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REVISION No. : 7 -2046 07 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR ATTACHMENT OF MLG FORWARD PICK-UP FITTING. MODIFICATION No. : NONE ATA SYSTEM : 57 This page transmits Revision No. 07 of Service Bulletin No. A310-57-2046. ADDITIONAL WORK No additional inspection/work is necessary to do this revision. REASON Investigations have established that for aircraft with Modification No. 07601H1085 embodied (Provide Cold Expansion of Attachment Holes) the inspection requirement of this Service Bulletin is not required. Therefore the inspection requirement of this Service Bulletin for these aircraft is cancelled (aircraft MSN 547 and subsequent). This revision has been issued to remove post Mod. No. 07601H1085 aircraft from the effectivity of this Service Bulletin. A paragraph has also has been added to state that if Modification No. 11578H5436 (Service Bulletin A310-57-2074) is embodied after 3,800 FC for A310-200 aircraft and after 4,600 FC for A310-300 aircraft then the inspection requirements of this Service Bulletin are cancelled. CHANGES Summary: - aircraft EFFECTIVITY updated. Service Bulletin: Planning information - Para. 1. A. (2) - aircraft EFFECTIVITY updated and NOTE added. - Para. 1. B. (5) (c) - statement re-worded. - Para. 1. B. (5) (h) - new statement added. Layout changes due to the computerization of this Service Bulletin are not identified. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete Service Bulletin. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS

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REVISION No. : -2046 0707 SERVICE BULLETIN REVISION TRANSMITTAL SHEET This is only applicable to Revision No. 02 and subsequent. If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact Airbus Industrie. - Revision No. 02 was issued to include new inspection requirements and to incorporate Change Notice No. 1A. - Revision No. 03 was issued to ammend the effectivity and the jacking points. - Revision No. 04 was issued to change the inspection method from HFEC to Ultrasonic. - Revision No. 05 was issued to simplify the instructions with regard to the HFEC inspections and the embodiment of Modification No. 07925H1113. - Revision No. 06 was issued to state that Modification No. 11578H5436 (SB A310-57-2074) only takes the aircraft to Design Life Goal (DLG) if it is embodied after 3800 flight cycles (FC) for A310-200 aircraft, or after 4600 FC for A310-300 aircraft. The content of Change Notice 4A, which corrects the AMM reference and the access doors for gaining access to the inboard fuel tanks was also included. REVISION SEQUENCE ORIGINAL : MAR 05/90 REVISION No. : 01 - MAY 24/93 REVISION No. : 02 - MAR 22/95 REVISION No. : 03 - OCT 17/95 REVISION No. : 04 - OCT 16/96 REVISION No. : 05 - MAR 18/98 REVISION No. : 06 - JUN 19/98 REVISION No. : 07 - Apr 02/99

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REVISION No. : 7 -2046 0707 SERVICE BULLETIN SUMMARY AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 FThis summary is for information only and is not approved for modification of the aircraft TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR ATTACHMENT OF MLG FORWARD PICK-UP FITTING. MODIFICATION No. : NONE ATA SYSTEM : 57 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During full-scale fatigue testing, at approximately 90000 simulated flights, cracks were discovered in the rear spar starting from certain bolt holes at the attachment of the MLG forward pick-up fitting. There is a possibility of similar cracks appearing on aircraft in service which, if allowed to continue beyond repairable limits, may require extensive and costly repairs. The initial issue and Revisions 1 thru 03 of this Service Bulletin required mandatory High Frequency Eddy Current (HFEC) inspections of certain bolt holes where the MLG forward pick-up fittings are attached to the rear spar. This required the fasteners to be removed. Revision 04 of this Service Bulletin replaced the HFEC inspection with an ultrasonic (US) inspection which does not require the fasteners to be removed. Mandatory US inspections are required at certain bolt holes where the MLG forward pick-up fittings are attached to the rear spar. The inspections are to be done in accordance with the time scales that follow : - Pre Mod. 07925H1113, A310-200 Aircraft have an inspection threshold of 12000 FC and an inspection interval of 3500 FC. - Pre Mod. 07925H1113, A310-300 Aircraft have an inspection threshold of 9000 FC and an inspection interval of 3100 FC. EFFECTIVITY This Service Bulletin is applicable to these customers : AFR, AIB, AIC, ANG, AUA, BAF, CCA, CFC, CYP, DAH, DGA, DLH, DYA, FDX, GAF, HLF, KQA, NGA, RJA, SAB, SIA, SWR, TAP, THA, THY, UAE, WDA, XB, XC, XF, ZB. NOTE: This Service Bulletin is not applicable to post Mod. No. 07601H1085 aircraft (aircraft MSN 547 and subsequent). SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY None

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REVISION No. : -2046 0707 SERVICE BULLETIN SUMMARY REFERENCES/REPERCUSSIONS None TFU :None OEB :None AOT :None SIL : LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No None OTHER : NATURE OF THE WORK AIRCRAFT : Yes. EQUIPMENT : No. HARD : No. SOFT : No. OBRM : No. COMPLIANCE Mandatory. MANPOWER Manhours TOTAL MANHOURS 26.0 ELAPSED TIME (HOURS) 14.0 MATERIAL INFORMATION AIRCRAFT DATA None EQUIPMENT DATA None APPENDICES None

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REVISION No. : 7 -2046 0707 SERVICE BULLETIN
AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR ATTACHMENT OF MLG FORWARD PICK-UP FITTING. MODIFICATION No. : NONE ATA SYSTEM : 57 1. PLANNING INFORMATION A. EFFECTIVITY (1) Aircraft models : A310-203, A310-204, A310-221, A310-222, A310-304, A310-308, A310-322, A310-324, A310-325 (2) Aircraft Customer and Fleet No. MSN Kit No. Qty of kits Config No. 572046 AFR001-005 316,326,335,355,369 051 454 061-062 502,504 AIB001-009 439,442,449,452,453,456, 457,458,467 101-105 267,276,278,318,331 AIC301-308 392,406,407,413,428,429, 538,544 ANG001-002 378,549 AUA401-402 489,492 BAF001-002 367,372 CCA031-032 435,440 CFC001-005 446,482,425,444,441 CYP001-003 300,309,352 051 486 DAH001-004 291,293,295,306 DGA001-002 421,422 DLH553-559 485,488,522,524,526,527 557-559 524,526,527 DYA001 473 FDX401-405 191,201,230,233,237

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Customer and Fleet No. MSN Kit No. Qty of kits Config No. 572046 407-430 254,257,273,356,359,360, 397,400,349,288,333,343, 345,339,342,346,281,241, 264,245,362,248,364,394 442-443 353,283 445-450 297,224,251,260,217,162 GAF001-006 498,499,503,434,484,523 HLF401-404 427,430,468,487 451-452 520,528 KQA001-003 416,426,519 NGA001-004 270,285,329,340 RJA003-006 445,490,491,531 SAB401-402 303,313 451 437 SIA101-104 347,350,357,363 121-126 433,443,493,500,501,534 SWR226-229 399,404,409,410 251 412 TAP501-504 483,494,495,541 THA001-002 415,424 THY001-008 338,375,379,386,370,389, 390,172 021-026 476,478,480,496,497,537 UAE001-003 432,436,545 WDA801 418 807-811 447,448,472,475,481 XB001 431 XC001-002 311,320 021 419 XF601 535 ZB052-053 451,455 101-102 539,542 NOTE: This Service Bulletin is not applicable to post Mod. No. 07601H1085 aircraft (aircraft MSN 547 and subsequent).

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This document contains Airbus Industrie PROPRIETARY INFORMATION and shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes for performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie’s prior written consent. (3) Spares None B. REASON (1) History During full-scale fatigue testing, at approximately 90000 simulated flights, cracks were discovered in the rear spar starting from certain bolt holes at the attachment of the MLG forward pick-up fitting. There is a possibility of similar cracks appearing on aircraft in service. Modification No. 07925H1113 (Service Bulletin A310-57-2049) was introduced to cold expand the bolt holes covered by this inspection and to install oversize studs. However, this did not take the aircraft to its Design Life Goal (DLG). Modification 07925H1113 has been superseded by Modification No. 11578H5436 (SB A310-57-2074). Embodiment of Modification No. 11578H5436 (SB A310-57-2074) after 3800 flight cycles (FC) for A310-200 aircraft, or after 4600 FC for A310-300 aircraft will take the aircraft to the DLG and cancel the inspection requirements of this Service Bulletin. Modification No. 11578H5436 (SB A310-57-2074) is recommended for embodiment at 12000 flight cycles (FC) on A310-200 aircraft and at 9000 FC on A310-300 aircraft. Production Modification 07601H1085 introduced cold working of all attachment holes through the rear spar for the undercarriage support rib and forward MLG pick-up fitting on A310-300 aircraft. The cold working gave an improvement over the original basic fatigue life but did not take the aircraft to DLG. The modification is embodied on MSN 547 and subsequent. The inspection requirements for the post Mod. 07601H1085 aircraft are detailed in the Maintenance Review Board Document, SSI 57.21.16. Revision 4 of this Service Bulletin was issued to change the inspection method from HFEC to US. The US inspection does not require bolt removal or jacking of the aircraft. However, the inspection intervals are reduced.

DATE : MAR 05/90 SERVICE BULLETIN No. : -57 - Apr 02/99 PAGE : 3 Printed in FranceAircraft Inspection Threshold (FC) Inspection Interval (FC) A310-200 Pre Mod. 07925H1113 12000 3500 A310-300 Pre Mod. 07925H1113 9000 3100

Aircraft Inspection Threshold (FC) Inspection Interval (FC) A310-200 Post Mod. 07925H1113 18000 11600 A310-300 Post Mod. 07925H1113 15000 6300

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(2) Objective/Action Mandatory Ultrasonic (US) inspections are required at certain bolt holes where the MLG forward pick-up fittings are attached to the rear spar. (3) Advantages Early detection of cracks is beneficial as significant cracking in this area would require very extensive and costly repairs. (4) Operational/Maintenance Consequences None (5) Accomplishment Timescale (a) The accomplishment of this Service Bulletin is rendered Mandatory by Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132B. (b) Mandatory Ultrasonic (US) inspections are required at certain bolt holes where the MLG forward pick-up fitting is attached to the rear spar not later than the following.

(c) If the spar is reworked, by embodiment of Modification 07925H1113 (SB A310-57-2049), the subsequent mandatory US inspections are required after embodiment of the modification:

(d) Where cracks are found at the first inspection, the repeat inspection interval will be dependent on the extent of the damage and the repairs that have been done. (e) Where HFEC inspections have already been done in accordance with Revision 0 to 03 of this Service Bulletin and: (1) No cracks were found and (2) Modification 07925H1113 (SB A310-57-2049) has not been done. Mandatory US inspections are required as follows :

DATE : MAR 05/90 SERVICE BULLETIN No. : -57 - Apr 02/99 PAGE : 4 Printed in FranceAircraft Model Next Inspection Interval (FC) Subsequent Repeat Inspections (FC) A310-200 5000 * 3500 A310-300 4300 * 3100

Aircraft Model Inspection Threshold (FC) Inspection Interval (FC) A310-200 18000 11600 A310-300 15000 6300

Aircraft Model Inspection Threshold (FC) Inspection Interval (FC) A310-200 12000 11600 A310-300 9500 6300

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* Next inspection interval taken from time of last HFEC inspection. (f) Where an HFEC inspection has already been done in accordance with Revision 0 to 03 of this Service Bulletin and: (1) No cracks were found and (2) Modification 07925H1113 (SB A310-57-2049) has subsequently been embodied at or before 12000 FC for A310-200 aircraft and at or before 9000 FC for A310-300 aircraft. The following mandatory US inspections are required after embodiment of the modification:

(g) Where HFEC inspections have already been done in accordance with Revision 0 to 03 of this Service Bulletin and: (1) No cracks were found and (2) Modification 07925H1113 (SB A310-57-2049) has subsequently been embodied after 12000 FC for A310-200 aircraft and after 9000 FC for A310-300 aircraft. The subsequent mandatory US inspections are required after the embodiment of the modification:

NOTE: Repair Instruction R571-49305, where no holes have been bushed, is equivalent to Service Bulletin A310-57-2049 for the purposes of paragraphs (f) and (g). (h) If Modification No. 11578H5436 (Service Bulletin A310-57-2074) is embodied after 3,800 FC for A310-200 aircraft and after 4,600 FC for A310-300 aircraft then the inspection requirements of this Service Bulletin are cancelled.

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C. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Defuel the aircraft. (2) Get access to the inboard fuel tanks. (3) Identify the selected bolts/studs at the MLG forward pick-up fitting. (4) Do a US inspection of the selected bolt/stud holes of the MLG forward pick-up fitting. (5) Do approved repairs if cracks are found. (6) Close-up. D. APPROVAL This Service Bulletin is approved by the Direction Generale de l’Aviation Civile France (DGAC). E. MANPOWER This Service Bulletin is written for an aircraft in a maintenance condition. The manhours/elapsed time estimates do not include the time to prepare for the inspection, non-productive elapsed time or administration. Manhours Get access 5.0 Inspection 16.0 Close-up 5.0 TOTAL MANHOURS 26.0 ELAPSED TIME (HOURS) 14.0 F. MATERIAL - COST AND AVAILABILITY None G. TOOLING - PRICE AND AVAILABILITY None H. WEIGHT AND BALANCE No change I. REFERENCES Aircraft Maintenance Manual (AMM) : 28-00-00, 28-25-00, 28-11-23 Nondestructive Testing Manual (NTM) : Part 4 57-21-24 Structural Repair Manual (SRM) : 51-10-13, 51-76-20 Service Bulletins (SB) : A310-57-2049, A310-57-2074

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REVISION No. : -2046 0707 SERVICE BULLETIN
Maintenance Review Board Document (MRBD): SSI 57.21.16 Consumable Materials List (CML) : J. PUBLICATIONS AFFECTED None

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2. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : LANDING GEAR - MAKE SURE THAT THE GROUND SAFETIES ARE IN POSITION. FLIGHT CONTROLS - MAKE SURE THAT THE GROUND SAFETIES AND NOTICES ARE IN POSITION. WARNING : OBEY THE SAFETY PRECAUTIONS LISTED IN AMM 28-00-00, PAGE BLOCK 301. WARNING : OBEY ALL THE WARNINGS AND ALL THE CAUTIONS LISTED IN THE REFERENCED PROCEDURES. NOTE: These instructions are applicable to both LH and RH wings unless stated otherwise. (1) Preparation (a) Drain the fuel tanks (Refer to AMM: 28-00-00,, P. Block 301 and AMM: 28-25-00, P. Block 301). (b) Get access to the inboard fuel tanks via the access doors 540/640 CB (Refer to AMM: 28-11-23,, P. Block 401). (c) Remove the sealant from the area to be inspected in the fuel tank (Refer to Refer to Figure 1 ). (2) Standard Practices None B. INSPECTION Refer to Refer to Figure 1 (1) Do a US inspection of the bolt/stud holes (Refer to NTM: Part 4, 57-21-24). (a) Where no cracks are found, refer to paragraph 2.E. and close-up. NOTE : If it is desired and if the aircraft has not been modified in accordance with Service Bulletin A310-57-2049, the selected fastener holes may be cold expanded in accordance with Service Bulletin A310-57-2074. (b) If cracks are found, refer to paragraph 2.C. and do a repair as necessary. (c) Report all crack findings, including no findings, to AI/SE-A (Refer to SRM: 51-10-13,, P. Block 1). C. REPAIR If any cracks are indicated, report the details to AI/SE-A (Refer to SRM: 51-10-13,, P. Block 1) and do an approved repair before the next flight.

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D. TEST None E. CLOSE-UP (1) Apply sealant to the inspection area in the fuel tank (Refer to SRM: 51-76-20). (2) Make sure that the inspection/repair areas are clean and clear of tools and other items of equipment. (3) Close the access doors 540/640 CB (Refer to AMM: 28-11-22,, P. Block 401). F. DOCUMENTATION Write in the applicable aircraft technical records that you have done all the work given in this Service Bulletin.

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Figure 1 Sheet 1

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3. MATERIAL INFORMATION None

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REVISION No. : 7 -2046 0707 SERVICE BULLETIN ACCEPTANCE/REJECTION SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR ATTACHMENT OF MLG FORWARD PICK-UP FITTING. MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW Please fill : ...REJECTED ...WILL BE EMBODIED ...EFFECTIVITY

This SB can only be incorporated in your "customized" documentation within the agreed time schedule in so far as this sheet returned to us on purchase date and signed by a duly authorized and empowered officer or representative.

FROM : AIRLINE :

NAME :

DATE : Please return to : AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : AI/SE-D32 Technical Data and Documentation Services FAX : (+33) 5 61 93 28 06

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