# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS STRUCTURE- FUELACCESS PANELS- INTRODUCTION OF REPLACEMENT PANELS (REPLACED TYPE 21 BY 11A) MODIFICATION No.: 13564H5728 13626H5742 This page transmits Revision No.01 of Service Bulletin No.A310-57-2097 ADDITIONAL WORK **CONF ALL Additional work is required by this revision for aircraft modified at Revision No. 00 of this Service Bulletin. REASON Revision No. 01 issued to: - add modification 13626H5742 to replace the fuel tank access panel labelling to prevent installation of fasteners of an incorrect length when Type 11 access panels are installed - include weight and balance figures - update the GENERAL EVALUATION table - extend the effectivity to include A310-203, A310-204 and A310-222 aircraft - update illustrations - include additional work (to paint mark the new access panel fastener details) for aircraft modified at Revision No. 00. CHANGES FRONT MATTER MODIFICATIONS MODIFICATION NUMBER(S) UPDATED R SUMMARY MODIFICATIONS MODIFICATION CLASSIFICATION UPDATED R GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R Fig. A-USUAA Fig. A-USUAA Sheet 01 SHEET UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R APPROVAL APPROVAL UPDATED R MANPOWER MANPOWER UPDATED R WEIGHT AND BALANCE WEIGHT AND BALANCE UPDATED R WEIGHT AND BALANCE ADDED N REFERENCES REFERENCED DOCUMENTATION UPDATED R INTERCHANGEABILITY/MIXABILITY INTERCHANGEABILITY/MIXABILITY UPDATED R MATERIAL INFORMATION LIST OF COMPONENTS Kit 572097B01R02 PART MATERIAL SET UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED R
LIST OF MATERIALS - OPERATOR SUPPLIED Consumable Materials Consumable CMLB01 CONSUMABLE MATERIAL SET UPDATED QUANTITY UPDATED CONSUMABLE UPDATED R
ACCOMPLISHMENT INSTRUCTIONS TASK 572097- 831-895-001-WINGS - INTRODUCTION OF REPLACEMENT FUEL ACCESS PANELS TASK SOLUTION UPDATED CAUTION UPDATED R
Task associated data - 001 PANEL UPDATED ZONE UPDATED MAN HOURS UPDATED ELAPSED TIME UPDATED R

Subtask 572097-910-401-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED PANEL UPDATED ZONE UPDATED WARNING UPDATED R

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 2 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 572097-831-401-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED PANEL UPDATED ZONE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED REFERENCES UPDATED NOTE UPDATED R

Subtask 572097-930-401-001 SUBTASK SOLUTION ADDED N Subtask 572097-831-402-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED PANEL UPDATED ZONE UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED NOTE UPDATED R

Subtask 572097-790-401-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED PANEL UPDATED ZONE UPDATED REFERENCED DOCUMENTATION UPDATED R

TASK 572097- 831-896-001-PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK TASK SOLUTION ADDED N
Task associated data - 001 TASK ASSOCIATED DATA ADDED N Subtask 572097-839-402-001 SUBTASK SOLUTION ADDED N Subtask 572097-941-401-001 SUBTASK SOLUTION ADDED N Subtask 572097-010-401-001 SUBTASK SOLUTION ADDED N Subtask 572097-930-402-001 SUBTASK SOLUTION ADDED N Subtask 572097-410-401-001 SUBTASK SOLUTION ADDED N Subtask 572097-790-402-001 SUBTASK SOLUTION ADDED N Subtask 572097-942-402-001 SUBTASK SOLUTION ADDED N Fig. A-UBAAA FIGURE SOLUTION ADDED N Fig. A-UBAAA Sheet 01 SHEET ADDED N Fig. A-UAAAA FIGURE SOLUTION UPDATED R Fig. A-UAAAA Sheet 01 SHEET UPDATED R Fig. A-UAAAA Sheet 02 SHEET ADDED N
DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 3 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET FILLING INSTRUCTIONS 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. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Apr 11/11 REVISION No. : 01 - Sep 29/11

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 4 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. 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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS STRUCTURE- FUELACCESS PANELS- INTRODUCTION OF REPLACEMENT PANELS (REPLACED TYPE 21 BY 11A) **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13564H5728 MINOR 13626H5742 NOTE: 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. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES This Service Bulletin introduces a modification to replace the fuel access panels at manhole positions No. 1 and No. 2 of A310-300 Pre Mod. 07257 aircraft which meets the current airworthiness regulation in agreement with EASA. As a result of obsolescence, Super Plastic Formed (SPF) panels are no longer manufactured. This Service Bulletin will introduce a solution to replace the SPF Type 21 access panels and associated Type 21 clamp ring with a Type 11 machined access panel and Type 11A clamp plate. Using the Type 11A clamp plate at manhole positions No. 1 and No. 2 will require one of the two locating lugs in the wing skin panel to be filled with aerodynamic filler. The accomplishment of this Service Bulletin will enable compliance with the latest airworthiness regulations and provide spares capability for the obsolete SPF panel. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY EVALUATION TABLE STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO DE-FUELLING/VENTILATION YES NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 572097B01R02 4 25,360.00 Type 11 Fuel Access Panel, Type 11A Clamp Plate, Knitted Gasket, Screws EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 46T 52X 58X 83V 98W 99Y AFG AIC CFC DGA F2I FDX G8E GAF HFY IRA IRM JAV RJA SUD THY TSC WHT WTJ CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 572097-831-895-001: WINGS - INTRODUCTION OF REPLACEMENT FUEL ACCESS PANELS TOTAL MANHOURS 22.00 ELAPSED TIME (HOURS) 20.00

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 2 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY Task 572097-831-896-001: PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 18.00 APPENDICES None

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 3 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

RIB2 RIB10 Z540 (Z640)

MANHOLE POSITION NO.2 MANHOLE POSITION NO.1

B_SB_572097_7_SUAA_01_01 ACCESS PANEL

SEALING RING

PROTECTIVE RING

KNITTED GASKET
CLAMP RING/PLATE WING SKIN ACCESS PANEL

SEALING RING

KNITTED GASKET
CLAMP PLATE WING SKIN 

### BEFORE **AFTER** LH WING SHOWN RH WING SIMILAR



## A **B A**  **B A**  **B**

Figure A-USUAA - Sheet 01
DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 4 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS STRUCTURE- FUELACCESS PANELS- INTRODUCTION OF REPLACEMENT PANELS (REPLACED TYPE 21 BY 11A) MODIFICATION No.: 13564H5728 13626H5742 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 **CONF ALL A. EFFECTIVITY (1) Models 310-203 310-204 310-222 310-304 310-322 310-324 (2) Effectivity by MSN 0378 0392 0399 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 0480-0485 0487-0492 0494-0499 (3) 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 18T 0473 19U 0399 DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

OPERATOR MSN 46T 0413 52X 0410 58X 0431 83V 0427 98W 0416 99Y 0489 AFG 0496 0497 AIC 0392 0406 0407 0428 0429 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0419 0487 FDX 0378 0439 0449 0452 0454 0456 0457 0458 0467 0492 G8E 0475 GAF 0434 0484 0498 0499 HFY 0495 IRA 0436 IRM 0488 JAV 0481 RJA 0445 0490 0491 SUD 0437 THY 0476 0478 0480 TSC 0447 0472 0483 0485 WHT 0448 WTJ 0494 (4) Configuration by MSN MSN CONFIGURATION 0378 0392 0399 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427 0428 0429 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0448 0449 0452 0454 0456 0457 0458 0467 0472 0473 0475 0476 0478 0480 0481 0482 0483 0484 0485 0487 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 001

(5) Configuration definition **CONF 001 Config. 01 is valid for all A310 aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLB01 As required Kit 572097B01R02 4

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 2 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
B. CONCURRENT REQUIREMENTS None C. REASON (1) History This Service Bulletin introduces a modification to replace the fuel access panels at manhole positions No. 1 and No. 2 of A310-300 Pre Mod. 07257 aircraft which meets the current airworthiness regulation in agreement with EASA. As a result of obsolescence, Super Plastic Formed (SPF) panels are no longer manufactured. (2) Objective/Action This Service Bulletin will introduce a solution to replace the SPF Type 21 access panels and associated Type 21 clamp ring with a Type 11 machined access panel and Type 11A clamp plate. Using the Type 11A clamp plate at manhole positions No. 1 and No. 2 will require one of the two locating lugs in the wing skin panel to be filled with aerodynamic filler. (3) Advantages The accomplishment of this Service Bulletin will enable compliance with the latest airworthiness regulations and provide spares capability for the obsolete SPF panel. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 572097-831-895-001: WINGS - INTRODUCTION OF REPLACEMENT FUEL ACCESS PANELS (1) Remove the Type 21 Fuel Access Panels And Associated Clamp Rings (2) Paint Mark the New Access Panel Fastener Details (3) Install the Type 11 Fuel Access Panels And Associated Type 11A Clamp Plates Task 572097-831-896-001: PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK (1) Remove the Type 11 Fuel Access Panels (2) Paint Mark the New Access Panel Fastener Details (3) Install the Type 11 Fuel Access Panels

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 3 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The accomplishment timescale, which has not yet been defined, will be given in the AD. F. APPROVAL The technical content of this document is approved under the authority of Design Organization 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. Task 572097-831-895-001: WINGS - INTRODUCTION OF REPLACEMENT FUEL ACCESS PANELS Get Access 6.50 On Aircraft Remove the Type 21 Fuel Access Panels And Associated Clamp Rings 4.00 Paint Mark the New Access Panel Fastener Details 2.00 Install the Type 11 Fuel Access Panels And Associated Type 11A Clamp Plates 6.00 Tests 2.00 Close-Up 1.50 TOTAL MANHOURS 22.00 ELAPSED TIME (HOURS) 20.00 Task 572097-831-896-001: PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK Get Access 6.50 On Aircraft Remove the Type 11 Fuel Access Panels 4.00 DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 4 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

Task 572097-831-896-001: PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK Paint Mark the New Access Panel Fastener Details 2.00 Install the Type 11 Fuel Access Panels 4.00 Tests 2.00 Close-Up 1.50 TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 18.00 H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. NOTE: The weight increase shown is for the replacement of all 4 access panels (2 on the LH wing and 2 on the RH wing). Manufacturers Empty Weight +5.196 KG (+11.455 LB) Effect on Balance +105.499 KGM (+763.074 LB.FT) I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 11-00-00 12-11-28 28-11-22 28-25-00 51-75-10 Common Support Data Dictionary (CSDD) ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-55-00 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 28-11-23 L. INTERCHANGEABILITY/MIXABILITY When the Pre Mod 13564H5728 Fuel Access Panel assembly is removed, it must be replaced by the Post Mod 13564/H5728 Fuel Access Panel assembly, and the associated fuel tank access panel labelling must be modified. When the Post Mod 13564H5728 assembly is removed, it must be replaced by the Post Mod 13564H5728 Fuel Access Panel assembly. NOTE: For definitions of interchangeability codes in column INT. refer to Chapter 2.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 5 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Bolt NAS2804-6 NAS1154-3 01 Not Applicable Access Panel A5735012200200 A5735005100000 01 Not Applicable Knitted Gasket A5735011820000 A5735007820200 01 Not Applicable Clamp Ring/Plate A5735011720000 A5735020000000 01 Not Applicable NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. M. SPARES None

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 6 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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: Kit 572097B01R02 AIRBUS Material Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability

Kit 572097B01R02 Cost 6,340.00 USD Availability 120 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 Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 572097B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 A5735005100000 1 Panel (5) A5735012200200 01 10 A5735007820200 1 Gasket (4) A5735011820000 01 11 A5735020000000 1 Plate (3) A5735011720000 01 12 NAS1154-3 20 Screw (2) NAS2804-6 01 NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 7 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Clear Varnish 07-018 As required Masking Tape 08-661 As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As requiredAnti-Corrosion Primer (EpoxyImproved Adhesion) 16-006 As required Polyurethane White Topcoat, Exterior 16-008 As required External Top Coat-White 16-018 As required Lint-Free Cotton Cloth 19-003 As required White Talcum Powder 19-004 As required Scotch Brite Pads 19-011 As required 8 Fillet Sealant 09-016 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 8 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 572097-831-895-001 - WINGS - INTRODUCTION OF REPLACEMENT FUEL ACCESS PANELS Task Associated Data Zone 540 640 Access Panel 540AB 540BB 640AB 640BB Manpower TOTAL MANHOURS 22.00 ELAPSED TIME (HOURS) 20.00 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. (1) Subtask 572097-839-401-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 9 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
B. PREPARATION (1) Subtask 572097-910-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 540 Work location Panel 540AB Panel 540BB 640 Work location Panel 640AB Panel 640BB Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401 28-25-00, Page Block 301 WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION. MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. MAKE SURE THAT THE FIRE FIGHTING EQUIPMENT IS AVAILABLE AND ADEQUATE. MAKE SURE THAT YOU ISOLATE THE ELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS. (a) Transfer fuel from the inner tank or defuel the inner tank (Refer to AMM 28-25-00, Page Block 301). (b) Open, safety and tag the relevant circuit breakers (Refer to AMM 28-11-22, Page Block 401). (c) Drain the residual fuel from the inner tank water drains (Refer to AMM 28-25-00, Page Block 301). (d) Put a 5.5m (18 ft) access platform in position below the access panels 540AB(640AB) and 540BB(640BB).

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 10 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 572097-831-401-001 - Remove the Type 21 Fuel Access Panels And Associated Clamp Rings Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB 640 Access Panel 640AB, Panel 640BB Manpower Resources Manhours 4.00 Minimum number of person 1 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401 Fig. A-UBAAA Access Panel Type 21 Sheet 01
NOTE: The procedure that follows applies to the L/H wing and is the same for the R/H wing. NOTE: The procedure that follows applies to manhole positions No. 1 and No. 2 (access panels 540AB and 540BB on the LH wing and (640AB) and (640BB) on the RH wing). (a) Remove the access panel 540AB from manhole position No. 1 and access panel 540BB from manhole position No. 2 (Refer to AMM 28-11-22, Page Block 401 and Fig. A-UBAAA Sheet 01) and remove these items: 40 Bolt NAS2804-6 Item (2) Discard 2 Clamp Ring/Plate A5735011720000 Item (3) Discard 2 Knitted Gasket A5735011820000 Item (4) Discard 2 Access Panel A5735012200200 Item (5) Discard 2 Ring-Sealing A5735012020000 Item (6) Discard 2 Ring-Protective A5735011220000 Item (7) Discard (b) Do workstep C.(1)(a) again for the RH wing access panel (640AB) at manhole position No. 1 and (640BB) at manhole position No. 2.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 11 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (2) Subtask 572097-930-401-001 - Paint Mark the New Access Panel Fastener Details Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB Work location Rib 2 Rib 6 640 Access Panel 640AB, Panel 640BB Work location Rib 2 Rib 6 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Clear Varnish 07-018 As required Masking Tape 08-661 As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer (Epoxy-Improved Adhesion) 16-006 As required Polyurethane White Topcoat, Exterior 16-008 As required External Top Coat-White 16-018 As required Lint-Free Cotton Cloth 19-003 As required Scotch Brite Pads 19-011 As required References Aircraft Maintenance Manual (AMM) 11-00-00, Page Block 001 51-75-10, Page Block 801 Fig. A-UAAAA Access Panel Type 11 Sheet 01

- Access Panel Type 11 with Clamp Plate Type 11A and Aerodynamic Filler Sheet 02

- Access Panel Type 11 Skin Door Fastener Identification

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 12 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (a) At each of the door fastener labels at Rib 2 and Rib 6 (Refer to Fig. A-UAAAA Sheet 01, Detail A and Fig. A-UAAAA Sheet 02, Detail C), do the steps that follow: 1 Remove the Old Paint Marked Bolt Identification Label Information Apply Masking Tape 08-661 As required around the bolt identification lettering ’NAS2804-6’ (Refer to AMM 11-00-00, Page Block 001). 2 Lightly abrade the door fastener labels with silicon carbide paper and Scotch Brite Pads 19-011 As required to remove the varnish and paint layers (Refer to AMM 51-75-10, Page Block 801). 3 Use Lint-Free Cotton Cloth 19-003 As required
made moist with Solvent General Purpose 11-026 As required to clean the abraded areas. Let the cleaned surfaces dry. 4 Prepare the Bolt Identification Label Areas Apply Chemical Conversion Coating Yellow Aluminum 13-002 As required

to the bare metal areas. 5 Apply Anti-CorrosionPrimer (EpoxyImproved Adhesion) 16-006 As required
in the taped off areas. Let the paint dry for a minimum of 4 hours. 6 Apply Polyurethane White Topcoat, Exterior 16-008 As required

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 13 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

orExternal Top CoatWhite 16-018 As required over the primer. Let the paint cure until it is dry. 7 Mark the new Bolt Identification Information Use a MARKER PEN 8404 and write the new panel bolt information ’NAS1154-3’ on the white painted area. Let the ink dry. NOTE: Make sure that the lettering looks the same as the lettering ’ALL SKIN DOOR FASTENERS’ (Refer to Fig. A-UAAAA Sheet 02, Detail D). 8 Apply a layer of Clear Varnish 07-018 As required over the new door fastener label lettering. Let the varnish dry. NOTE: Make sure that the varnish is applied with a single brush stroke. Subsequent brush strokes may cause damage to the new lettering. 9 Remove and discard the masking tape. (b) Adhesion Test At each of the door fastener labels at Rib 2 and Rib 6 (Refer to Fig. A-UAAAA Sheet 02, Detail D, Section C-C), do the steps that follow: 1 Use Lint-Free Cotton Cloth 19-003 As required
made moist with Solvent General Purpose 11-026 As required
to clean the areas to be tested. 2 Apply Masking Tape 08-661 As required approximately 100 to 150mm (4.0 to 6.0in.) in length to the new varnished area. 3 Use a roller (and over a contact length of approximately 50 to 75mm (2.0 to 3.0in.)) push the masking tape onto the new varnished area. DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 14 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

4 Hold the remaining masking tape at an angle of approximately 160 degrees, and in a single movement, quickly pull off the masking tape. Discard the masking tape. 5 If any of the paint marking comes off, do steps (2)(a) thru (2)(b) again. (c) Make sure that all the masking tape is removed from the fuel tank. (3) Subtask 572097-831-402-001 - Install the Type 11 Fuel Access Panels And Associated Type 11A Clamp Plates Work Zones and Access Panels Zone Access/Work location 540 Work location Panel 540AB Panel 540BB 640 Work location Panel 640AB Panel 640BB Manpower Resources Manhours 6.00 Minimum number of person 1 Skills AIRFRAME Material necessary to do the job Kit 572097B01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 A5735005100000 1 Panel 10 A5735007820200 1 Gasket 11 A5735020000000 1 Plate 12 NAS1154-3 20 Screw Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES 8 Fillet Sealant 09-016 As required White Talcum Powder 19-004 As required References Aircraft Maintenance Manual (AMM) 11-00-00, Page Block 001 28-11-22, Page Block 401 51-75-10, Page Block 801 Fig. A-UAAAA Access Panel Type 11 Sheet 01

- Access Panel Type 11 with Clamp Plate Type 11A and Aerodynamic Filler Sheet 02

- Access Panel Type 11 Skin Door Fastener Identification NOTE: The procedure that follows applies to the L/H wing and is the same for DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 15 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN the R/H wing. NOTE: The procedure that follows applies to manhole positions No. 1 and No. 2 (access panels 540AB and 540BB on the LH wing and (640AB) and (640BB) on the RH wing). (a) Prepare the manholes at Rib 2 and Rib 6 for installation of new panels (Refer to AMM 28-11-22, Page Block 401). (b) Mix Item 8 Fillet Sealant 09-016 As required of 5.4 parts base to 1.0 part cure agent by weight first: 1 Slowly mix the curing agent into the base using a spatula. 2 Make sure that the curing agent and base are fully mixed together. (c) Push the sealant into the outboard lobe recess of the skin panel cut-out using a non-metallic spreader (Refer to Fig. A-UAAAA Sheet 01, Detail B and Section B-B). (d) Remove air bubbles or voids in the sealant and leave to cure for 3 hours at 23 +/- 2 degrees. (e) Make sure that the fillet sealant is touch dry. (f) Use silicon carbide paper (320 grade) to get the sealant to the same shape as the cut-out in the skin panels and flush to the aircraft skin (Refer to Fig. A-UAAAA Sheet 01, Detail B, Section B-B). (g) Make sure that the fuel tank is clean and clear of unwanted material, tools and other items of equipment. (h) Apply a light dusting of White Talcum Powder 19-004 As required to the sealing ring of the Panel Assy-Access,Type 11, Item 9. (i) Install the items that follow (Refer to AMM 28-11-22, Page Block 401 and Fig. AUAAAA Sheet 01):1 Panel AssyAccess,Type 11 A5735005100000 Item 9
1 Gasket-Knitted A5735007820200 Item 10 1 Clamp Plate,Type 11A A5735020000000 Item 11 20 Screw NAS1154-3 Item 12
DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 16 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
D. TEST (1) Subtask 572097-790-401-001 - Leak Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB 640 Access Panel 640AB, Panel 640BB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 28-25-00 (a) Transfer sufficient fuel to the inner tanks (Refer to AMM 28-25-00, Page Block 301) or refuel the inner tanks (Refer to AMM 12-11-28, Page Block 301). (b) Inspect the new access panels 540AB(640AB) and 540BB(640BB) for leaks. E. CLOSE-UP (1) Subtask 572097-942-401-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Make sure that the working area is clean and clear of all tools and other items of equipment. (b) Remove the access platform. (c) Remove all ground handling and maintenance equipment, standard and special tools, all access equipment and other items.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 17 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 18 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Task 572097-831-896-001 - PAINT MARK THE NEW ACCESS PANEL FASTENER DETAILS - ADDITIONAL WORK 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data Zone 540 640 Access Panel 540AB 540BB 640AB 640BB Manpower TOTAL MANHOURS 20.00 ELAPSED TIME (HOURS) 18.00 A. GENERAL (1) Subtask 572097-839-402-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 572097-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 540 Work location Panel 540AB Panel 540BB DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 19 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

640 Work location Panel 640AB Panel 640BB Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401 28-25-00, Page Block 301 WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION. MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. MAKE SURE THAT THE FIRE FIGHTING EQUIPMENT IS AVAILABLE AND ADEQUATE. MAKE SURE THAT YOU ISOLATE THE ELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS. (a) Transfer fuel from the inner tank or defuel the inner tank (Refer to AMM 28-25-00, Page Block 301). (b) Open, safety and tag the relevant circuit breakers (Refer to AMM 28-11-22, Page Block 401). (c) Drain the residual fuel from the inner tank water drains (Refer to AMM 28-25-00, Page Block 301). (d) Put a 5.5m (18 ft) access platform in position below the access panels 540AB(640AB) and 540BB(640BB). C. PROCEDURE (1) Subtask 572097-010-401-001 - Remove the Type 11 Fuel Access Panels Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB 640 Access Panel 640AB, Panel 640BB

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 20 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401 (a) Remove the access panels that follow (Refer to AMM 28-11-22, Page Block 401): 1 Remove the access panel 540AB from manhole position No. 1 and access panel 540BB from manhole position No. 2 on the LH wing. 2 Remove the access panel 640AB from manhole position No. 1 and access panel 640BB from manhole position No. 2 on the RH wing. (2) Subtask 572097-930-402-001 - Paint Mark the New Access Panel Fastener Details Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB Work location Rib 2 Rib 6 640 Access Panel 640AB, Panel 640BB Work location Rib 2 Rib 6 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Clear Varnish 07-018 As required Masking Tape 08-661 As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer (Epoxy-Improved Adhesion) 16-006 As required Polyurethane White Topcoat, Exterior 16-008 As required
DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 21 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES External Top Coat-White 16-018 As required Lint-Free Cotton Cloth 19-003 As required Scotch Brite Pads 19-011 As required References Aircraft Maintenance Manual (AMM) 11-00-00, Page Block 001 51-75-10, Page Block 801 Fig. A-UAAAA Access Panel Type 11 Sheet 01

- Access Panel Type 11 with Clamp Plate Type 11A and Aerodynamic Filler Sheet 02

- Access Panel Type 11 Skin Door Fastener Identification (a) At each of the door fastener labels at Rib 2 and Rib 6 (Refer to Fig. A-UAAAA Sheet 01, Detail A and Fig. A-UAAAA Sheet 02, Detail C), do the steps that follow: 1 Remove the Old Paint Marked Bolt Identification Label Information Apply Masking Tape 08-661 As required around the bolt identification lettering ’NAS2804-6’ (Refer to AMM 11-00-00, Page Block 001). 2 Lightly abrade the door fastener labels with silicon carbide paper and Scotch Brite Pads 19-011 As required to remove the varnish and paint layers (Refer to AMM 51-75-10, Page Block 801). 3 Use Lint-Free Cotton Cloth 19-003 As required
made moist with Solvent General Purpose 11-026 As required to clean the abraded areas. Let the cleaned surfaces dry. 4 Prepare the Bolt Identification Label Areas Apply

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 22 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

Chemical Conversion Coating Yellow Aluminum 13-002 As required

to the bare metal areas. 5 Apply Anti-CorrosionPrimer (EpoxyImproved Adhesion) 16-006 As required
in the taped off areas. Let the paint dry for a minimum of 4 hours. 6 Apply Polyurethane White Topcoat, Exterior 16-008 As required

orExternal Top CoatWhite 16-018 As required over the primer. Let the paint cure until it is dry. 7 Mark the new Bolt Identification Information Use a MARKER PEN 8404 and write the new panel bolt information ’NAS1154-3’ on the white painted area. Let the ink dry. NOTE: Make sure that the lettering looks the same as the lettering ’ALL SKIN DOOR FASTENERS’ (Refer to Fig. A-UAAAA Sheet 02, Detail D). 8 Apply a layer of Clear Varnish 07-018 As required over the new door fastener label lettering. Let the varnish dry. NOTE: Make sure that the varnish is applied with a single brush stroke. Subsequent brush strokes may cause damage to the new lettering. 9 Remove and discard the masking tape. (b) Adhesion Test At each of the door fastener labels at Rib 2 and Rib 6 (Refer to Fig. A-UAAAA Sheet 02, Detail D, Section C-C), do the steps that follow:

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 23 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

1 Use Lint-Free Cotton Cloth 19-003 As required
made moist with Solvent General Purpose 11-026 As required
to clean the areas to be tested. 2 Apply Masking Tape 08-661 As required approximately 100 to 150mm (4.0 to 6.0in.) in length to the new varnished area. 3 Use a roller (and over a contact length of approximately 50 to 75mm (2.0 to 3.0in.)) push the masking tape onto the new varnished area. 4 Hold the remaining masking tape at an angle of approximately 160 degrees, and in a single movement, quickly pull off the masking tape. Discard the masking tape. 5 If any of the paint marking comes off, do steps (2)(a) thru (2)(b) again. (c) Make sure that all the masking tape is removed from the fuel tank. (3) Subtask 572097-410-401-001 - Install the Type 11 Fuel Access Panels Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB, Panel 540BB 640 Access Panel 640AB, Panel 640BB Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-11-22, Page Block 401 (a) Make sure that the fuel tank is clean and clear of unwanted material, tools and other items of equipment.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 24 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (b) Install the access panels that follow (Refer to AMM 28-11-22, Page Block 401): 1 Install the access panel 540AB at manhole position No. 1 and access panel 540BB at manhole position No. 2 on the LH wing. 2 Install the access panel 640AB at manhole position No. 1 and access panel 640BB at manhole position No. 2 on the RH wing. D. TEST (1) Subtask 572097-790-402-001 - Leak Work Zones and Access Panels Zone Access/Work location 540 Work location Panel 540AB Panel 540BB 640 Work location Panel 640AB Panel 640BB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 28-25-00, Page Block 301 (a) Transfer sufficient fuel to the inner tanks (Refer to AMM 28-25-00, Page Block 301) or refuel the inner tanks (Refer to AMM 12-11-28, Page Block 301). (b) Inspect the access panels 540AB(640AB) and 540BB(640BB) for leaks. E. CLOSE-UP (1) Subtask 572097-942-402-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Make sure that the working area is clean and clear of all tools and other items of equipment. (b) Remove the access platform. (c) Remove all ground handling and maintenance equipment, standard and special tools, all access equipment and other items.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 25 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

RIB2 RIB10

EXISTING FUEL PANEL INSTALLATION (MANHOLE COVERS NO.1 AND NO.2) (5)

(6)

(7)

(4)

(3)
(2) Z540 (Z640)

MANHOLE POSITION NO.2 MANHOLE POSITION NO.1

B_SB_572097_7_BAAA_01_00 

### A

WING SKIN LH WING SHOWN RH WING SIMILAR



## A

Figure A-UBAAA - Sheet 01 Access Panel Type 21 DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 26 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL MANHOLE POSITION NO. 1 MANHOLE POSITION NO. 2 

### A

LOWER SKIN SURFACE 8 THREAD INSERT SKIN 9

8 11 12 10 

## A **A**

**B B**  ACCESS PANEL TYPE 11 WITH CLAMP PLATE TYPE 11A

SKIN PANEL CUT−OUT OUTBOARD RECESS FILLED VIEW ON UNDERSIDE OF WING RIB2



### B **B** 

## A 11 NO.1

NO.2 

### B



## B LH WING SHOWN RH WING SIMILAR

WITH AERODYNAMIC FILLER 

### C **D**

**C D**  RIB6 RING WING SEALING

APPLY A LIGHT DUSTING OF TALCUM POWDER TO SEALING 01 **NOTE:** RING BEFORE INSTALLATION OF ACCESS PANEL. 01

B_SB_572097_7_AAAA_01_04 

### A **A**

Figure A-UAAAA - Sheet 01 Access Panel Type 11 - Access Panel Type 11 with Clamp Plate Type 11A and Aerodynamic Filler DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 27 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL 

### BEFORE

**AFTER**

RIB 

## C

**D**

AREA OF MODIFICATION **NOTE:** 160° APPROX MASKING

TAPE PULL TAPE IN THIS DIRECTION PAINTED

LABEL ROLLER AREA



## C **C C**  **C**

B_SB_572097_7_AAAA_02_02 RIB TYPICAL FOR RIB 2 AND RIB 6

TYPICAL FOR RIB 2 AND RIB 6 RIB

Figure A-UAAAA - Sheet 02 Access Panel Type 11 - Access Panel Type 11 Skin Door Fastener Identification DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 28 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS STRUCTURE- FUELACCESS PANELS- INTRODUCTION OF REPLACEMENT PANELS (REPLACED TYPE 21 BY 11A) MODIFICATION No.: 13564H5728 13626H5742 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:

B - SB HAS BEEN embodied on aircraft: Operator comments:
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(s): 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.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN QUALITY PERCEPTION FORM 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 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - 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 Operator Supplied X Mod/Inspection X Manpower X Industry support 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 CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097 REVISION No.: 01 - Sep 29/11 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.