# A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

**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 - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING PLATE**  **MODIFICATION No. :** 12525H5572 This page transmits Revision No. 03 of Service Bulletin No. A310-57-2081 A D D I T I O N A L WO R K No additional work is required by this revision for aircraft modified by any previous issue. R E AS O N This Service Bulletin has been issued at Revision 03 to inform operators that: - the Part Nos. of the Landings supplied by the operator have been amended - the countersink washers, Items 18 and 19, are used to fill the existing countersinks in the aileron hinge ribs. The opportunity has also been taken to update the effectivity. C H A N G E S SUMMARY : - EFFECTIVITY

. Effectivity revised. PLANNING INFORMATION : - EFFECTIVITY

. 1.A. Effectivity revised. NOTE added. MATERIAL INFORMATION : - Price and Availability

. 2.A.(2) Cost updated for Kit B01 and Kit B02. - LIST OF MATERIALS - OPERATOR SUPPLIED DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 2 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

. 2.D.(2) The Part Nos. of the Landings have been amended. ACCOMPLISHMENT INSTRUCTIONS : - GENERAL

. 3.A. CAUTION has been updated. - MODIFICATION

. 3.B.(1)(a)2 The Part Nos. of the Landings have been amended. . 3.B.(1)(b)3 NOTE added. NOTE : Layout changes due to computerization of this revision are not identified. F I L I N G I N ST R U CT I O N S This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. H I STO RY O F P R E V I O U S R E V I S I O N S Revision 01 was issued to change the Kit prices and to add an inspection procedure for cracks in the landing-plate before embodying the modification. Revision 02 was issued to inform operators that: - the reference to, Item 6 NSA5476VHK5-10 has been amended to NSA5478VHK5-10 in the modification worksteps - the manhours have been increased to 28 manhours - the embodiment of the modification is now recommended at 10,200 FC - other minor changes to this Service Bulletin have been added. R E V I S I O N S E Q U E N C E ORIGINAL : Jun 11/02 REVISION No. : 01 - Feb 26/03 REVISION No. : 02 - Oct 18/07 REVISION No. : 03 - Oct 13/10

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 2 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN SUMMARY

**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 - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING**  **PLATE MODIFICATION No. :**  12525H5572 R E AS O N / D E S C R I PT I O N /O P E RA T I O N A L C O N S E Q U E N C E S On the full scale wing fatigue test, skin cracking occurred in the area covered by this modification. The crack was found at 51,500 simulated flights and started from one of the access door landing plate attachment holes. Service Bulletin A310-57-2004 (Modification 05106H0894) was issued for the removal of the clearance fit bolts, the holes reamed oversize and the installation of interference fit bolts. The mandatory Inspection Service Bulletin A310-57-2037 (now superseded by Inspection Service Bulletin A310-57-2082) was also issued for HFEC inspections around the bolt heads of the access door landing to detect cracks. During routine maintenance on a Post Mod. 05106H0894 A310 aircraft, a crack of 62mm in length was found on the RH wing in the bottom skin panel. The crack was found at the trailing edge, forward of the all-speed-aileron servo control bay access door. This Service Bulletin has been issued for a modification to the LH and RH wing, as follows: - the cutting of the aileron access door landing plate into three parts - the cold expansion of the landing plate fastener holes - the installation of an interference fit plug - the installation of an external reinforcing plate - the cold expansion of the reinforcing plate attachment holes - the installation of interference fit fasteners. The embodiment of this Service Bulletin will prevent costly and time consuming repairs and should also ensure that the area is crack free beyond the Extended Service Goal (ESG) of the aircraft. The accomplishment of this Service Bulletin cancels the inspection requirements of the Inspection Service Bulletin A310-57-2082. This Service Bulletin also supersedes Service Bulletin A310-57-2004 beyond the extended service goal of the aircraft. DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 3 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN SUMMARY

EVALUATION TABLE COMPLIANCE Recommended CANCELS INSPECTION SB A310-57-2082 POTENTIAL AD No A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING Yes ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) B01R01 3440 KIT PRICE (USD) B02R01 3440

MODIFICATION CLASSIFICATION MAJOR None

MINOR 12525H5572
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. **E F**  **F E**  **C T**  **I V**  **I T** **Y** This Service Bulletin is applicable to this (these) operator(s) : 18T 19U 52X 58X 82Z 83V 98W 99Y ACQ AFG AIB AIC BAF BBC BLE CFC DAH DEC DGA F2I FDX G8E GAF HFY I2L IRA IRM IYE JAB JAV K1P KAC KTC KYV KZU MGL MWA PIA QAF R1T RJA ROT RZO SBI SGX SUD THY TSC UZB WHT WTJ C O N C U R R E N T R E Q U I R E M E N T S None R E F E R E N C E S/ R E P E R C U S S I O N S TFU : 57-20-00-019 OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN SUMMARY

OTHERS : None N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No M A N P OW E R Config. 01

**TOTAL MANHOURS 28.0 ELAPSED TIME (HOURS) 14.0**  M A T E R I A L I N FO R M A T I O N AIRCRAFT DATA Config. 01 aircraft require Kit 572081B01R01 and Kit 572081B02R01 consisting of, reinforcing plates, skin hole plugs and fasteners. A P P E N D I C E S None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

This Page Intentionally Left Blank

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# A310 SERVICE BULLETIN

**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 - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING PLATE**  **MODIFICATION No. :** 12525H5572 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. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. E**  **F F**  **E C** **T I**  **V I**  **T Y**  (1) Models 310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 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 0427-0429 0431 0434 0436 0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472 0473 0475 0476 0478 0480-0492 0494-0500 0502 0503 0519 0520 0522-0524 0526 0527 0531 0534 0537-0539 0541 0542 0544 0545 0547 0549-0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585-0588 0590-0595 0597 0599 0600 0620 0622 0624 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 0697 0700 0702 0704 0706 (b) Effectivity by Operator

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

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 18T 0473 19U 0399 52X 0410 58X 0431 82Z 0550 0551 83V 0427 98W 0672 99Y 0489 ACQ 0538 0544 AFG 0496 0497 AIB 0686 AIC 0392 0406 0407 0413 0428 0429 0654 0665 0669 0680 BAF 0367 0372 BBC 0594 0642 0700 BLE 0650 0674 CFC 0425 0441 0444 0446 0482 DAH 0291 0293 DEC 0684 0693 0697 DGA 0418 0421 0422 F2I 0309 0487 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 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 0593 0638 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

OPERATOR MSN G8E 0475 GAF 0434 0484 0498 0499 0503 0522 0523 HFY 0495 0565 I2L 0640 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0488 0537 0564 0586 0595 IYE 0568 0702 0704 JAB 0320 0419 JAV 0357 0481 K1P 0648 KAC 0647 0649 0663 KTC 0524 0567 0620 KYV 0386 KZU 0592 0622 0646 MGL 0526 MWA 0652 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0416 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0624 0651 0661 SBI 0486 0520 SGX 0519 0562 SUD 0437 THY 0476 0478 0480 0502 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

OPERATOR MSN TSC 0447 0472 0483 0485 0527 0541 0545 0547 0588 0597 0599 0600 0658 UZB 0574 0576 0706 WHT 0448 0573 WTJ 0494 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 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 0427-0429 0431 0434 0436-0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472-0473 0475-0476 0478 0480-0492 0494-0500 0502-0503 0519-0520 0522-0524 0526-0527 0531 0534 0537-0539 0541-0542 0544-0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 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 0697 0700 0702 0704 0706 KIT No. QTY PER A/C CONFIGURATION 572081B01R01 1 01 572081B02R01 1 01 NOTE : Config. 01 is valid for all aircraft given in the effectivity of this Service Bulletin. NOTE : Kit 572081B01R01 contains the components for the LH wing. NOTE : Kit 572081B02R01 contains the components for the RH wing. NOTE : The Repair Instruction R57349237 with the steel plate R57349236202/203 and Repair Instruction R57349243 with the aluminium plate are equivalent to this modification. (3) Spares None **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

**C. R E**  **A S**  **O N**  (1) History On the full scale wing fatigue test, skin cracking occurred in the area covered by this modification. The crack was found at 51,500 simulated flights and started from one of the access door landing plate attachment holes. Service Bulletin A310-57-2004 (Modification 05106H0894) was issued for the removal of the clearance fit bolts, the holes reamed oversize and the installation of interference fit bolts. The mandatory Inspection Service Bulletin A310-57-2037 (now superseded by Inspection Service Bulletin A310-57-2082) was also issued for HFEC inspections around the bolt heads of the access door landing to detect cracks. During routine maintenance on a Post Mod. 05106H0894 A310 aircraft, a crack of 62mm in length was found on the RH wing in the bottom skin panel. The crack was found at the trailing edge, forward of the all-speed-aileron servo control bay access door. (2) Objective/Action This Service Bulletin has been issued for a modification to the LH and RH wing, as follows: - the cutting of the aileron access door landing-plate into three parts - the cold expansion of the landing-plate fastener holes - the installation of an interference fit plug at a fastener hole - the installation of an external repair plate - the cold expansion of the repair plate attachment holes - the installation of interference fit fasteners. (3) Advantages The embodiment of this modification will prevent costly and time consuming repairs and should also ensure that the area is crack free beyond the extended service goal of the aircraft. The accomplishment of this Service Bulletin cancels the inspection requirements of the Inspection Service Bulletin A310-57-2082 beyond the ESG of the aircraft. This Service Bulletin also supersedes Service Bulletin A310-57-2004. (4) Operational/Maintenance Consequences None **D. D E**  **S C**  **R I**  **P T**  **I O**  **N** To accomplish this Service Bulletin it is necessary to: (1) Config. 01 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

(a) Get access to the modification areas at the all-speed-aileron servo control bay (underside of the LH and RH wing). (b) Do an HFEC inspection of the access panel landing-plate for cracks. (c) Remove the applicable fasteners and the access panel landing-plate. (d) Do an HFEC inspection of the landing-plate fastener holes in the wing skin for cracks. (e) If a crack is found at the fastener hole shown in Detail A of Figure 1, do a repair in accordance with Inspection Service Bulletin A310-57-2082. (f) If cracks are found in other areas of the landing-plate fasteners, contact AIRBUS, SEE-82 for instructions. (g) If cracks are not found do the modification, as follows: 1 Transfer drill the pilot holes from the external reinforcing plate into the wing skin. 2 Ream, cold expand and countersink all the fastener holes. 3 Mark the cut lines on the landing-plate and then remove it. 4 Cut the landing-plate into three sections. 5 Install the three sections of the landing-plate. 6 Install a fastener hole plug. 7 Install the external aluminium reinforcing plate. 8 Apply protective coating to the modification area. 9 Reidentify the landing-plates. 1 0 Close up. **E. C O**  **M P**  **L I**  **A N**  **C E**  (1) Classification Recommended (2) Accomplishment Timescale It is recommended to embody this modification at or before 10,200 FC. **F. A P**  **P R**  **O V**  **A L**  Approved under 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 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. **G. M A**  **N P**  **O W**  **E R**  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 Get access 1.0 Prepare modification on the LH wing 9.0 Install modification on the LH wing 4.0 Prepare modification on the RH wing 9.0 Install modification on the RH wing 4.0 Close up 1.0 **TOTAL MANHOURS 28.0 ELAPSED TIME (HOURS) 14.0**  **H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Config. 01 Manufacturers Empty Weight : +1.54 kg (+3.39 lb) Effect on Balance : +43.16 kgm (+311.69 lb.ft) **I. E L**  **E C** **T R**  **I C**  **A L**  **L O** **A D**  **D A**  **T**

**A** Not applicable **J. R E**  **F E**  **R E**  **N C**  **E S**  Aircraft Maintenance Manual (AMM) : 06-41-57 24-00-00 Structural Repair Manual (SRM) : 51-20-00 51-23-10 51-24-00 51-27-00 51-40-41 51-40-21 51-40-44 51-40-47 51-40-50 51-43-00 51-75-10 51-76-10 Nondestructive Testing Manual (NTM) : 51-10-01 Aircraft Maintenance Manual (AMM) : 06-41-57 24-00-00 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

Elec. Std. Practices Manual (ESPM) : 20-55-00 Service Bulletin (SB) : A310-57-2004 A310-57-2037 A310-57-2082 Process and Material Specification (PMS) : 01-06-12 **K. P U**  **B L**  **I C**  **A T**  **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  None **L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

**2. M A**  **T E**  **R I**  **A L**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. M**  **A T**  **E R**  **I A**  **L -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  (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 572081B01R01 Cost : 3440 US dollars Availability : 120 calendar days from receipt of order The sales terms (cost and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin Kit 572081B02R01 Cost : 3440 US dollars Availability : 120 calendar days from receipt of order The sales terms (cost and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin NOTE : The kit availability given is the standard lead time from the date of your purchase order. If you require the kit(s) before this time, please include your retrofit planning schedule with your order so that we can try to comply with your requirements. **B. I N**  **D U**  **S T**  **R Y**  **S U**  **P P**  **O R** **T I**  **N F**  **O R**  **M A**  **T I**  **O N**  None **C. L I**  **S T**  **O F**  **C O**  **M P**  **O N**  **E N**  **T S**  Kit 572081B01R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

1 NSA5476VHK4-6 11 Bolt 2 NSA5476VHK4-10 6 Bolt 3 NSA5478VHK4-12 4 Bolt 4 NSA5476VHK5-6 6 Bolt 5 NSA5476VHK5-8 4 Bolt 6 NSA5478VHK5-10 1 Bolt 7 NSA5478VHK5-12 1 Bolt 8 NSA5478VHK5-14 2 Bolt 9 NSA5478VHK5-16 2 Bolt 10 NSA5478VHK6-14 4 Bolt 11 NSA5478VHK6-16 1 Bolt 12 NSA5472-4K7 21 Nut 13 NSA5472-5K7 16 Nut 14 NSA5472-6K7 5 Nut 15 NSA5353D05B 16 Washer 16 NSA5353D04B 21 Washer 17 NSA5353D06B 5 Washer 18 R5704003020200 4 Washer 19 R5704003020400 5 Washer 20 R5734923620000 1 Plate 28 A5735801520000 1 Plug Kit 572081B02R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 NSA5476VHK4-6 11 Bolt 2 NSA5476VHK4-10 6 Bolt 3 NSA5478VHK4-12 4 Bolt 4 NSA5476VHK5-6 6 Bolt 5 NSA5476VHK5-8 4 Bolt 6 NSA5478VHK5-10 1 Bolt 7 NSA5478VHK5-12 1 Bolt 8 NSA5478VHK5-14 2 Bolt 9 NSA5478VHK5-16 2 Bolt 10 NSA5478VHK6-14 4 Bolt 11 NSA5478VHK6-16 1 Bolt 12 NSA5472-4K7 21 Nut 13 NSA5472-5K7 16 Nut 14 NSA5472-6K7 5 Nut 15 NSA5353D05B 16 Washer 16 NSA5353D04B 21 Washer 17 NSA5353D06B 5 Washer 18 R5704003020200 4 Washer 19 R5704003020400 5 Washer 21 R5734923620100 1 Plate 28 A5735801520000 1 Plug **D. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Sealant Mat. No. 09-002 As required Sealant Mat. No. 09-005 As required Cleaning agent Mat. No. 11-026 As required Alodine Mat. No. 13-002 As required Primer Mat. No. 16-006 As required (2) Components ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP A5724279520001 1 Landing A5724279520101 1 Landing NOTE : The items above will only be necessary if the old landings are found to be cracked. If necessary, procure by spares purchase order. **E. P A**  **R T** **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** LH Wing: ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT 22 A57358015202 Landing A57242795200 03 23 A57358015204 Landing A57242795200 03 24 A57358015206 Landing A57242795200 03 RH Wing: ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT 25 A57358015203 Landing A57242795201 03 26 A57358015205 Landing A57242795201 03 27 A57358015207 Landing A57242795201 03

**F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  Fatigue Technology Inc (FTI) has allocated tool Kit A310-572081-1 for accomplishment of this Service Bulletin. Operators who require these tools should contact: FATIGUE TECHNOLOGY INC. 401 Andover Park East Seattle WA 98188-7605 USA Tel: (206) 246-2010 Telex: 321004 Fax: (206) 244-9886

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

**G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - LANDING GEAR AND RELATED DOORS - COMPONENTS THAT MOVE. 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING. (1) Preparation (a) Config. 01 1 Make sure the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301) 2 Put access platforms in position under the LH and RH wing in the area of the all-speed-aileron servo control bay. 3 Open the access panels 575CB (675CB) (Refer to AMM 06-41-57, Page block 1). (2) Standard Practices (a) For the removal/installation of fasteners, refer to SRM 51-40-21. (b) For the drilling/reaming of fastener holes, refer to SRM 51-40-44. (c) For cold expanding fastener holes, refer to SRM 51-40-41. DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 13 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

(d) For the countersinking of fastener holes, refer to SRM 51-40-47. (e) For fastener spacing and margin data, refer to SRM 51-40-50. (f) For the cutting of the landing plates, refer to SRM 51-27-00. (g) For the wet assembly of components, refer to SRM 51-76-10. (h) For the torque value of the fasteners, refer to Figure 1, Sheet 2. (i) For the application of protective coating, Alodine 13-002 and primer 16-006, refer to SRM 51-75-10. (j) For the application of paint coatings, refer to SRM 51-23-10. (k) For the re-identification of items, refer to PMS 01-06-12. (l) Clean the modification areas with cleaning agent (Mat. No. 11-026). **B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  (1) Config. 01 (a) Preparation of the Landing plate, Wing Skin and Reinforcing Plate Kit 572081B01R01 (LH wing) and Kit 572081B02R01 (RH wing) Refer to Figure 1, Sheet 1, Sheet 2 The worksteps that follow are applicable to the LH and RH wing. 1 At the access panel area (575CB/675CB), do a HFEC inspection around the landing-plate fasteners and along the full length of the landing-plate between the fasteners, LH and RH wing. Inspect the inside and outside surfaces except for the four hole positions at the aileron hinge ribs where it is only possible to inspect the outside surface. (Refer to Figure 1, Sheet 1 and NTM 51-10-08, Part 6). 2 If cracks are found on the landing-plate after workstep (a), a new landing-plate A5724279520001 (LH) or A5724279520101 (RH) will be necessary. NOTE : Use the old landing-plate as a template to transfer drill the fastener holes to the new landing-plate. Transfer the camlok receptacles from the old landing-plate to the new landing-plate. Use the old landing-plate as a template for the position of the camlok receptacles on the new landing-plate. 3 At the access panel area (575CB/675CB), remove and discard the landing-plate fasteners. Remove and retain the landing-plate if no cracks were found at workstep (a). CAUTION : GREAT CARE MUST BE TAKEN NOT TO DAMAGE THE WING SKIN WHEN YOU CUT THE LANDING-PLATE IN ITS INSTALLED POSITION.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 14 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

NOTE : If it is difficult to remove the landing-plate in one piece, you can cut the plate in its installed position, at the applicable areas (Refer to Figure 1), and then remove the plate. 4 Do a HFEC inspection of the landing plate fastener holes (Refer to NTM 51-10-01 Part 6, Procedure A and Figure 1, Sheet 1): - if only the fastener hole shown in Detail A is found cracked, do a repair in accordance with Service Bulletin A310-57-2082, - if cracks are found in other areas of the landing plate fasteners, contact AIRBUS, SEE-82, for instructions, - if cracks are not found, continue with the modification, as follows: 5 Remove and discard the fasteners in the area where the reinforcing plate will be installed. 6 Put the landing plate in its installation position on the wing skin and temporarily slave bolt in position. 7 Put the reinforcing plate, Item 20 or Item 21, temporarily in position and transfer drill the ten pilot holes into the wing skin. 8 Attach the reinforcing plate, Item 20 or Item 21, with slave bolts. 9 Drill/ream the existing and new fastener holes of the skin, landing and reinforcing plate to the start hole diameter. Cold expand the holes and ream to the final hole diameter, Refer to Figure 1, Sheet 1, Sheet 2 and the FTI tool Kit A310-572081-1. NOTE : The skin plug, Item 28, installation hole is to be cold expanded through the landing plate and skin only (Refer to Figure 1, Sheet 1, Detail A). NOTE : Alternate the installation of the temporary slave bolts of the landing plate and reinforcing plates to allow the reaming and cold expansion of the fastener holes. 1 0 Refer to Figure 1, Sheet 1 and mark the landing plate to the dimensions shown. 1 1 Remove the reinforcing plate and the landing plate. 1 2 Countersink the fastener holes (Refer to Figure 1, Sheet 2). 1 3 Deburr all the holes. 1 4 Cut the landing plate at the two positions that you have marked. NOTE : If necessary, reprofile the reinforcing plate, Item 20 and/or Item 21, to prevent any overlap of adjacent fasteners (the minimum edge clearance must be 2D). If re-profiled, make sure the plate edge radius is 0.22in. (5.6mm). DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

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# A310 SERVICE BULLETIN

1 5 Apply protective coating to the cut areas of the landing plates and, if applicable, to the reprofiled areas of the reinforcing plate. (b) Installation of the Landing Plates and Reinforcing Plate (LH and RH wing) Kit 572081B01R01 and Kit 572081B02R01 Refer to Figure 1, Sheet 1, Sheet 2 1 Install the three sections of the landing plates, Items 22, 23, 24 or Items 25, 26, 27, on the wing skin. For the landing plate, Items 22 (25), wet install with sealant (Mat. No. 09-005) these fasteners: 4 Bolts NSA5476VHK4-6 Item 1 3 Bolts NSA5478VHK4-12 Item 3 7 Washers NSA5353D04B Item 16 7 Nuts NSA5472-4K7 Item 12

For the landing plate, Item 23 (26), wet install with sealant (Mat. No. 09-005) these fasteners: 6 Bolts NSA5478VHK4-6 Item 1 1 Bolt NSA5478VHK5-10 Item 6 6 Nuts NSA5472-4K7 Item 12 1 Nut NSA5472-5K7 Item 13 1 Washer NSA5353D05B Item 15 6 Washers NSA5353D04B Item 16

For the landing plate, Item 24 (27), wet install with sealant (Mat. No. 09-005) these fasteners: 1 Bolt NSA5476VHK4-6 Item 1 1 Bolt NSA5478VHK4-12 Item 3 2 Washers NSA5353D04B Item 16 2 Nuts NSA5472-4K7 Item 12 1 Bolt NSA5478VHK5-12 Item 7 1 Washer NSA5353D05B Item 15 1 Nut NSA5472-5K7 Item 13 1 Plug A57358015200 Item 28

NOTE : Make sure that the head of the skin plug, Item 28, is installed to the dimensions given in Detail A of Figure 1, Sheet 1. Fill the void at the tail of the plug with sealant (Mat. No. 09-002). 2 Apply protective coating to the head of the plug and the heads of the fasteners in the landing plates. 3 Apply sealant (Mat. No. 09-005) and put these countersink washers in position on the fastener holes at the aileron hinge ribs: 4 Washers R57040030202 Item 18 5 Washers R57040030204 Item 19 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 16 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

NOTE : The countersink washers, Items 18 and 19, are used to fill the existing countersinks in the aileron hinge ribs. 4 Apply sealant (Mat. No. 09-005) to the mating surfaces of the reinforcing plate, Item 20 or Item 21, and the skin. 5 Put this reinforcing plate in position: 1 Plate R57349236200 Item 20

or: 1 Plate R57349236201 Item 21

and wet install these fasteners with sealant (Mat. No. 09-005): 6 Bolts NSA5476VHK4-10 Item 2 6 Washers NSA5353D04B Item 16 6 Nuts NSA5472-4K7 Item 12

and: 4 Bolts NSA5476VHK5-8 Item 5 4 Washers NSA5353D05B Item 15 4 Nuts NSA5472-5K7 Item 13

and: 6 Bolts NSA5476VHK5-6 Item 4 6 Washers NSA5353D05B Item 15 6 Nuts NSA5472-5K7 Item 13

and: 2 Bolts NSA5478VHK5-14 Item 8 2 Washers NSA5353D05B Item 15 2 Nuts NSA5472-5K7 Item 13

and: 4 Bolts NSA5478VHK6-14 Item 10 4 Washers NSA5353D06B Item 17 4 Nuts NSA5472-6K7 Item 14

and: 2 Bolts NSA5478VHK5-16 Item 9 2 Washers NSA5353D05B Item 15 2 Nuts NSA5472-5K7 Item 13

and: 1 Bolt NSA5478VHK6-16 Item 11 DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 17 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

1 Washer NSA5353D06B Item 17 1 Nut NSA5472-6K7 Item 14 6 Remove all swarf from inside the servo control bay area. 7 Apply a bead of sealant around the reinforcing plate, Item 20 (21). 8 Apply protective coating to the reinforcing plate fasteners. 9 Apply external paint to the repaired area (to the applicable aircraft paint scheme). 1 0 Reidentify the three sections of the landing plates (LH wing), as follows: - Item 22 as A57358015202. - Item 23 as A57358015204. - Item 24 as A57358015206. 1 1 Reidentify the three sections of the landing plates (RH wing), as follows: - Item 25 as A57358015203. - Item 26 as A57358015205. - Item 27 as A57358015207. **C. T E**  **S T**  None **D. C L**  **O S**  **E U**  **P** (1) Config. 01 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 575CB (675CB). (c) Remove the access platforms. (d) Put the aircraft and the systems in a normal operating condition. **E. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 18 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

Figure 1, Sheet 1 Config. 01 : Reinforcing Plate Installation DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 19 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

Figure 1, Sheet 2 Config. 01 : Reinforcing Plate Installation
DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 20 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN REPORTING SHEET

**TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING PLATE**  **MODIFICATION No. :** 12525H5572 P l e as e co m p l et e t h e a p p ro p r i at e i t e m (A o r B ) : A - SB W I L L B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. B - SB H AS B E E N embodied on aircraft: ............................................................................................................

............................................................................................................................... ..............................................

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

..............................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. From Airline: ...................................................................................................................

..................................... Name/Title: ....................................................................................................................

...................................... Signature:..................... Date: ..................................................... I f o p e rat i o n a l d o c u m e n tat i o n i s affe ct e d (s e e Pa ra g ra p h 1

. K of t h i s S B ) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m p o rta n t I n fo r m at i o n : 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. P l e as e ret u r n t h i s co m p l et e d s h e et to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 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.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN REPORTING QUALITY

**TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING PLATE**  **MODIFICATION No. :** 12525H5572 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 futher 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 C o m m e n ts :

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEMB Service Bulletins Management FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office. DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved