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SERVICE BULLETIN SUMMARY

7 DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : 1 of 4 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft ATA SYSTEM : 57 TITLE : WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING FORWARD LUG OF GEAR RIB 5 MODIFICATION No. : 13329H5686 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During routine maintenance, a crack has been found visually in main landing gear (MLG) rib 5 on two A310 in-service aircraft. The crack was found in the forward lug of the MLG rib 5 aft bearing attachment. The concerned aircraft had accumulated 24,000 flight cycles (FC) and 27,000 FC at the time of finding, refer to Operator Information Telex (OIT) 999.0115/06. In both cases the cracks extended through the entire thickness of the forward lug. Inspection of the MLG rib 5 forward lug on the opposite wings was performed after removal of the bushes on the concerned aircraft. The inspection revealed medium to heavy corrosion in the forward lug holes. A laboratory examination of the two cracked ribs confirmed that the origin of the cracks was due to pitting corrosion. This Service Bulletin introduces new bushes with an increased interference fit in the aft bearing forward lugs. The aft lug of the aft bearing attachment is not affected as the bush is already installed during production with an increased interference fit. After removal of the old bushes, a dye penetrant flaw detection inspection is carried out on the lug bores and faces before installation of the new bushes to make sure that the lugs are damage free. If oversized interference fit bushes have already been installed in one or more of the forward lug positions of the MLG rib 5 aft bearing as per repair R57249121, the intent of this modification can be considered as embodied in these positions. Accomplishment of this Service Bulletin will significantly reduce the likelihood of corrosion and any subsequent cracks in the forward lug of the MLG rib 5 aft bearing attachment. Accomplishment of this Service Bulletin will cancel the inspection requirements of Service Bulletins A310-57A2088 and A310-57-2091. The intent of this Service Bulletin has been validated on A310 aircraft MSN 0539 by the application of repair R57249121.

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SERVICE BULLETIN SUMMARY

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) : 34W 58X 82Z 85Z 99Y A1L ABD AIC ARG BAF BBC BLM CFC CSA DAH DGA DRD F2I FDX GAF IRA IRM IYE JAB JAV KAC KYV MGL MPD MPJ MWA PIA QAF QSC R1T RJA ROT RZO S8G SBI SGX SUD TAP THY TSC UAE UZB WHT This modification is applicable by Service Bulletin only. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 57.51.11.004 OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : OIT SE 999.0115/06 EVALUATION TABLE COMPLIANCE Recommended CANCELS INSPECTION SB Yes POTENTIAL AD No A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No KIT PRICE (USD)B01R02 3960 NORMAL JACKING Yes

MODIFICATION CLASSIFICATION MAJOR None MINOR 13329H5686

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SERVICE BULLETIN SUMMARY

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NATURE OF THE WORK AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No MANPOWER Config. 01

NOTE : If the Repair Instruction R57249121, "Removal of corrosion from the gear rib lugs and the installation of oversized bushes" is necessary, then approximately 52.0 manhours for each wing will be necessary for repair. MATERIAL INFORMATION AIRCRAFT DATA 2 x Kit 572090B01R02 will be necessary for accomplishment of this Service Bulletin on each aircraft. Kit 572090B01R02 comprises 1 bush A5724244120200 and 1 bush A5724244220200. 1 kit will be necessary for the LH Gear Rib 5 and 1 kit will be necessary for the RH Gear Rib 5. A Tool Kit 044A411058D is necessary to accomplish this Service Bulletin. The Tool Kit includes tools for the removal/installation of the bushes and a line honing tool to finish the internal diameter of the bushes after installation. NOTE : Tool Kit 044A411058D also includes the re-boring tool which is required to repair aft bearing attachment lugs in case they are found to be damaged. APPENDICES None TOTAL MANHOURS 41.50 ELAPSED TIME (HOURS) 22.00

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SERVICE BULLETIN SUMMARY

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4

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SERVICE BULLETIN

7 DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : 1 of 21 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 ATA SYSTEM : 57 TITLE : WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING FORWARD LUG OF GEAR RIB 5 MODIFICATION No. : 13329H5686 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS 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 of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS' prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models 310-203 310-203C 310-204 310-222 310-304 310-308 310-322 310-324 310-325 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0349 0353 0355-0357 0359 0360 0362 0364 0367 0369 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427-0431 0434 0436 0437 0439 0441 0444-0449 0451-0458 0467 0468 0472 0473 0475 0476 0478 0480-0492 0494-0503 0519 0520 0522-0524 0526 0527 0531 0534 0535 0537-0539 0541 0542 0544 0545 0547-0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585-0595 0597-0600 0620 0622 0624 0634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660 0661 0663 0665 0667 0669 0671 0672 0674 0676 0678 0680 0682

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 0684 0686 0687 0689 0691 0693 0695 0697 0698 0700 0702 0704 0706 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 34W 0399 58X 0431 82Z 0550 0551 85Z 0524 99Y 0489 A1L 0648 ABD 0624 AIC 0392 0406 0407 0413 0428 0429 0501 0538 0544 0548 0598 0654 0665 0669 0680 0684 0693 0695 0697 ARG 0640 0686 BAF 0367 0372 BBC 0594 0650 0698 0700 BLM 0488 CFC 0425 0441 0444 0446 0482 CSA 0564 0567 0672 0674 DAH 0291 0293 DGA 0418 0421 0422 DRD 0527 F2I 0309 0320 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539 0542 0549 0552 0589 0593 0634 0638 GAF 0434 0484 0498 0499 0503 0522 0523 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0537 0586 IYE 0535 0568 0702 0704 JAB 0419

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved This modification is applicable by Service Bulletin only. (c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0353 0355-0357 0359-0360 0362 0364 0367 0369-0370 0372 0375 0378-0379 0386 0389-0390 0392 0394 0397 0399-0400 0406-0407 0410 0413 0416 0418-0419 0421-0422 0425 0427-0431 0434 0436-0437 0439 0441 0444-0449 0451-0458 0467-0468 0472-0473 0475-0476 0478 0480-0492 0494-0503 0519-0520 0522-0524 0526-0527 0531 0534-0535 0537-0539 0541-0542 0544-0545 0547-0552 0562 JAV 0357 0481 KAC 0647 0649 0663 KYV 0172 MGL 0526 MPD 0451 0455 0642 MPJ 0410 MWA 0652 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0473 QSC 0620 R1T 0591 RJA 0416 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0651 0661 S8G 0300 SBI 0427 0430 0453 0468 0475 0486 0487 0520 SGX 0519 0562 SUD 0437 TAP 0483 0494 0495 0541 0565 0573 THY 0386 0476 0478 0480 0496 0497 0502 TSC 0447 0472 0485 0545 0547 0588 0595 0597 0599 0600 0658 UAE 0592 0622 0646 0667 UZB 0574 0576 0706 WHT 0448 OPERATOR MSN

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 0564-0565 0567-0568 0571 0573-0574 0576 0585-0595 0597-0600 0620 0622 0624 0634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-0661 0663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 0684 0686-0687 0689 0691 0693 0695 0697-0698 0700 0702 0704 0706

NOTE : Config. 01 is valid for all aircraft that have not had oversized interference fit bushes installed at aft bearing forward lug position by Repair Instruction R57249121. If oversized interference fit bushes have been installed at aft bearing forward lug position by Repair Instruction R57249121 on one wing only, then only 1 Kit 572090B01R02 will be necessary. (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History During routine maintenance, a crack has been found visually in MLG rib 5 on two A310 in-service aircraft. The crack was found in the forward lug of the MLG rib 5 aft bearing attachment lug. The concerned aircraft had accumulated 24,000 FC and 27,000 FC at the time of finding, refer to OIT 999.0115/06. In both cases the cracks extended through the entire thickness of the forward lug. Inspection of the MLG rib 5 forward lug on the opposite wings was performed after removal of the bushes on the concerned aircraft. The inspection revealed medium to heavy corrosion in the forward lug holes. A laboratory examination of the two cracked ribs confirmed that the origin of the cracks was due to pitting corrosion. The intent of this Service Bulletin has been validated on A310 aircraft MSN 0539 by the application of repair R57249121. (2) Objective/Action This Service Bulletin introduces new bushes with an increased interference fit in the aft bearing forward lugs. The aft lug of the aft bearing attachment is not affected as the bush is already installed during production with an increased interference fit. KIT No. QTY PER A/C CONFIGURATION 572090B01R02 2 01

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved After removal of the old bushes, a dye penetrant flaw detection inspection is carried out on the lug bores and faces before installation of the new bushes to make sure that the lugs are damage free. If oversized interference fit bushes have already been installed in one or more of the forward lug positions of the MLG rib 5 aft bearing as per repair R57249121, the intent of this modification can be considered as embodied in these positions. (3) Advantages Accomplishment of this Service Bulletin will significantly reduce the likelihood of corrosion and any subsequent cracks in the forward lug of the MLG rib 5 aft bearing attachment. Accomplishment of this Service Bulletin will cancel the inspection requirements of Service Bulletins A310-57A2088 and A310-57-2091. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Lift the aircraft on jacks. (b) Remove the LH and RH MLG legs. (c) Remove the LH and RH MLG secondary doors. (d) Remove the bushes from the forward lugs of the gear support rib 5 aft bearing attachment. (e) Inspect the lug faces and bores for damage/corrosion. NOTE : If damage/corrosion is found on a lug it will be necessary to report to AIRBUS for advice and to refer to repair drawing R57249121. (f) Install the new bushes in the forward lugs of the gear support rib 5 aft bearing attachment. NOTE : It is necessary to freeze fit the new bushes. (g) Line-hone the new bushes to the finished internal diameter. (h) Install the LH and RH MLG secondary doors. (i) Install the LH and RH MLG legs.

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (j) Do the applicable tests. (k) Lower the aircraft off jacks. (l) Close up and complete the documentation. E. COMPLIANCE (1) Classification Recommended (2) Accomplishment Timescale Accomplishment is recommended at the next MLG overhaul or at the earliest opportunity where manpower and facilities are available. F. APPROVAL Approved under the EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 Remove LH MLG 5.00 Remove RH MLG 5.00 Remove the LH MLG secondary door 1.00 Remove the RH MLG secondary door 1.00 Remove LH Gear Rib 5 bushes 1.50 Remove RH Gear Rib 5 bushes 1.50 Inspect bores/faces of the LH lugs 1.00

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : If the Repair Instruction R57249121, "Removal of corrosion from the gear rib lugs and the installation of oversized bushes" is necessary, then approximately 52.0 manhours for each wing will be necessary for repair. H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not applicable Inspect bores/faces of the RH lugs 1.00 Install new LH Gear Rib 5 bushes 3.00 Install new RH Gear Rib 5 bushes 3.00 Install the LH MLG secondary door 1.00 Install the RH MLG secondary door 1.00 Install LH MLG 5.00 Install RH MLG 5.00 Test 6.00 Close up 0.50 TOTAL MANHOURS 41.50 ELAPSED TIME (HOURS) 22.00

Aircraft Maintenance Manual (AMM) : 07-11-00 32-11-11 32-12-13 Elec. Std. Practices Manual (ESPM) : 20-55-00 Non destructive Testing Manual (NTM) : 51-90-00 Process and Mat. Spec. Manual (PMSM) : 01-06-12 Structural Repair Manual (SRM) : 51-21-10 51-76-10

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DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Page Intentionally Left Blank

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : Airbus Spares Support and Services Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability Kit 572090B01R02 Cost : 3960 US Dollars Availability : 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION Airbus will provide a 20 percent reduction to the applicable sales prices given in paragraph 2A(2) for orders placed before 31 December 2012. C. LIST OF COMPONENTS Kit 572090B01R02

NOTE (*) Discard ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 A5724244220200 1 Bush (1) A5724244220000 * 2 A5724244120200 1 Bush (2) A5724244120000 *

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

NOTE (01) Mat. No. 07-018 is an alternative lacquer to Mat. No. 16-021B when used to protect written part numbers. NOTE (02) The Marker Pen 8404 can be procured from : Edding (UK) Ltd. Merlin Centre Acrewood Way St. Albans Herts England (2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

NOTE : * Re-identify by marking the SB number "SB A310-57-2090" adjacent to the old part number. DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP Honing Fluid 06-010 As required Varnish 07-018 As required 01 Sealant, Anaerobic 08-003 As required Fuel Tank Sealant Polysulfide 09-002 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required 01 Marker Pen 8404 None 1 02

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT * Gear Rib A57242444000 02 * Gear Rib A57242444001 02 * Gear Rib A57242444004 02 * Gear Rib A57242444005 02 * Gear Rib A57242444008 02 * Gear Rib A57242444009 02

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved F. TOOLING — PRICE AND AVAILABILITY

NOTE (01) The tool kit contains the following items for the removal of the bushes, Items (1) and (2) (Refer to Figure 1 , Sheet 2 ): — Qty 1 044A411058D-34 Split Location Ring — Qty 1 044A411058D-35 Bolt — Qty 1 044A411058D-43 Enerpac Cylinder — Qty 1 044A411058D-44 Enerpac Hand Pump — Qty 1 044A411058D-45 Enerpac Connector Hose — Qty 1 044A411058D-46 Spherical Washer — Qty 1 044A411058D-47 Location Block — Qty 4 044A411058D-48 Bolt (for Item 47) — Qty 1 044A411058D-49 Thrust Washer — Qty 2 044A411058D-50 Nut — Qty 1 044A411058D-51 Reaction Block (Aft Bush Item (1)) — Qty 1 044A411058D-86 Captive Washer — Qty 1 044A411058D-87 Shoulder Screw (for item 86) — Qty 1 044A411058D-89 Reaction Block (Fwd Bush Item (2)) NOTE (02) The tool kit contains the following items for the installation of the bushes, Items 1 and 2 (Refer to Figure 1 , Sheet 3 ): — Qty 1 044A411058D-35 Bolt — Qty 1 044A411058D-39 Installation Block — Qty 1 044A411058D-43 Enerpac Cylinder — Qty 1 044A411058D-44 Enerpac Hand Pump — Qty 1 044A411058D-45 Enerpac Connector Hose — Qty 1 044A411058D-46 Spherical Washer — Qty 2 044A411058D-50 Nut — Qty 1 044A411058D-51 Reaction Block (Fwd Bush Item 2) ITEM PART NUMBER QTY DESCRIPTION 044A411058D 1 Kit MLG Boring Fixture

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — Qty 1 044A411058D-86 Captive Washer — Qty 1 044A411058D-87 Shoulder Screw (for Item 86) — Qty 1 044A411058D-89 Reaction Block (Aft Bush Item 1) NOTE (03) The tool kit will also contain an In-Line Honing Tool PN MT79005/197 to line hone the bushes to the finished internal diameter after installation (Refer to Figure 2 ). It will also contain an Alignment Tool (truing sleeve) PN MT19048 to set up the In-Line Honing Tool. G. SPECIAL TOOLS None

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. (1) Preparation (a) Config. 01 1 Lift the aircraft on jacks (Refer to AMM 07-11-00 Page block 1). 2 Remove the LH and RH MLG legs (Refer to AMM 32-11-11 Page block 401). 3 Remove the LH and RH MLG secondary doors (Refer to AMM 32-12-13 Page block 401). 4 Put access platforms in position in Zones 730/740. (2) Standard Practices (a) Part marking with indelible ink (Refer to PMS 01-06-12 and Para. 2.D.). (b) Application of protective treatments (Refer to SRM 51-21-10 Page block 1). (c) Application of a bead sealant as a fillet (Refer to SRM 51-76-10 Page block 201). B. MODIFICATION NOTE : The worksteps that follow are applicable to the LH and RH wings. (1) Config. 01

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (a) Removal of Bushes Refer to Figure 1 , Sheet 1 and 2 1 Use the removal/installation tool from the tool kit 044A411058D to remove these items :

(b) Inspection of Lug Faces and Bores Refer to Figure 1 , Sheet 1 1 Clean the bores of the lugs with a plastic spatula and Solvent General Purpose (Mat No. 11-026) . 2 Visually inspect the bore and the spotfaces of the lug to make sure there is no corrosion and/or damage. NOTE : If corrosion and/or damage is found visually it is not necessary to do the next workstep (b)3. 3 Do a dye penetrant flaw detection test of the bore and the spotfaces of the lug to make sure there is no corrosion and/or damage (Refer to NTM 51-90-00 Page block 901). 4 Do a check to make sure that the diameter of the bore of the lug (dimension F) is within the tolerance of 4.7791 to 4.7805 ins. (121.389 to 121.425 mm). 5 If no damage and/or corrosion is found and dimension F is within the tolerance do workstep 3.B.(1)(c). 6 If there is damage and/or corrosion found, or if dimension F is more than the given tolerance, report the findings to AIRBUS and wait for advice for repair R57249121 and re-boring tool 044A411058D. (c) Installation of Bushes Refer to Figure 1 , Sheet 1 and 3 and Figure 2 , Sheet 1 and 2 1 Apply Chemical Conversion Coating Yellow Aluminum (Mat No. 13-002) to the bore and the spotfaces of the lug. 2 Apply Sealant, Anaerobic (Mat No. 08-003) to the bores of the lug and the mating surface for the seat of the bush flange. 1 Bush A5724244220000 Item (1) Discard 1 Bush A5724244120000 Item (2) Discard

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved WARNING : LIQUID NITROGEN IS DANGEROUS. OBEY THE MANUFACTURERS INSTRUCTIONS AND WEAR THE CORRECT PROTECTIVE CLOTHING WHEN YOU USE LIQUID NITROGEN. CAUTION : DO NOT PUT MORE THAN ONE BUSH AT A TIME INTO THE LIQUID NITROGEN, USE CLEAN TONGS TO REMOVE THE BUSH FROM THE LIQUID NITROGEN AND TO INSTALL IT IN THE BORE OF THE LUG. 3 Install these items from Kit 572090B01R02 as follows:

— freeze each bush in sequence in liquid nitrogen for not less than three minutes, — install each bush in sequence in the applicable end of the bore of forward lug of the aft gear rib bearing, — allow the bushes to return to ambient temperature, — before the sealant cures, use the installation tool (refer to Figure 1 Sheet 3) to make sure that the bush is fully installed. 4 Make sure that the dimension G is within the tolerance of 2.785 to 2.797 ins. (70.74 to 71.04 mm). 5 Make sure that the clearance dimension between the bushes, Item 1 and Item 2 is free of sealant. 6 Assemble the in-line honing tool as shown, refer to Figure 2 , Sheet 1 . 7 Use the alignment tool (truing sleeve) to set up the in-line honing tool as shown, refer to Figure 2 , Sheet 2 . CAUTION : USE ONLY "DELAPENA" HONING FLUID (MAT NO. 06-010) . 8 Use the in-line honing tool to finish the internal diameter (dimension E) of the bushes, Item 1 and Item 2, within the tolerance of 4.5275 to 4.5289 ins. (114.999 to 115.034 mm) and to a surface finish of 32 microns. 9 Use Solvent General Purpose (Mat No. 11-026) and a cloth to clean the area. 10 Apply Adhesion Promoter For Polysulfide Sealant (Mat No. 09-028) around the flanges of the bushes, Items 1 and 2. 11 Apply a continous bead of sealant around the edges of the bushes, Item 1 and Item 2 to form a fillet seal, use Fuel Tank Sealant Polysulfide (Mat No. 09-002) . 1 Bush A5724244220200 Item 1 1 Bush A5724244120200 Item 2

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 12 Use Solvent General Purpose (Mat No. 11-026) and a cloth to remove any unwanted sealant. 13 Apply Polyurethane Gloss Finish (Clear Basecoat) (Mat No. 16-021B) to the fillet seals to protect the sealant from hydraulic fluid. (d) Re-identify the gear ribs 5 by marking this SB No. adjacent to the part number, refer to Para. 2.E. and Para. 3.A.(2)(a). Apply Polyurethane Gloss Finish (Clear Basecoat) (Mat No. 16-021B) to protect the written SB No. from hydraulic fluid. C. TEST (1) Config. 01 (a) The test procedures necessary for the LH and RH MLG Leg and MLG secondary door are included in the reference for installation (Refer to Para. D.(1)(a) and (b)). D. CLOSE UP (1) Config. 01 (a) Install the LH and RH MLG secondary doors (Refer to AMM 32-12-13 Page block 401). (b) Install the LH and RH MLG legs (Refer to AMM 32-11-11 Page block 401). (c) Make sure that the work areas are clean and clear of tools and other items of equipment. (d) Remove the access platforms from Zones 730/740. (e) Lower the aircraft off jacks (Refer to AMM 07-11-00 Page block 1). E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 1 Config. 01: Replacement of Gear Support Rib Bushes

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 2 Config. 01: Replacement of Gear Support Rib Bushes

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 3 Config. 01: Replacement of Gear Support Rib Bushes

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 2 Sheet 1 Config. 01: Line Honing of Bushes

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SERVICE BULLETIN

DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 2 Sheet 2 Config. 01: Line Honing of Bushes

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SERVICE BULLETIN REPORTING SHEET

7 DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved TITLE : WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING FORWARD LUG OF GEAR RIB 5 MODIFICATION No. : 13329H5686

Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:..........................

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........................................ B - SB HAS BEEN embodied on aircraft:.....................

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........................................ Operator comments:..............................

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....................................... From Airline:................................. Name/Title:.................................. Signature:.............. Date:............. If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: Either: Modification Operational Impact (MOI), if available. . YES/NO Or : Intermediate revision.
................ YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

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SERVICE BULLETIN QUALITY PERCEPTION FORM

7 DATE : May 22/07 SERVICE BULLETIN No. : A310—57—2090 REVISION No. : 00 — Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments :

Operator : Date: Name/Title : Please return this form to : AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.