1121 General

MC0 This modification has no effect on the aircraft exhaust system. .1123 Exhaust piping

POWERPLANT CONTROLS AND ACCESSORIES

.1141 Powerplant controls: general

MC0 This modification has no effect on the aircraft Powerplant controls and accessories.

.1143 Engine controls

.1145 Ignition switches

.1149 Propeller speed and pitch controls

.1153 Propeller feathering controls

.1155 Reverse thrust and propeller pitch settings below the flight regime

.1161 Fuel jettisoning system controls

.1163 Powerplant accessories

.1165 Engine ignition systems

.1167 Accessory gearboxes

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POWERPLANT FIRE PROTECTION

.1181 Designated fire zones: regions included

MC0 This modification has no effect on the aircraft Powerplant fire protection systems.

.1182 Nacelle areas behind firewalls, and engine pod attaching structures containing flammable fluid lines

.1183 Flammable fluid-carrying components

.1185 Flammable fluids

.1187 Drainage and ventilation of fire zones

.1189 Shut-off means

.1191 Firewalls

.1193 Cowling and nacelle skin

.1195 Fire-extinguisher systems

.1197 Fire-extinguishing agents

.1199 Extinguishing agent containers

.1201 Fire extinguishing system materials

.1203 Fire-detector system

.1207 Compliance

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SUBPART F – EQUIPMENT

GENERAL

.1301 Function and installation MC1 MC9

MC5

The Elementary and Enhanced Mode ‘S’ Transponder System incorporated in accordance with this modification is of a kind appropriate to its intended function will transmit additional data, which will be displayed to the air traffic controller.

Tests of the functionality will be performed as called up in this document Paragraph 8.

All information required for identification and proper function will be displayed on the equipment at the appropriate locations.

All cables connectors and terminals newly introduced are identified and labelled in accordance with drawings ATL10030-801 et seq. or ATL11350-801.

.1303 Flight and navigation instruments

MC0 The location and installation of all required flight and navigation instruments is unchanged from the existing approved locations.

.1305 Powerplant instruments. MC0 This modification has no effect on the power plant instruments.

.1307 Miscellaneous equipment MC0 Electrical protective devices are as prescribed in CS 25.

.1309 Equipment, systems, and installations.

MC1

The Elementary and Enhanced Mode ‘S’ Transponder’ System installed under this Modification Summary ATL/737/556 replaces an existing ATC Transponder System.

Faults developed in the Elementary and Enhanced Mode ‘S’ Transponder’ System in relation to other systems will not adversely affect the safe operation of the aircraft.

Should the Elementary and Enhanced Mode ‘S’ Transponder’ System malfunction or fail a warning indication is provided to the flight crew via the control panel.

This will not present a hazard to the aircraft whilst all other systems are operational.

In the event of failure due diligence is to be carried out by the flight crew to maintain safe operation of the aircraft.

The aircraft is not dependent on the functioning of the Elementary and Enhanced Mode ‘S’ Transponder’ System for normal flight and landings.

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.1310 Power source capacity and distribution

MC1 The increase in power required to be supplied will have no effect on the operation of the power source. The additional load is deemed negligible.

This modification does not affect the power source capacity or distribution system.

Refer paragraph 10 for electrical loads analysis.

.1315 Negative acceleration MC0 No hazard will result from negative acceleration sustained by the aircraft.

.1316 System lightning protection

MC0 This modification has no effect on the aircraft lightning protection.

INSTRUMENTS: INSTALLATION

.1321 Arrangement and visibility MC0 Flight instruments location and operation are not affected by this modification action.

.1322 Warning, caution, and advisory lights

MC0 Warning, caution and advisory lights are not affected by this modification action.

.1323 Airspeed Indicating system

MC0 Flight instruments location and operation are not affected by this modification action.

.1325 Static pressure systems

.1326 Pitot heat indication systems

.1327 Direction indicator

.1329 Automatic pilot system

.1331 Instruments using a power supply

.1333 Instrument systems

.1335 Flight director systems

.1337 Powerplant instruments

ELECTRICAL SYSTEMS AND EQUIPMENT

.1351 General MC1 The increase in power required to be supplied will have no effect on the operation of the power source. The additional load is deemed negligible.

This modification does not affect the power source capacity or distribution system.

Refer to paragraph 10 for electrical loads analysis.

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.1353 Electrical equipment and installations

MC1 The system wiring complies with the requirements of the Boeing Standard Wiring Practices Manual. Wire to be used is “BMS 13-60, Type 34, Class 2, 24 AWG (or equivalent) for multi-core wires” and “BMS 13-60, Type 1, Class 1, 24 AWG (or equivalent) for single core wires” in accordance with wiring diagram ATL10030-801 et seq. or ATL11350-801.

This wire meets the requirements regard flame resistance and toxicity.

Routing and segregation of wiring is in accordance with Boeing Standard Wiring Practices Manual, Chapter 20.

All wiring to connectors and terminals are identified and installed to negate the risk of damage from external influences.

.1355 Distribution system MC0 The distribution system is unchanged from the existing configuration.

.1357 Circuit protective devices MC1 Existing circuit protection and wiring will be used to supply power to the new equipment.

.1360 Precautions against injury MC0 The modification has no effect on the existing precautions against injury.

.1362 Electrical supplies for emergency conditions

MC0 This modification has no effect on the electrical supplies for emergency conditions.

.1363 Electrical system tests MC0 This modification has no effect on the aircraft electrical system test.

.1365 Electrical appliances, motors and transformers

MC0 This modification has no effect on electrical appliances, motors or transformers.

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LIGHTS

.1381 Instrument lights

MC0 The installation and function of the instrument and aircraft lights are not affected by this modification.

.1383 Landing lights

.1385 Position light system installation

.1387 Position light system dihedral angles

.1389 Position light distribution and intensities

.1391 Minimum intensities in the horizontal plane of forward and rear position lights

.1393 Minimum intensities in any vertical plane of forward and rear position lights

.1395 Maximum intensities in over-lapping beams of forward and rear position lights

.1397 Colour specifications

.1401 Anti-collision light system

.1403 Wing icing detection lights

SAFETY EQUIPMENT

.1411 General

MC0 All required safety equipment is not affected by this modification.

.1415 Ditching equipment

.1419 Ice Protection

.1421 Megaphones

.1423 Public address system

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MISCELLANEOUS EQUIPMENT

.1431 Electronic equipment MC1

MC5

The Elementary and Enhanced Mode ‘S’ Transponder System and associated wiring installed will not adversely affect the simultaneous operation of any other aircraft equipment essential to the safe operation of the aircraft.

Power requirements comply with CS 25.1355 (c).

Equipment has been located where removed equipment was fitted.

Routing and segregation of wiring is in accordance with Boeing Standard Wiring Practices Manual, Chapter 20.

Ground Testing will be conducted in accordance with ATL/737E556 paragraph 7 to ensure that the installation does not adversely affect the response, operation, or accuracy of any equipment essential to the safe operation of the aircraft.

.1433 Vacuum systems MC0 Installation and function of the vacuum systems is not affected by this modification.

.1435 Hydraulic Systems MC0 Installation and function of the Hydraulic systems is not affected by this modification.

.1436 Pneumatic systems – high pressure

MC0 Installation and function of the pneumatic systems – high pressure is not affected by this modification.

.1438 Pressurisation and low pressure pneumatic systems

MC0 Installation and function of the pressurisation and low pressure pneumatic systems is not affected by this modification.

.1439 Protective breathing equipment

MC0 Protective breathing equipment installations are not affected by this modification action.

.1441 Oxygen equipment and supply

MC0 Function of the oxygen equipment and supply is not affected by this modification.

.1443 Minimum mass flow of supplemental oxygen

MC0 The minimum mass flow at each oxygen dispensing unit is not affected by this modification.

.1445 Equipment standards for the oxygen distribution system

MC0 The equipment standards for the oxygen distribution system are not affected by this modification.

.1447 Equipment standards for oxygen dispensing units

MC0 The equipment standards for the oxygen dispensing units are not affected by this modification.

.1449 Means for determining use of oxygen

MC0 Crew monitoring of oxygen use is not affected by this modification.

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.1450 Chemical oxygen generators

MC0 The function of the chemical oxygen generators is not affected by this modification.

.1453 Protection of oxygen equipment from rupture

MC0 Protection of the oxygen equipment is not affected by this modification.

.1455 Draining of fluids subject to freezing

MC0 Protection of the oxygen equipment from rupture is not affected by this modification.

.1457 Cockpit voice recorders MC0 Fluid drains are not altered by this modification.

.1459 Flight recorders MC0 The function and installation of the cockpit voice is not affected by this modification.

.1461 Equipment containing high energy rotors.

MC0 The function and installation of the flight recorders is not affected by this modification.

SUBPART G – OPERATING LIMITATIONS AND INFORMATION

.1501 General MC0 No changes to the operating limitations of the aircraft are introduced as a result of this modification.

OPERATING LIMITATIONS

.1503 Airspeed limitations: general

MC0 No changes to the operating limitations of the aircraft are introduced as a result of this modification.

.1505 Maximum operating limit speed

.1507 Manoeuvring speed

.1511 Flap extended speed

.1513 Minimum control speed

.1515 Landing gear speeds

.1516 Other speed limitations

.1517 Rough air speed, VRA

.1519 Weight, centre of gravity and weight distribution

.1521 Powerplant limitations

.1523 Minimum flight crew

.1525 Kinds of operations

.1527 Ambient air temperature and operating altitude

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.1529 Instructions for Continued Airworthiness.

MC1 Refer to paragraph 13.0 of this document for continued airworthiness instructions.

.1531 Manoeuvring flight load factors

MC0 The operating limitations listed are not affected by this modification.

.1533 Additional operating limitations

MC0 The operating limitations listed are not affected by this modification.

MARKINGS AND PLACARDS

.1541 General

MC0 The aircraft Markings and Placards listed are not affected by this modification.

.1543 Instrument markings; general

.1545 Airspeed limitation information

.1547 Magnetic direction indicator

.1549 Powerplant instruments

.1551 Oil quantity indicator

.1553 Fuel quantity indicator

.1555 Control markings

.1557 Miscellaneous markings and placards

.1561 Safety equipment

.1563 Airspeed placard

AEROPLANE FLIGHT MANUAL

.1581 General MC9 Flight Manual Supplement ATL No. 48, is to be inserted into the Boeing 737-300 series aircraft Flight Manual after incorporation of STC Modification Summary ATL/737/M556.

Flight Manual Supplement ATL No. 51, is to be inserted into the Boeing 737-500 series aircraft Flight Manual after incorporation of STC Modification Summary ATL/737/M556.

Flight Manual Supplement ATL No. 11350-AFM-00001, is to be inserted into the Boeing 737-400 series aircraft Flight Manual after incorporation of STC Modification Summary ATL/737/M556.

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.1583 Operating limitations MC0 This modification does not affect any of the aeroplane operating limitations.

.1585 Operating procedures MC0 This modification does not affect any of the aeroplane operating procedures.

.1587 Performance information MC0 This modification does not affect any of the aeroplane performance information.

SUPPLEMENTARY INFORMATION

.1591 Performance Information for Operations with Contaminated Runway Surface Conditions

MC0 No additional performance information is required.

SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEM

.1701 Definition MC1 This modification is raised to introduce Elementary and Enhanced Mode ‘S’ Transponders in accordance with operator requirements.

.1703 Function and Installation; EWIS

MC1 The EWIS Components incorporated in accordance with this modification are of a kind appropriate to their intended function, in that they are qualified for airborne use, and are installed according to Boeing Standard Wiring Practices and the limitations specified by the manufacturer regarding operating temperature, local humidity, voltage drop, and current capacity, such as to ensure safe performance of its intended function of transmitting electrical energy, including data, and signals, and to minimise mechanical strain.

The EWIS components are not located in areas of known moisture accumulation.

.1705 Systems and Functions; EWIS

MC1 The EWIS Components affected by this modification are considered to be an integral part of the ATC System, and as such have been assessed against the requirements of CS-25, the most relevant paragraphs of which are cross-referenced below:

25.1310 – Power Source Capacity and Distribution

25.1351 – General

25.1431(c),(d) – Electronic Equipment.

It has been shown elsewhere in this matrix that none of the requirements of these paragraphs have been affected by this modification action.

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.1707 System Separation; EWIS MC1 The routing of wires and EWIS components affected by this modification is such that appropriate separation is provided to minimise the interference (electrical or mechanical) between individual wires, wire bundles, and static objects such as aircraft structure, so that a hazard is not presented to the aircraft. Separation is achieved primarily by physical distance. Separation distances are determined in accordance with the factors stipulated by this requirement. The Methods used to determine separation are in accordance with Boeing Standard Wiring Practices Manual D6-54446, which has been shown through prolonged service of installed EWIS components to be safe Methodology.

.1709 System Safety; EWIS MC1 An appraisal of the integrity and safety of the EWIS system components installation in respect to deviations from normal industry-accepted installation practices has been carried out. No new methods are introduced by this modification action. Those that have been used are traditional, well proven methods, which are defined in the Boeing Standard Wiring Practices Manual D6-54446, and have been adhered to.

The proper functioning of the new EWIS components under operating and environmental conditions is substantiated by comparable service experience on other aeroplanes of the same type, and is installed and routed so as to not adversely interfere with other EWIS components, equipment and systems.

This modification does not affect existing circuit breakers installed.

Electrical interference likely to be present in the aircraft will not result in hazardous effects upon the aircraft or its systems except under extremely remote conditions.

The capability to check a EWIS component condition is provided by using existing aircraft cable runs which are checked on periodic basis as part of the aircrafts maintenance program.

Substantiation of the proper functioning of the newly installed EWIS components is shown by test; Engineering Order ATL/737/E556 Paragraph 7 refers.

The likelihood of each catastrophic failure condition is considered to be extremely improbable and will not result from any one single failure, whilst each hazardous failure condition is considered to be extremely remote.

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.1711 Component identification; EWIS

MC1 EWIS components will be labelled or otherwise identified using a consistent method that facilitates identification of each EWIS component, its function, and its design limitations, where applicable.

EWIS components that cannot be marked physically will be identified by means of placards.

The identifying markings mentioned above will remain legible throughout the expected service life of the EWIS components.

The means used for identifying each EWIS component as required by this paragraph will not have an adverse effect on the performance of that component throughout its expected service life.

Identification for EWIS components introduced by this modification is consistent with the identification scheme of the original type design.

.1713 Fire Protection; EWIS MC1 Any failures or malfunctions of the EWIS components installed by this modification will not cause harmful or hazardous concentrations of gases or vapours in excess of the levels prescribed in CS-25.831(c) and CS-25.863.

.1715 Electrical bonding and protection against static electricity; EWIS

MC1 There is no change by this modification to EWIS components used for electrical bonding under both normal and fault conditions; they still meet the requirement of CS-25.899.

.1717 Circuit protective devices; EWIS

MC1 EWIS components installed by this modification are compatible with the circuit protection devices required by CS-25.1357, so that a fire or smoke hazard cannot be created under temporary or continuous fault conditions.

Circuit protective devices are unchanged by this modification.

.1719 Accessibility Provisions;

EWIS

MC1 The EWIS components introduced by this modification are installed as such as to facilitate full access for periodic inspection and/or test. Requirements for periodic inspection are detailed in the aircraft Maintenance Schedule, and methods are detailed in Paragraph 13, Continued Airworthiness, of Modification Summary Document ATL/737/M556, and in the Boeing Standard Wiring Practices Manual.

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.1721 Protection of EWIS MC1 Existing cable runs are used to provide protection in accordance with the Aircraft Standard Wiring Practice Manual, which prevent personnel from stepping, walking or climbing on the components and/or wire.

The EWIS components located in the fight deck/passenger compartment are installed such as to minimise damage due to the movement of people in the aeroplane during all phases of flight, or maintenance in accordance with the Aircraft Standard Wiring Practice Manual.

In the event of damage or failure of components, a fire will not be created.

.1723 Flammable fluid protection; EWIS

MC0 No new EWIS components are located in “areas” where flammable fluid or vapours might escape, so as to minimise the probability of ignition by separation methods described in CS25.1707.

.1725 Power-plants; EWIS MC0 Not applicable to this modification. EWIS associated with the aircraft power-plants will remain compliant with the requirements of CS-25.1725.

.1727 Flammable Fluid Shutoff Means; EWIS

MC0 Not applicable to this modification. EWIS associated with flammable fluid shutoff means and control will remain compliant with the requirements of this paragraph and CS-25.1189.

.1729 Instructions for Continued Airworthiness; EWIS

MC1 Instructions for Continued Airworthiness applicable to EWIS in accordance with the requirements of CS-25.1529 and Appendix H paragraphs H25.4 and H25.5 appear in Paragraph 13 of this Modification Summary Document ATL/737/M556. Paragraph 8 of this compliance document refers.

Boeing have issued an Electrical Wiring Interconnection System, (EWIS) Instructions for Continued Airworthiness (ICA) document see Maintenance Review Board Report D6 82981-MRBR dated March 2009. (specifically Section 2 - Systems And Powerplant Maintenance Program), for the Boeing 737-300/400/500 Series aircraft as defined in CS25.1701, and in accordance with CS25 Appendix H paragraph H25.5 and AMC appendix H25.5 paragraphs 1 and 6. The instructions included in this document have been reviewed by ATL in light of the changes introduced by this modification, and it has been determined that no further inspection levels and intervals are required.

.1731 Power-plant and APU fire detector system; EWIS

MC0 Not applicable to this modification. EWIS components that are part of each fire or overheat detector system will remain compliant with the requirements of this paragraph.

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SUBPART J – AUXILIARY POWER UNIT INSTALLATIONS

GENERAL

J901 Installation MC0 This modification does not affect any of the aeroplane’s APU installations.

J903 Auxiliary Power Unit MC0 This modification does not affect the aeroplane’s APU.

J939 APU operating characteristics

MC0 This modification does not affect the aeroplane’s APU operating characteristics.

J943 Negative acceleration MC0 This modification does not affect the aeroplane’s APU negative acceleration.

FUEL SYSTEM

J951 General

MC0 This modification does not affect the aeroplane’s fuel system, tests, operation, components, or fittings.

J952 Fuel system analysis and test

J953 Fuel system independence

J955 Fuel flow

J961 Fuel system hot weather operation

J977 Fuel tank outlet

J991 Fuel pumps

J993 Fuel system lines and fittings

J994 Fuel system components

J995 Fuel valves

MC0 This modification does not affect the aeroplane’s fuel system, tests, operation, components, or fittings. J997 Fuel strainer or filter

OIL SYSTEM

J1011 Oil System General

MC0 This modification does not affect the aeroplane’s oil system, lines, fittings, filter, drains, radiators or valves.

J1017 Oil lines and fittings

J1019 Oil filter

J1021 Oil system drains

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J1023 Oil radiators

J1025 Oil valves

COOLING

J1041 General

MC0 This modification does not affect the aeroplane’s cooling system, tests or procedures.

J1043 Cooling tests

J1045 Cooling test procedures

AIR INTAKE AND BLEED AIR DUCT SYSTEMS

J1091 Air intake

MC0 This modification does not affect the aeroplane’s air intake system.

J1093 Air intake system icing protection

J1103 Air intake system ducts

J1106 Bleed air duct systems

EXHAUST SYSTEM

J1121 General MC0

This modification does not affect the aeroplane’s exhaust system.

J1123 Exhaust piping

APU CONTROLS AND ACCESSORIES

J1141 APU controls

MC0 This modification does not affect the aeroplane’s APU controls, accessories or ignition systems.

J1163 APU accessories

J1165 APU ignition systems

APU FIRE PROTECTION

J1181 Designated fire zone

MC0 This modification has no effect on the aeroplane’s APU fire protection systems.

J1183 Lines, fittings and components

J1185 Flammable fluids

J1187 Drainage and ventilation of fire zones

J1189 Shut-off means

J1191 Firewalls

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J1193 APU compartment

J1195 Fire extinguisher systems

J1197 Fire extinguishing agents

J1199 Extinguishing agent containers

J1201 Fire extinguishing system materials

J1203 Fire-detector system

J1207 Compliance

GENERAL

J1305 APU instruments MC0

This modification does not affect the aeroplane’s APU instruments.

J1337 APU instruments

OPERATING LIMITATIONS

J1501 General

MC0 This modification does not affect the aeroplane’s APU operating limitations.

J1521 APU limitations

J1527 Ambient air temperature and operating altitude

MARKINGS AND PLACARDS

J1549 APU instruments MC0 This modification does not affect the aeroplane’s APU instruments.

J1551 Oil quantity indicator MC0 This modification does not affect the aeroplane’s APU oil quantity indicator.

J1557 Miscellaneous markings and placards

MC0 This modification does not affect the aeroplane’s APU miscellaneous markings and placards.

AEROPLANE FLIGHT MANUAL

J1583 Operating limitations MC0 This modification does not affect the aeroplane’s APU operating limitations.

7.1.4 All other CS25 Airworthiness Requirements are deemed not affected by this modification action.

7.2 Additional Advisory Data

7.2.1 Compliance with JAA TGL 13 has been shown as listed in paragraph 8.11.1 of the Compliance Plan Matrix (CPM) CP/026/9162.

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7.2.2 Compliance with JAA NPA 20-12a (which is now superseded by EASA AMC 20-13) has been shown, as listed in paragraph 8.11.2 of the Compliance Plan Matrix (CPM) CP/026/9162. In accordance with EASA’s Letter to Industry reference Mode-S ELS and EHS Certification Requirements, issue 2, dated 02 March 2007, no further compliance demonstration is required with EASA AMC 20-13, if compliance with JAA NPA 20-12a has already been demonstrated.

7.3 Environmental Requirements

7.3.1 The units installed by this modification have no effect on noise or environmental pollution.

7.4 Operational Approvals

7.4.1 EU OPS 1 Transponder System 1.845, 1.860, 1.865 and 1.866.

7.5 Other Airworthiness Approvals

7.5.1 None applicable.

7.6 Equipment Approval

7.6.1 The Rockwell Collins model TPR-901 transponder holds UK CAA approval number: VC01175.

7.6.2 The Honeywell model TRA-67A transponder holds UK CAA approval number: VC 01204.

7.6.3 An appropriate assessment has been carried out to determine that the equipment is safe and fit for purpose and shows compliance with CS 25.1301 and 1309 as a minimum. Para 7.1.3 refers.

7.7 Additional Requirements

7.7.1 None applicable.

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8 Checks

8.1 Ground Checks


8.2 Flight Checks


9 Weight and Balance

9.1 Equipment Removed

9.1.1 Aircraft: MSN 24449; MSN 24027; MSN 23635 and MSN 24025

Description Weight (lbs)

Station (in)

Moment (lbs in)

Remarks

Rockwell Collins Transponders TPR-720

(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2

Gables Control Panel

(Pt No: G6990-30) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2

9.1.2 Aircraft: MSN 27924


Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-0336-001) 24.0 lbs 352.3 8455.2


(Pt No: G6990-51) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2


Description Weight

(lbs) Station

(in) Moment (lbs in)

Remarks

Bendix Transponders

(Pt No: 066-1123-000 24.0 lbs 352.3 8455.2

Control Panel

(Pt No: 204-1600-6503) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2

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Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-0336-001) 12.0 lbs 352.3 4227.6 No. 1 Transponder



Rockwell Collins Control Panel

(Pt No: 622-8594-121) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2



Station (in)

Moment (lbs in)

Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2


(Pt No: 622-8974-004) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2


Description Weight

(lbs) Station


Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2


(Pt No: 622-8974-008) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2

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Station (in)

Moment (lbs in)

Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2


(Pt No: 622-8974-304) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2


Description Weight

(lbs) Station


Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2


(Pt No: G6992-19) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2



Station (in)

Moment (lbs in)

Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2

Honeywell Control Panel CTA-81A

(Pt No: 071-01477-0001) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2



Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-1338-003) 27.6 lbs 352.3 9723.48


(Pt No: G6992-18) 2.0 lbs 210.0 420.0

Totals 29.6 lbs - 10143.48

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Station (in)

Moment (lbs in)

Remarks

Rockwell Collins Transponder TPR-720 (Pt No: 622-7878-200)

12.0 lbs 352.3 4227.6 No. 1 Transponder

Rockwell Collins Transponder 621A-6A


Rockwell Collins Control Panel TTC-920A

(Pt No: 622-9288-003) 2.0 lbs 210.0 420.0

Totals 26.9 lbs - 9192.27



Station (in)

Moment (lbs in)

Remarks


(Pt No: 622-7878-301) 24.0 lbs 352.3 8455.2


(Pt No: G6992-26) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2

9.1.13 Aircraft MSN 24059


Station (in)

Moment (lbs in)

Remarks

L3 model XS-910 Transponders

(Pt No: 4061400-905) 24.0 lbs 352.3 8455.2 estimated


(Pt No: 622-8974-016) 2.0 lbs 210.0 420.0 estimated

Totals 26.0 lbs - 8875.2

9.1.14 Aircraft MSN 25429


Station (in)

Moment (lbs in)

Remarks

Honeywell model TRA-67A Transponders

(Pt No: 066-01127-1301) 27.0 lbs 352.3 9512.1

Honeywell Control Panel

(Pt No: 071-01503-2601) 1.8 lbs 210.0 378.0

Totals 28.8 lbs - 9890.1

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9.1.15 Aircraft MSN 24440, 24446, 26961 & 24433


Station (in)

Moment (lbs in)

Remarks


(Pt No: 622-7878-201) 24.0 lbs 352.3 8455.2


(Pt No: G6990-51) 2.0 lbs 210.0 420.0

Totals 26.0 lbs - 8875.2

9.2 Equipment Added

9.2.1 Aircraft: MSN 24825; MSN 24449; MSN 24027; MSN 23635; MSN 24025; MSN 24026; MSN 24299 and MSN 24662

Description Weight

(lbs) Station


Remarks


(Pt No: 822-1338-003) 27.6 lbs 352.3 9723.48


(Pt No: G7490-30) 2.0 lbs 210.0 420.0

Totals 29.6 lbs - 10143.48

9.2.2 Aircraft: MSN 27267; MSN 24785; MSN 23653, MSN 27924, MSN 23636 and MSN 24059


Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-1338-003) 27.6 lbs 352.3 9723.48


(Pt No: G7490-40) 2.0 lbs 210.0 420.0

Totals 29.6 lbs - 10143.48



Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-1338-003) 27.6 lbs 352.3 9723.48


(Pt No: G7492-05) 2.0 lbs 210.0 420.0

Totals 29.6 lbs - 10143.48

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Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-1338-003) 27.6 lbs 352.3 9723.48


(Pt No: G7490-26 or 47) 2.0 lbs 210.0 420.0

Totals 29.6 lbs - 10143.48



Station (in)

Moment (lbs in)

Remarks

Honeywell model TRA-67A Transponders

(Pt No: 066-01127-1602) 27.0 lbs 352.3 9512.1


(Pt No: G7490-40) 2.0 lbs 210.0 420.0

Totals 29.0 lbs - 9932.1

9.2.6 Aircraft: MSN 24440, 24446, 26961 & 24433


Station (in)

Moment (lbs in)

Remarks


(Pt No: 822-1338-021) 27.6 lbs 352.3 9723.48


(Pt No: G7490-01) 2.0 lbs 210.0 420.0

Alt P/Ns G7490-30 or G7490-40

Totals 29.6 lbs - 10143.48

9.3 Total Weight & Balance Change:

9.3.1 Aircraft: MSN 24825; MSN 24449; MSN 24027; MSN 27924; MSN 23635; MSN 24025; MSN 24026; MSN 24299, MSN 24699; MSN 24662; MSN 23811, MSN 27267, MSN 24785, MSN 24059, MSN 24440, MSN 24446, MSN 26961 and MSN 24433.

Weight (lbs)

Station (in)

Moment (lbs in)

+3.6 lbs 352.3 1268.28

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Weight (lbs)

Station (in)

Moment (lbs in)

0 lbs - 0


Weight (lbs)

Station (in)

Moment (lbs in)

+2.7 lbs 352.3 951.21


Weight (lbs)

Station (in)

Moment (lbs in)

+0.2 lbs 210 42.0

9.4 It is the responsibility of the operator to calculate the influence of this modification on the Aircraft Weight and Balance Schedule and to ensure that the Aircraft Weight and Balance Schedule is updated to include the changes introduced by this modification.

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MODIFICATION No.


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10 Electrical Load Analysis

10.1 Equipment Removed (All Aircraft)

Description Bus

(V AC) Load

(Amps) Remarks

Transponder 1 115 V AC Standby Bus 0.320 Amps

Transponder 2 115 V AC Elex Power Bus 2 0.320 Amps

Control Panel 115 V AC Standby Bus 0.022 Amps

Control Panel 115 V AC Elex Power Bus 2 0.022 Amps

Totals 115 V AC Standby Bus 0.342 Amps

115 V AC Elex Power Bus 2 0.342 Amps

10.2 Equipment Added (All Aircraft)

Description Bus

(V AC) Load

(Amps) Remarks

Transponder 1 115 V AC Standby Bus 0.490 Amps

Transponder 2 115 V AC Elex Power Bus 2 0.490 Amps

Control Panel 115 V AC Standby Bus 0.035 Amps

Control Panel 115 V AC Elex Power Bus 2 0.035 Amps

Totals 115 V AC Standby Bus 0.525 Amps

115 V AC Elex Power Bus 2 0.525 Amps

10.3 Load Change (All Aircraft)

10.3.1 The total load change introduced by this modification is:

Bus (V AC) Load

115 V AC Standby Bus + 0.183 Amps

115 V AC Elex Power Bus 2 + 0.183 Amps

10.4 It is the responsibility of the operator to ensure that the Electrical Load Analysis is updated to include the changes introduced by this modification and that the capacity of the aircraft generating system and standby battery is not exceeded.

11 Associated Reports

11.1 None.

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MODIFICATION No.


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12 Limitations/Concession

12.1 The Limitations Section is approved and variations must also be approved.

12.2 None applicable.

13 Continued Airworthiness

13.1 Introduction

13.1.1 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.

13.2 Overview

13.2.1 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 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.

13.3 Aeroplane Maintenance Manual

13.3.1 Refer to Rockwell Collins TCAS II Installation Manual - Document: 523-0775651; Chapter: 34-40-70; Dated: Apr 27, 2006; Revision: 17.

13.3.2 Refer to Document number: CPN 523-0805869; Dated: July 10, 2004; Revision: 10, Declaration of Design and Performance TPR-901 ATCRBS / Mode ‘S’ Transponder.

13.3.3 Refer to Honeywell Maintenance Manual for TRA-67 Mode S ATC Link Transponder System, 34-54-11, Revision 10; Dated: 12 September 2003.

13.3.4 Refer to Honeywell TRA-67A Declaration of Design and Performance document number 176.

13.3.5 Refer to Gables Engineering Installation Manual for Flight ID/ATC/TCAS Control Panel, Document IST.G7490-( ), Revision 01, 28 June 2004.

13.3.6 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.

13.3.7 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.

13.3.8 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

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

13.3.8.2 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.

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

13.4 Maintenance Instructions

13.4.1 Amend Chapter 34-53-00; Page 522; 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 Honeywell TRA-67A Maintenance 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 1; page 1 onwards Figs 1 - 33; page 1 onwards

Para 1, page 1; Para 2A, pg 5; Para 3A, fig 13, page 23. Para 4, pg30; Para 5A, pg 30.Para 6, pg 42.

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 1; page 101 onwards Fig 101; page 103 onwards

Para 1, pg 101; Para 2 pgs 102 – 106.

N/A

ATC System –System Test

Para 2.D; page 506 onwards

Para 6B, pg 236 onwards.

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

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.

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

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’.

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13.5 Scheduled Maintenance

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.

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

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

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

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

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

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: 512 et seq; Task Nos: 34-53-02-735-281 34-53-02-735-368 at 2 year intervals.

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.

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.

All Approved Manual amendments/changes made as a result of data contained in this modification must be verified by ATL.

13.6 Airworthiness Limitations

13.6.1 This section sets forth each mandatory replacement time, structural and inspection interval, and related structural inspection procedure approved under CS 25.571.

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

13.6.3 None applied for.

14 Conditions Affecting this Approval

14.1 The compatibility of this modification with other previously approved modifications installed on the particular aircraft must be verified by the installer. Where the potential for interactions between modifications exists, the advice of the Design Organisation, the National Authority or EASA shall be sought.

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15 Authorisation for Release to Service

15.1 In addition to the actions required by the procedures for release to service following maintenance or modification, prior to signing the Certificate of Release to Service, all actions and ground test procedures specified by the modification instructions (see paragraphs 5 & 8) must be completed satisfactorily.

16 Post Modification Action

16.1 Record the accomplishment of this modification in the Aircraft Modification Record.

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