@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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS STRUCTURE- FUEL ACCESS 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

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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

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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

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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

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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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS STRUCTURE- FUEL ACCESS 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

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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

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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

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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

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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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS STRUCTURE- FUEL ACCESS 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

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@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

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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

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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

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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

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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

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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

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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 required

Anti-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

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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

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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

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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

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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

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(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-Corrosion

Primer (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

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SERVICE BULLETIN

or

External Top CoatWhite16-018 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

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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

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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 11A5735005100000 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

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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

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This Page Intentionally Left Blank

DATE: Apr 11/11 SERVICE BULLETIN No.: A310-57-2097

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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

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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

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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

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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

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Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

to the bare metal areas.

5 Apply

Anti-Corrosion

Primer (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

or

External Top CoatWhite16-018 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

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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

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@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

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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

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SERVICE BULLETIN

**CONF ALL

MANHOLE

POSITION

NO. 1

MANHOLE

POSITION

NO. 2

A

LOWER SKIN

SURFACE

8

THREAD

INSERT

9 SKIN

10 12 11 8

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

SEALING WING

01 APPLY A LIGHT DUSTING OF TALCUM POWDER TO SEALING

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

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**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

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@A310

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS STRUCTURE- FUEL ACCESS 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.