@A340

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 - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A340-57-4124

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to add the accomplishment timescale figures for A340-300 W000 series and to

improve the kits definition depending on the possible scenarios.

CHANGES

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER UPDATED R

APPENDICES APPENDICES UPDATED R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 1

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FSAAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FSAAB FIGURE SOLUTION ADDED N

Fig. A-FSAAB Sheet 01 SHEET ADDED N

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 005 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

CONFIGURATION UPDATED

MATERIAL SET QUANTITY UPDATED

MATERIAL SET UPDATED

R

MATERIAL EFFECTIVITY ADDED N

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 2

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL SET UPDATED

R

LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R

Kit 574124A01R05 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

R

Kit 574124A02R05 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 574124A03R04 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

PART NUMBER UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

R

Kit 574124A04R06 PART MATERIAL SET UPDATED

QUANTITY UPDATED

MATERIAL SET LABEL UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Kit 574124A05R05 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

QUANTITY UPDATED

R

Kit 574124A06R04 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

R

Kit 574124A08R00 PART MATERIAL SET ADDED N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 3

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

ACCOMPLISHMENT INSTRUCTIONS

TASK 574124- 832-801-001-Inspection TASK SOLUTION UPDATED

CAUTION UPDATED

NOTE UPDATED

R

Task associated data - 005 MAN HOURS UPDATED R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 4

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-110-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-832-005-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-006-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-008-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-011-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-012-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-005-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-006-002 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-008-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-011-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 5

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-832-012-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-005-003 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-006-003 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-008-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-011-003 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-012-003 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-005-004 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-006-004 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-007-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-008-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-011-004 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 6

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-832-012-004 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-001-001 SUBTASK SOLUTION UPDATED R

Subtask 574124-832-002-001 SUBTASK SOLUTION UPDATED R

Subtask 574124-832-005-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-006-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-007-003 SUBTASK SOLUTION ADDED N

Subtask 574124-832-008-003 SUBTASK SOLUTION ADDED N

Subtask 574124-832-007-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-832-008-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-832-011-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-012-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-009-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-010-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-011-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-832-012-005 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-001-002 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 7

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-700-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-001-003 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-001-004 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-001-005 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-001-007 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

TASK 574124- 833-801-001-Repair TASK SOLUTION UPDATED

NOTE UPDATED

R

Task associated data - 005 MAN HOURS UPDATED R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 8

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-941-003-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-001-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-002-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-003-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-004-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-007-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-009-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-010-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 9

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-011-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-012-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-017-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-018-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-019-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-020-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-023-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-001-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-002-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-003-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-004-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-007-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-009-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-010-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 10

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-011-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-012-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-017-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-018-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-019-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-020-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-023-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-001-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-002-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-003-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-004-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-007-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-009-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-010-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 11

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-011-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-012-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-017-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-018-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-019-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-020-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-023-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-003 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-001-004 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-002-004 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-003-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-004-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-007-004 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-004 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-009-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 12

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-010-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-011-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-012-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 574124-833-017-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-018-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-019-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-020-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-023-004 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-004 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-001-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-002-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-003-002 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 13

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-004-002 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-007-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-009-003 SUBTASK SOLUTION ADDED N

Subtask 574124-833-010-003 SUBTASK SOLUTION ADDED N

Subtask 574124-833-011-003 SUBTASK SOLUTION ADDED N

Subtask 574124-833-012-003 SUBTASK SOLUTION ADDED N

Subtask 574124-833-009-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-833-010-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-833-011-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-833-012-001 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 574124-833-017-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-018-002 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-019-002 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 574124-833-020-002 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 14

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-833-023-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-005-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-006-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

KEYWORD UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-007-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-008-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-021-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-022-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-023-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-833-024-005 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 574124-700-002-002 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 15

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574124-700-002-003 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-002-004 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-002-005 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-700-002-007 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Subtask 574124-942-002-001 SUBTASK SOLUTION UPDATED

REFERENCES UPDATED

PANEL UPDATED

REFERENCED DOCUMENTATION UPDATED

R

Fig. A-FCAAB

Fig. A-FCAAB Sheet 02 SHEET UPDATED R

Fig. A-FCAAA

Fig. A-FCAAA Sheet 02 SHEET UPDATED R

Fig. A-FCAAC

Fig. A-FCAAC Sheet 02 SHEET UPDATED R

Fig. A-FCAAD

Fig. A-FCAAD Sheet 02 SHEET UPDATED R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 16

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FCAAD Sheet 03 SHEET UPDATED R

Fig. A-FCAAF

Fig. A-FCAAF Sheet 01 SHEET UPDATED R

Fig. A-FCAAF Sheet 02 SHEET UPDATED R

Fig. A-FCBAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCBAB FIGURE SOLUTION ADDED N

Fig. A-FCBAB Sheet 01 SHEET ADDED N

Fig. A-FCBAB Sheet 02 SHEET ADDED N

Fig. A-FCCAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCCAA Sheet 01 SHEET UPDATED R

Fig. A-FCCAB FIGURE SOLUTION ADDED N

Fig. A-FCCAB Sheet 01 SHEET ADDED N

Fig. A-FCDAA FIGURE SOLUTION UPDATED

CONFIGURATION UPDATED

R

Fig. A-FCDAA Sheet 01 SHEET UPDATED R

Fig. A-FCDAB FIGURE SOLUTION ADDED N

Fig. A-FCDAB Sheet 01 SHEET ADDED N

Fig. A-FCEAA

Fig. A-FCEAA Sheet 01 SHEET UPDATED R

Fig. A-FRAAA FIGURE SOLUTION UPDATED R

Fig. A-FRAAA Sheet 02 SHEET UPDATED R

Fig. A-FRAAB FIGURE SOLUTION UPDATED R

Fig. A-FRAAB Sheet 02 SHEET UPDATED R

Fig. A-FRAAB Sheet 03 SHEET UPDATED R

APPENDIX APPENDIX DELETED D

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 04/13

REVISION No. : 01 - Aug 22/13

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 17

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 18

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@A340

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 - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT (Full Scale

Fatigue Test). Recently it appears necessary to modify this inspection due to the availability of in

service findings in the Frame 40 Rear Fitting. The latter were discovered thanks to the HF/EC Rototest

inspections done during the embodiment of the modification 52094S17923 through recommended

Service Bulletin No. A340-57-4090 which has pre-modification 44360S13013 and 44360S13482 and

post-modification 44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity.

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web - above

Center Wing Box lower panel, left and right sides for all A340 aircraft pre-modification 55306S18660

and 55792S18775 embodiments. The aim of this Inspection Service Bulletin is to implement the

corrective inspection necessary to the in-service aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair

Instruction R57115092, Inspection task of this ISB is not valid for the repaired side(s); dedicated RDAS

instructions have to be followed.

For aircraft previously inspected as per Technical Disposition ref. LR57D11029170, LR57D11023714,

LR57D11029172 or LR57D11030740, next inspection is due based on ISB 57-4124 interval value or

dedicated RDAS instruction requirements in case of deviation to the Technical Disposition instructions.

Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical web above Center

Wing Box lower panel, left and right sides and will contribute to maintain the structural integrity of the

area.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 1

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SERVICE BULLETIN

SUMMARY

The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and 44360S13482 , Pre

modification 55306S18660 and Pre modification 55792S18775 will be superseded by accomplishment

of Service Bulletin No. A340-57-4124.

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 LROPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A01R05 2 5,800.00 Screws, Washers, Nuts

Kit 574124A02R05 2 360.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 6,600.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A04R06 2 5,380.00 Screws, Washers, Nuts

Kit 574124A02R05 2 360.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 6,180.00

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A05R05 2 5,080.00 Screws, Washers, Nuts

Kit 574124A02R05 2 360.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 5,880.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 2

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A06R04 2 6,560.00 Screws, Washers, Nuts

Kit 574124A02R05 2 360.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 7,360.00

**CONF 005

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A08R00 2 4,600.00 Screws, Washers, Nuts

Kit 574124A02R05 2 360.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 5,400.00

**CONF 007

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574124A08R00 2 4,600.00 Screws, Washers, Nuts

Kit 574124A03R04 2 440.00 Screws, Washers, Nuts

TOTAL 5,040.00

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

15R 15T 56W 58X 83V ABD ABQ ACA AFR AIB ALK ARG CAL

CCA CPA DGA DLH FIN GAF GFA HFY I2L IBE IRC IRM KAC

LAN M3R MAU MDG MSR NMB PAL QAF RJA S3R SAA SAS SFB

SLM SWR TAP THT THY UAE VCV VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.007

OEB None

AOT None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 3

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@A340

SERVICE BULLETIN

SUMMARY

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT ref. 999.0086/11 and 999.0082/12

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 002

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 003

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 4

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 004

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 005

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 45.25

ELAPSED TIME (HOURS) 39.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 52.00

ELAPSED TIME (HOURS) 44.00

**CONF 007

Task 574124-832-801-001: Inspection

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

Task 574124-833-801-001: Repair

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

APPENDICES

**CONF ALL

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 5

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 001 thru 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

NOTE:

HOLE OF THE AREA A TO BE INSPECTED

A

HOLES OF THE AREA B TO BE INSPECTED

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

Z141 Z142 − 

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, B

A 260

24, 261, 262, 263

F_SB_574124_5_SAAA_01_03

Figure A-FSAAA - Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 6

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 005, 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

NOTE:

HOLE OF THE AREA A TO BE INSPECTED

A

HOLES OF THE AREA B TO BE INSPECTED

VIEW LOOKING AFT

Z141 Z142 − 

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, B

A 260

24, 261, 262, 263

STGR38

STGR39

STGR40

STGR37

CENTER WING BOX LOWER PANEL REFERENCE

H260 H263

H262

H23 H14

H21 H13 H12

H24

H22

H261

F_SB_574124_5_SAAB_01_00

Figure A-FSAAB - Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 7

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@A340

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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 - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

MODIFICATION No.: None

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

NOTE: This Service Bulletin is applicable only to aircraft on which Mod. No.

55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN

ANGLE AT FR.40 (ADAPTATION SOLUTION)) and Mod. No. 55792S18775

(REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) are not embodied.

(1) Models

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002 0004-0006 0009 0011 0013-0014 0018-0020 0022-0029 0031-0035 0038 0041

0043-0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081

0084-0085 0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128

0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164

0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199

0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233

0236-0237 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274

0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 1

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@A340

SERVICE BULLETIN

0331-0332 0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381

0385 0387 0390 0395 0399 0402 0406 0411 0413-0415 0424 0429-0430 0433-0435

0438 0442 0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546

0554 0556 0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800

(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

15R 0151

15T 0009

56W 0011 0013 0018 0019

58X 0004

83V 0280 0292

ABD 0210

ABQ 0216 0257

ACA 0170

AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377

0399

AIB 0131 0141 0161 0182

ALK 0032 0033 0034 0367 0374 0381

ARG 0048 0063 0074 0080 0085 0093 0094 0123 0126 0128 0373

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0024 0027 0028 0035 0052 0053 0135 0158 0213 0233 0252 0297

0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447

FIN 0058 0168 0174

GAF 0274 0355

GFA 0212 0215 0282 0554

HFY 0117 0133 0190 0202

I2L 0005

IBE 0088 0125 0134 0145 0146 0193 0217 0221 0329 0387 0414 0459

0474 0483

IRC 0002

IRM 0020 0056

KAC 0089 0090 0101 0104

LAN 0359 0363 0429 0442

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MDG 0319

MSR 0156 0159 0178

NMB 0047 0051

PAL 0173 0176 0187 0196 0302 0318 0332

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 2

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@A340

SERVICE BULLETIN

OPERATOR MSN

QAF 0026 0528

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0167 0413 0424 0430 0435 0450 0467 0470

SFB 0046

SLM 0049

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0270 0331

UAE 0139 0149 0163 0166 0185 0236

VCV 0031

VIR 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0004 0005 0006 0009 0011 0013 0014 0018 0019 0020

0022 0023 0024 0025 0026 0027 0028 0029 0031 0032 0033

0034 0035 0038 0041 0043 0044 0046 0047 0048 0049 0051

0052 0053 0056 0057 0058 0061 0063 0074 0075 0076 0078

0079 0080 0081 0084 0085 0088 0089 0090 0091 0093 0094

0101 0104

001

0114 0115 0125 0134 002

0117 0123 0126 0128 0131 0133 0135 0136 0137 0139 0141

0142 0145 0146 0147 0149 0150 0151 0152 0154 0156

004

0157 0158 0159 0160 0161 0163 0164 0166 0167 0168 0169

0170 0173 0174 0175

003

0176 0178 0179 0180 0182 0185 0186 0187 0190 0192 0193

0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212

0213 0214 0215 0216 0217 0218 0220 0221 0225 0227 0228

0233 0236 0237 0242 0243 0245 0246 0252 0257 0260 0263

0264 0268 0270 0273 0274 0278 0280 0282 0292 0297 0302

0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332

0335 0347 0352 0354 0355 0359 0363 0367 0373 0374 0377

0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411

0413 0414 0415 0424 0429 0430 0433 0434 0435 0438 0442

0446 0447 0450 0459 0467 0470 0474 0483

005

0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562

0582 0585 0590 0598 0643 0646 0651 0668 0793 0800

007

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 3

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@A340

SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT

SPAR (SERIAL SOLUTION)) are not embodied and on which Service Bulletin No.

A340-57-4036 is accomplished (or Mod No. 43577S12677 (MODIFY LOWER KEEL

FITTING AND FORWARD LOWER SHELL CONNECT.(RETROFIT SOLUTION VIA SB

ONLY)) is embodied).

**CONF 002

Config. 002 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Service

Bulletin No. A340-57-4058 is accomplished (or Mod No. 44440S13324 (REINFORCE

KEEL ANGLE OF FRONT SPAR (RETROFIT SOLUTION)) and Mod No. 41652S11819

(INTRODUCE A340 COMMONALITY ITEMS) are embodied.

**CONF 003

Config. 003 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No.

44440S13090 (MODIFY LOWER KEEL FITTING AND FWD LOWER SHELL

CONNECTION (SERIAL SOLUTION)) and Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) are embodied.

**CONF 004

Config. 004 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No.

44440S13276 (REINFORCE LOWER KEEL ANGLE OF FRONT SPAR (ADAPTATION

SOLUTION)) and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS)

are embodied.

**CONF 005

Config. 005 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) and Mod No. 41652S11819 (INTRODUCE

A340 COMMONALITY ITEMS) are embodied and on which Mod No. 49202S16307

(REINFORCE SECTION 15/21) is not embodied.

**CONF 007

Config. 007 is valid for aircraft on which Mod No. 44360S13482 (MODIFY FR40 AND

FRONT SPAR (SERIAL SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) and Mod No. 49202S16307 (REINFORCE SECTION 15/21)

are embodied and on which Mod No. 55306S18660 (REPLACE THE ONE-PIECE

FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and

Mod No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIES AIRCRAFT)) are

not embodied.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 4

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@A340

SERVICE BULLETIN

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A01R05 2

Kit 574124A02R05 2

Kit 574124A03R04 2

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A04R06 2

Kit 574124A02R05 2

Kit 574124A03R04 2

Consumable CMLA01 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A05R05 2

Kit 574124A02R05 2

Kit 574124A03R04 2

Consumable CMLA01 1

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A06R04 2

Kit 574124A02R05 2

Kit 574124A03R04 2

Consumable CMLA01 1

**CONF 005

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A08R00 2

Kit 574124A02R05 2

Kit 574124A03R04 2

Consumable CMLA01 1

**CONF 007

MATERIAL QTY PER A/C SEE NOTES

Kit 574124A08R00 2

Kit 574124A03R04 2

Consumable CMLA01 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 5

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@A340

SERVICE BULLETIN

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT

(Full Scale Fatigue Test). Recently it appears necessary to modify this inspection due to

the availability of in service findings in the Frame 40 Rear Fitting. The latter were

discovered thanks to the HF/EC Rototest inspections done during the embodiment of the

modification 52094S17923 through recommended Service Bulletin No. A340-57-4090

which has pre-modification 44360S13013 and 44360S13482 and post-modification

44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity.

(2) Objective/Action

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40

Vertical Web - above Center Wing Box lower panel, left and right sides for all A340

aircraft pre-modification 55306S18660 and 55792S18775 embodiments. The aim of this

Inspection Service Bulletin is to implement the corrective inspection necessary to the inservice aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per

Repair Instruction R57115092, Inspection task of this ISB is not valid for the repaired

side(s); dedicated RDAS instructions have to be followed.

For aircraft previously inspected as per Technical Disposition ref. LR57D11029170,

LR57D11023714, LR57D11029172 or LR57D11030740, next inspection is due based

on ISB 57-4124 interval value or dedicated RDAS instruction requirements in case of

deviation to the Technical Disposition instructions.

(3) Advantages

Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical

web above Center Wing Box lower panel, left and right sides and will contribute to

maintain the structural integrity of the area.

(4) Operational/Maintenance Consequences

The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and

44360S13482 , Pre modification 55306S18660 and Pre modification 55792S18775 will

be superseded by accomplishment of Service Bulletin No. A340-57-4124.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 6

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@A340

SERVICE BULLETIN

**CONF 001

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 7

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@A340

SERVICE BULLETIN

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 002

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 8

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@A340

SERVICE BULLETIN

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 9

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@A340

SERVICE BULLETIN

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 003

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 10

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@A340

SERVICE BULLETIN

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 004

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 11

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@A340

SERVICE BULLETIN

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 12

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@A340

SERVICE BULLETIN

(15) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 005

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 13

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@A340

SERVICE BULLETIN

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A340-57-4090 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 007

Task 574124-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 14

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Side

(5) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(8) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574124-833-801-001: Repair

(1) Install New same Fastener of the Area A in transition fit, LH Side

(2) Install New same Fastener of the Area A in transition fit, RH Side

(3) Install New same Fasteners of the Area B in transition fit, LH Side

(4) Install New same Fasteners of the Area B in transition fit, RH Side

(5) Oversize the Hole of the Area A to First Oversize in comparison with the current hole

diameter, LH Side

(6) Oversize the Hole of the Area A to First Oversize in comparison with the current hole

diameter, RH Side

(7) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(8) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(9) Install New Fastener of the Area A in transition fit, LH Side

(10) Install New Fastener of the Area A in transition fit, RH Side

(11) Install New Fasteners of the Area B in transition fit, LH Side

(12) Install New Fasteners of the Area B in transition fit, RH Side

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 15

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(2) Accomplishment Timescale

**CONF 001

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Do a Rototest

Inspection Pre SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-005

001 for LH Side

and to SUBTASK

574124-832-006

001 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 001 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Config. 001 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 16

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 001 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

002 for LH Side

and to SUBTASK

574124-832-012

002 for RH Side

Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 001 Pre

Service Bulletin

No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-005

001 for LH Side

and to

SUBTASK

574124-832-006

001 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 17

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Pre SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-001

002 for LH Side

and/or to

SUBTASK

574124-833-002

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

001 for LH Side

and/or to

SUBTASK

574124-832-006

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

Or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 18

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

No crack found A340-200 None None

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Pre SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-009

001 for LH Side

and/or to

SUBTASK

574124-833-010

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 19

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 20

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Pre

SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-017

001 for LH Side

and/or to

SUBTASK

574124-833-018

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

002 for LH Side

and/or to

SUBTASK

574124-832-006

002 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 21

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 31,800

FC/127,300 FH

or

FH optimized

set: 24,800

FC/167,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 27,800

FC/111,400 FH

or

FH optimized

set: 21,700

FC/146,700 FH

See NOTE (*)

Config. 001

Post Service

Bulletin No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and to

SUBTASK

574124-832-008

001 for RH

Side

FC optimized

set: 26,100

FC/104,700 FH

or

FH optimized

set: 20,400

FC/137,900 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 22

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Post SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-003

001 for LH Side

and/or to

SUBTASK

574124-833-004

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 23

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Post SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-011

001 for LH Side

and/or to

SUBTASK

574124-833-012

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 24

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Post

SB 57-4090 in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-019

001 for LH Side

and/or to

SUBTASK

574124-833-020

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 25

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 001

A340-300,

WV020 Serie

Do a Rototest

Inspection of

the Holes on

LH and RH

Side, refer to

SUBTASK

574124-832-011

002 for LH Side

and to

SUBTASK

574124-832-012

002 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 26

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-007

002 for LH Side

and/or to

SUBTASK

574124-833-008

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Side, refer to

SUBTASK

574124-832-011

002 for LH Side

and/or to

SUBTASK

574124-832-012

002 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 27

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300,

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Holes to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-015

002 for LH Side

and/or to

SUBTASK

574124-833-016

002 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 28

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-023

002 for LH Side

and/or to

SUBTASK

574124-833-024

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Side, refer to

SUBTASK

574124-832-011

002 for LH Side

and/or to

SUBTASK

574124-832-012

002 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 29

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 002

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Do a Rototest

Inspection Pre SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-005

002 for LH Side

and to SUBTASK

574124-832-006

002 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 002 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 30

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 002 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 002 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

001 for LH Side

and to SUBTASK

574124-832-012

001 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 31

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 002 Pre

Service Bulletin

No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-005

002 for LH Side

and to

SUBTASK

574124-832-006

002 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 32

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Pre SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-001

001 for LH Side

and/or to

SUBTASK

574124-833-002

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

002 for LH Side

and/or to

SUBTASK

574124-832-006

002 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

Or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 33

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

No crack found A340-200 None None

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Pre SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-009

001 for LH Side

and/or to

SUBTASK

574124-833-010

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 34

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 35

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000

Serieand

A340-300

WV020 Serie

Install New

Fastener Pre

SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-017

001 for LH Side

and/or to

SUBTASK

574124-833-018

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

002 for LH Side

and/or to

SUBTASK

574124-832-006

002 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 36

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 31,800

FC/127,300 FH

or

FH optimized

set: 24,800

FC/167,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 27,800

FC/111,400 FH

or

FH optimized

set: 21,700

FC/146,700 FH

See NOTE (*)

Config. 002

Post Service

Bulletin No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and to

SUBTASK

574124-832-008

001 for RH

Side

FC optimized

set: 26,100

FC/104,700 FH

or

FH optimized

set: 20,400

FC/137,900 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 37

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Post SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-003

001 for LH Side

and/or to

SUBTASK

574124-833-004

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 38

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Post SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-011

001 for LH Side

and/or to

SUBTASK

574124-833-012

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 39

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Post

SB 57-4090 in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-019

001 for LH Side

and/or to

SUBTASK

574124-833-020

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 40

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 002

A340-300,

WV020 Serie

Do a Rototest

Inspection of

the Holes on

LH and RH

Side, refer to

SUBTASK

574124-832-011

001 for LH Side

and to

SUBTASK

574124-832-012

001 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 41

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 and

A340-300

WV020 Serie

Install New

same

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-007

001 for LH Side

and/or to

SUBTASK

574124-833-008

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Side, refer to

SUBTASK

574124-832-011

001 for LH Side

and/or to

SUBTASK

574124-832-012

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 42

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Holes to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-015

001 for LH Side

and/or to

SUBTASK

574124-833-016

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 43

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-023

001 for LH Side

and/or to

SUBTASK

574124-833-024

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Side, refer to

SUBTASK

574124-832-011

001 for LH Side

and/or to

SUBTASK

574124-832-012

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 44

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 003

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Do a Rototest

Inspection Pre SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-005

003 for LH Side

and to SUBTASK

574124-832-006

003 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 003 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 45

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 003 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 003 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

003 for LH Side

and to SUBTASK

574124-832-012

003 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 46

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 003 Pre

Service Bulletin

No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-005

003 for LH Side

and to

SUBTASK

574124-832-006

003 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 47

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Pre SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-001

003 for LH Side

and/or to

SUBTASK

574124-833-002

003 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

003 for LH Side

and/or to

SUBTASK

574124-832-006

003 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

Or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 48

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

No crack found A340-200 None None

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Pre SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-009

001 for LH Side

and/or to

SUBTASK

574124-833-010

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 49

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 50

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Pre

SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-017

001 for LH Side

and/or to

SUBTASK

574124-833-018

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

003 for LH Side

and/or to

SUBTASK

574124-832-006

003 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 51

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 31,800

FC/127,300 FH

or

FH optimized

set: 24,800

FC/167,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 27,800

FC/111,400 FH

or

FH optimized

set: 21,700

FC/146,700 FH

See NOTE (*)

Config. 003

Post Service

Bulletin No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and to

SUBTASK

574124-832-008

001 for RH

Side

FC optimized

set: 26,100

FC/104,700 FH

or

FH optimized

set: 20,400

FC/137,900 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 52

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Post SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-003

001 for LH Side

and/or to

SUBTASK

574124-833-004

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 53

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Post SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-011

001 for LH Side

and/or to

SUBTASK

574124-833-012

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 54

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Post

SB 57-4090 in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-019

001 for LH Side

and/or to

SUBTASK

574124-833-020

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 55

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 003

A340-300,

WV020 Serie

Do a Rototest

Inspection of

the Holes on

LH and RH

Side, refer to

SUBTASK

574124-832-011

003 for LH Side

and to

SUBTASK

574124-832-012

003 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 56

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-007

003 for LH Side

and/or to

SUBTASK

574124-833-008

003 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Side, refer to

SUBTASK

574124-832-011

003 for LH Side

and/or to

SUBTASK

574124-832-012

003 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 57

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Holes to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-015

003 for LH Side

and/or to

SUBTASK

574124-833-016

003 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 58

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-023

003 for LH Side

and/or to

SUBTASK

574124-833-024

003 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Side, refer to

SUBTASK

574124-832-011

003 for LH Side

and/or to

SUBTASK

574124-832-012

003 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 59

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 004

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Do a Rototest

Inspection Pre SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-005

004 for LH Side

and to SUBTASK

574124-832-006

004 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 004 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 60

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 004 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

001 for LH Side

and to SUBTASK

574124-832-008

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 004 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

004 for LH Side

and to SUBTASK

574124-832-012

004 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 61

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 004 Pre

Service Bulletin

No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-005

004 for LH Side

and to

SUBTASK

574124-832-006

004 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 62

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Pre SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-001

004 for LH Side

and/or to

SUBTASK

574124-833-002

004 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

004 for LH Side

and/or to

SUBTASK

574124-832-006

004 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

Or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 63

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

No crack found A340-200 None None

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Pre SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-009

001 for LH Side

and/or to

SUBTASK

574124-833-010

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 64

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 65

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 and

A340-300

WV020 Serie

Install New

Fastener Pre

SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-017

001 for LH Side

and/or to

SUBTASK

574124-833-018

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

004 for LH Side

and/or to

SUBTASK

574124-832-006

004 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 66

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 31,800

FC/127,300 FH

or

FH optimized

set: 24,800

FC/167,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 27,800

FC/111,400 FH

or

FH optimized

set: 21,700

FC/146,700 FH

See NOTE (*)

Config. 004

Post Service

Bulletin No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and to

SUBTASK

574124-832-008

001 for RH

Side

FC optimized

set: 26,100

FC/104,700 FH

or

FH optimized

set: 20,400

FC/137,900 FH

See NOTE (*)

1,300 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 67

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Post SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-003

001 for LH Side

and/or to

SUBTASK

574124-833-004

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 68

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Post SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-011

001 for LH Side

and/or to

SUBTASK

574124-833-012

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 69

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Post

SB 57-4090 in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-019

001 for LH Side

and/or to

SUBTASK

574124-833-020

001 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

001 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 70

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 20,200

FC/80,900 FH

or

FH optimized

set: 16,100

FC/108,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 17,700

FC/70,800 FH

or

FH optimized

set: 14,100

FC/95,200 FH

See NOTE (*)

Config. 004

A340-300,

WV020 Serie

Do a Rototest

Inspection of

the Holes on

LH and RH

Side, refer to

SUBTASK

574124-832-011

004 for LH Side

and to

SUBTASK

574124-832-012

004 for RH

Side

FC optimized

set: 16,600

FC/66,600 FH

or

FH optimized

set: 13,200

FC/89,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 71

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fasteners

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-007

004 for LH Side

and/or to

SUBTASK

574124-833-008

004 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Side, refer to

SUBTASK

574124-832-011

004 for LH Side

and/or to

SUBTASK

574124-832-012

004 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 72

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Holes to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-015

004 or LH Side

and/or to

SUBTASK

574124-833-016

004 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 73

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-023

004 for LH Side

and/or to

SUBTASK

574124-833-024

004 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 13,300

FC/53,200 FH

or

FH optimized

set: 11,000

FC/74,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 11,600

FC/46,500 FH

or

FH optimized

set: 9,700

FC/65,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH Side,

refer to

SUBTASK

574124-832-011

004 for LH Side

and/or to

SUBTASK

574124-832-012

004 for RH

Side

None None

FC optimized

set: 10,900

FC/43,700 FH

or

FH optimized

set: 9,100

FC/61,500 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 74

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 005

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Do a Rototest

Inspection Pre SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-005

005 for LH Side

and to SUBTASK

574124-832-006

005 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 005 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

003 for LH Side

and to SUBTASK

574124-832-008

003 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 75

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 005 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

of the Hole on LH

and RH Side, refer

to SUBTASK

574124-832-007

003 for LH Side

and to SUBTASK

574124-832-008

003 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 005 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

005 for LH Side

and to SUBTASK

574124-832-012

005 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 76

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 19,000

FC/76,100 FH

or

FH optimized

set: 15,100

FC/102,000 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 16,600

FC/66,500 FH

or

FH optimized

set: 13,200

FC/89,200 FH

See NOTE (*)

Config. 005 Pre

Service Bulletin

No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-005

005 for LH Side

and to

SUBTASK

574124-832-006

005 for RH

Side

FC optimized

set: 15,600

FC/62,500 FH

or

FH optimized

set: 12,400

FC/83,800 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 77

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Pre SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-001

005 for LH Side

and/or to

SUBTASK

574124-833-002

005 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

005 for LH Side

and/or to

SUBTASK

574124-832-006

005 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

Or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 78

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

No crack found None None

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

003 for LH Side

and/or to

SUBTASK

574124-832-008

003 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A340-57-4090 embodiment

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Pre SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-009

003 for LH Side

and/or to

SUBTASK

574124-833-010

003 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 79

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 80

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Pre

SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-017

002 for LH Side

and/or to

SUBTASK

574124-833-018

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Pre

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-005

005 for LH Side

and/or to

SUBTASK

574124-832-006

005 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 81

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 30,600

FC/122,400 FH

or

FH optimized

set: 23,800

FC/160,800 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 26,700

FC/107,100 FH

or

FH optimized

set: 20,800

FC/140,700 FH

See NOTE (*)

Config. 005

Post Service

Bulletin No.

A340-57-4090

A340-300,

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and RH

Side, refer to

SUBTASK

574124-832-007

003 for LH Side

and to

SUBTASK

574124-832-008

003 for RH

Side

FC optimized

set: 25,100

FC/100,700 FH

or

FH optimized

set: 19,600

FC/132,300 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 82

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same Fastener

Post SB No.

A340-57-4090

in transition fit

on LH and/or

RH Side, refer

to SUBTASK

574124-833-003

002 for LH Side

and/or to

SUBTASK

574124-833-004

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

003 for LH Side

and/or to

SUBTASK

574124-832-008

003 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 83

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Hole Post SB

No.

A340-57-4090

to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-011

003 for LH Side

and/or to

SUBTASK

574124-833-012

003 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 84

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fastener Post

SB 57-4124 in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-019

002 for LH Side

and/or to

SUBTASK

574124-833-020

002 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection Post

SB No.

A340-57-4090

of the Hole on

LH and/or RH

Side, refer to

SUBTASK

574124-832-007

003 for LH Side

and/or to

SUBTASK

574124-832-008

001 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 85

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

SB

A340-57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200,

WV000 Serie

FC optimized

set: 19,000

FC/76,100 FH

or

FH optimized

set: 15,100

FC/102,000 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 16,600

FC/66,500 FH

or

FH optimized

set: 13,200

FC/89,200 FH

See NOTE (*)

Config. 005

A340-300,

WV020 Serie

Do a Rototest

Inspection of

the Holes on

LH and RH

Side, refer to

SUBTASK

574124-832-011

005 for LH Side

and to

SUBTASK

574124-832-012

005 for RH

Side

FC optimized

set: 15,600

FC/62,500 FH

or

FH optimized

set: 12,400

FC/83,800 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 86

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

same

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-007

005 for LH Side

and/or to

SUBTASK

574124-833-008

005 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No crack found

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Side, refer to

SUBTASK

574124-832-011

005 for LH Side

and/or to

SUBTASK

574124-832-012

005 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 87

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Oversize the

Holes to First

Oversize in

comparison

with current

hole diameter

on LH and/or

RH Side, refer

to SUBTASK

574124-833-015

005 for LH Side

and/or to

SUBTASK

574124-833-016

005 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 88

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

A340-200

WV000 Serie,

A340-300

WV000 Serie

and A340-300

WV020 Serie

Install New

Fasteners in

transition fit on

LH and/or RH

Side, refer to

SUBTASK

574124-833-023

005 for LH Side

and/or to

SUBTASK

574124-833-024

005 for RH

Side

and

Before next

flight

None None

A340-200,

WV000 Serie

FC optimized

set: 10,400

FC/41,800 FH

or

FH optimized

set: 8,700

FC/58,700 FH

See NOTE (*)

A340-300,

WV000 Serie

FC optimized

set: 9,100

FC/36,500 FH

or

FH optimized

set: 7,600

FC/51,400 FH

See NOTE (*)

No Crack found

after rototest

inspection

A340-300,

WV020 Serie

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Side, refer to

SUBTASK

574124-832-011

005 for LH Side

and/or to

SUBTASK

574124-832-012

005 for RH

Side

None None

FC optimized

set: 8,550

FC/34,300 FH

or

FH optimized

set: 7,150

FC/48,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 89

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 007

Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH

Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 007 Do a Rototest

Inspection of the

Hole on LH and

RH Side, refer to

SUBTASK

574124-832-001

002 for LH Side

and to SUBTASK

574124-832-002

002 for RH Side

Refer to Table 3

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and

RH Side

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 007 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-003

006 for LH Side

and to SUBTASK

574124-832-004

006 for RH Side

Refer to Table 4

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 90

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 007 Do a Rototest

Inspection of the

Hole on LH and

RH Side, refer to

SUBTASK

574124-832-009

001 for LH Side

and to SUBTASK

574124-832-010

001 for RH Side

FC optimized set:

25,100 FC/100,700

FH

or

FH optimized set:

19,600 FC/132,300

FH

See NOTE (*)

1,300 FC or 24

months from SB

issuance date

None

Install New same

Fastener in

transition fit on LH

and/or RH Side,

refer to SUBTASK

574124-833-005

001 for LH Side

and/or to

SUBTASK

574124-833-006

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Hole on LH

and/or RH Side,

refer to SUBTASK

574124-832-009

001 for LH Side

and/or to

SUBTASK

574124-832-010

001 for RH Side

None None FC optimized set:

8,550 FC/34,300

FH

or

FH optimized set:

7,150 FC/48,300

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 91

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Crack found Oversize the Hole

to First Oversize in

comparison with

current hole

diameter on LH

and/or RH Side,

refer to SUBTASK

574124-833-013

001 for LH Side

and/or to

SUBTASK

574124-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fastener in

transition fit on LH

and/or RH Side,

refer to SUBTASK

574124-833-021

001 for LH Side

and/or to

SUBTASK

574124-833-022

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Hole on LH

and/or RH Side,

refer to SUBTASK

574124-832-009

001 for LH Side

and/or to

SUBTASK

574124-832-010

001 for RH Side

None None FC optimized set:

8,550 FC/34,300

FH

or

FH optimized set:

7,150 FC/48,300

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 92

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Config. 007 Do a Rototest

Inspection of the

Holes on LH and

RH Side, refer to

SUBTASK

574124-832-011

005 for LH Side

and to SUBTASK

574124-832-012

005 for RH Side

FC optimized set:

15,600 FC/62,500

FH

or

FH optimized set:

12,400 FC/ 83,800

FH

See NOTE (*)

1,300 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Side,

refer to SUBTASK

574124-833-007

005 for LH Side

and/or to

SUBTASK

574124-833-008

005 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Side,

refer to SUBTASK

574124-832-011

005 for LH Side

and/or to

SUBTASK

574124-832-012

005 for RH Side

None None FC optimized set:

8,550 FC/34,300

FH

or

FH optimized set:

7,150 FC/48,300

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 93

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Crack found Oversize the Holes

to First Oversize in

comparison with

current hole

diameter on LH

and/or RH Side,

refer to SUBTASK

574124-833-015

005 for LH Side

and/or to

SUBTASK

574124-833-016

005 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Side,

refer to SUBTASK

574124-833-023

005 for LH Side

and/or to

SUBTASK

574124-833-024

005 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes on LH

and/or RH Side,

refer to SUBTASK

574124-832-011

005 for LH Side

and/or to

SUBTASK

574124-832-012

005 for RH Side

None None FC optimized set:

8,550 FC/34,300

FH

or

FH optimized set:

7,150 FC/48,300

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A340 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 94

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF ALL

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 574124-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 95

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-832-801-001: Inspection

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 96

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

**CONF 002

Task 574124-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 97

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-832-801-001: Inspection

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 98

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

**CONF 003

Task 574124-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 99

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-832-801-001: Inspection

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 100

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

**CONF 004

Task 574124-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 101

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-832-801-001: Inspection

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 102

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

**CONF 005

Task 574124-832-801-001: Inspection

Get Access 12.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 103

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@A340

SERVICE BULLETIN

Task 574124-832-801-001: Inspection

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, LH Side

6.50

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame

40, RH Side

0.75

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 45.25

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 104

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@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

1.00

Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.75

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, LH Side

6.50

Oversize the Hole of the Area A Post Service Bulletin

No. A340-57-4090 to First Oversize in comparison with

the current hole diameter, RH Side

0.75

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 52.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 105

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@A340

SERVICE BULLETIN

**CONF 007

Task 574124-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection of the Hole of the Area A of

the Frame 40, LH Side

0.50

Do a Rototest Inspection of the Hole of the Area A of

the Frame 40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574124-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener of the Area A in transition

fit, LH Side

0.25

Install New same Fastener of the Area A in transition

fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 106

5

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@A340

SERVICE BULLETIN

Task 574124-833-801-001: Repair

Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener of the Area A in transition fit, LH

Side

0.25

Install New Fastener of the Area A in transition fit, RH

Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

NOTE: For Area A, if Service Bulletin No.A340-57-4090 is accomplished, only the

manhours stating post Service Bulletin No.A340-57-4090 apply.

For Area A, if Service Bulletin No.A340-57-4090 is not accomplished, only the

manhours stating pre Service Bulletin No.A340-57-4090 apply.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 107

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@A340

SERVICE BULLETIN

Service Bulletin (SB) A340-57-4090

A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 002

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 003

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 004

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 108

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@A340

SERVICE BULLETIN

Service Bulletin (SB) A340-57-4090

A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 005

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 007

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-25-00 36-22-19

52-30-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF ALL

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Airworthiness Limitation Section

(ALS) Part 2

Maintenance Planning Document (MPD) 571102

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 109

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@A340

SERVICE BULLETIN

M. SPARES

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 110

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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 574124A01R05

Kit 574124A02R05

Kit 574124A03R04

Kit 574124A04R06

Kit 574124A05R05

Kit 574124A06R04

Kit 574124A08R00

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 574124A01R05

Cost 2,900.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A02R05

Cost 180.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A03R04

Cost 220.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A04R06

Cost 2,690.00 USD

Availability 90 calendar days from receipt of order

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 111

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SERVICE BULLETIN

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A05R05

Cost 2,540.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A06R04

Cost 3,280.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 574124A08R00

Cost 2,300.00 USD

Availability 90 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

B. INDUSTRY SUPPORT INFORMATION

This Service Bulletin is subject to a specific support provided by AIRBUS. For more details

regarding the applicable commercial policy, please contact your Customer Support Director.

C. LIST OF COMPONENTS

Kit 574124A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

4 EN6115V6-18 1 SCREW

5 EN6115V6X18 1 SCREW

6 EN6115V6-20 4 SCREW

7 EN6115V6X20 4 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 112

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

91 EN6115-5X18 1 SCREW

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.

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

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.

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

94 EN6115V7-16 1 SCREW

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.

Kit 574124A04R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

4 EN6115V6-18 1 SCREW

5 EN6115V6X18 1 SCREW

6 EN6115V6-20 4 SCREW

7 EN6115V6X20 4 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 113

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

53 MS21250-07018 1 SCREW

54 NSA5399-6-16A 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

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.

Kit 574124A05R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

4 EN6115V6-18 1 SCREW

5 EN6115V6X18 1 SCREW

6 EN6115V6-20 4 SCREW

7 EN6115V6X20 4 SCREW

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 2 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

88 EN6115-5-19 1 SCREW

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.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 114

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@A340

SERVICE BULLETIN

Kit 574124A06R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

4 EN6115V6-18 1 SCREW

5 EN6115V6X18 1 SCREW

6 EN6115V6-20 4 SCREW

7 EN6115V6X20 4 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

57 EN6115-5Y18 1 SCREW

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

85 MS21250-07023 1 SCREW

86 NSA5399-6-25A 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

91 EN6115-5X18 1 SCREW

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.

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

65 NSA5398-6-18A 1 SCREW

73 EN6115V5-20 1 SCREW

74 EN6115V5X20 1 SCREW

75 EN6115V6-24 4 SCREW

76 EN6115V6X24 4 SCREW

91 EN6115V6-19 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

92 EN6115V6X19 1 SCREW

93 EN6115V6-22 1 SCREW

95 EN6115V6X22 1 SCREW

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 CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

NOTE: To accomplish this Service Bulletin it is necessary to use the expendable

parts listed in the AMM Task 21-52-41-400-801 mentioned in paragraph

close-up.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed

in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-up

and in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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(3) Special Tools

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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This Page Intentionally Left Blank

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 574124-832-801-001 - Inspection

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

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.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The purpose of flow charts are for information only to show the various

Inspection/Repair phases described in this Service Bulletin.

Task Associated Data

**CONF 001

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 002

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 003

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 004

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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**CONF 005

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 45.25

ELAPSED TIME (HOURS) 39.00

**CONF 007

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

**CONF ALL

A. GENERAL

CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft

under zero stress jacking. No zero stress jacking is required also in case of

concurrent accomplishment of maintenance tasks or SBs in frame 40 area.

However this is applicable only for the accomplishment of these tasks/SBs

without deviation. Indeed, in case of heavy repair, a temporary re-installation

of fasteners and/or zero stress jacking procedure could be anticipated.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF 001

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 574124-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 574124-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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(2) Subtask 574124-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 004

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 574124-839-001-001 - 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 04/13 SERVICE BULLETIN No.: A340-57-4124

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**CONF 005

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 574124-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 007

(1) Subtask 574124-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 574124-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

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(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

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(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

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(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 002

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 132

5

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@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 133

5

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@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 134

5

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@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 135

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 003

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 136

5

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 137

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 138

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 139

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 140

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 004

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 141

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 142

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 143

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 144

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 145

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 005

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 146

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 147

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@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 148

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@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 149

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@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 150

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@A340

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 007

(1) Subtask 574124-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 151

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 152

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@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 153

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@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 154

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@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 574124-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous Cleaner--

Trichloroethane Legacy

08BBU9 As required

Textile-Lint Free Cotton 14SBA1 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 155

5

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@A340

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

Non Aqueous

Cleaner--

Trichloroethane

Legacy

08BBU9 As required

and (if necessary)

Textile-Lint Free

Cotton

14SBA1 As required

(8) Subtask 574124-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 156

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@A340

SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 574124-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-005 001 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 157

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@A340

SERVICE BULLETIN

(2) Subtask 574124-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-006 001 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(3) Subtask 574124-832-003-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 158

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-011 002 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-012 002 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 574124-832-005-001 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 159

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-001 002 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 160

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-005 001 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-009 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-017 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 001 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(6) Subtask 574124-832-006-001 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 161

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-002 002 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 162

5

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-006 001 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-010 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-018 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 001 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(7) Subtask 574124-832-007-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 163

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-003 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 164

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-011 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-019 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(8) Subtask 574124-832-008-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 165

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-004 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 166

5

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@A340

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-012 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-020 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(9) Subtask 574124-832-011-002 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 167

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (56) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (59) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (50) Discard

1 Washer Item (58) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 168

5

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@A340

SERVICE BULLETIN

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 002 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 002 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-015 002 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 002 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 002 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(10) Subtask 574124-832-012-002 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 169

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (56) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 170

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (59) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (50) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 002 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 002 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-016 002 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 002 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 171

5

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-012 002 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

**CONF 002

(1) Subtask 574124-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-005 002 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 172

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(2) Subtask 574124-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-006 002 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 173

5

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@A340

SERVICE BULLETIN

(3) Subtask 574124-832-003-002 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-011 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-002 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-012 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 174

5

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@A340

SERVICE BULLETIN

(5) Subtask 574124-832-005-002 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 175

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-001 001 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 002 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-009 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-017 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 002 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 176

5

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@A340

SERVICE BULLETIN

(6) Subtask 574124-832-006-002 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 177

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-002 001 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 002 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-010 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-018 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 002 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 178

5

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@A340

SERVICE BULLETIN

(7) Subtask 574124-832-007-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 179

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-003 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-011 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-019 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(8) Subtask 574124-832-008-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 180

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-004 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 181

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-012 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-020 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(9) Subtask 574124-832-011-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 182

5

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@A340

SERVICE BULLETIN

References

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (8) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (50) Discard

1 Washer Item (51) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 183

5

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@A340

SERVICE BULLETIN

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (54) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 001 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-015 001 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 001 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 184

5

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@A340

SERVICE BULLETIN

(10) Subtask 574124-832-012-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAA

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 185

5

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@A340

SERVICE BULLETIN

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (8) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (50) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (54) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 001 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 186

5

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@A340

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-016 001 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 001 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

**CONF 003

(1) Subtask 574124-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 187

5

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@A340

SERVICE BULLETIN

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-005 003 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(2) Subtask 574124-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 188

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@A340

SERVICE BULLETIN

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-006 003 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(3) Subtask 574124-832-003-003 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-011 003 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-003 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 189

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) Do SUBTASK 574124-832-012 003 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 574124-832-005-003 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 190

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@A340

SERVICE BULLETIN

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-001 003 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 003 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-009 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 191

5

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@A340

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-017 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 003 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(6) Subtask 574124-832-006-003 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 192

5

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@A340

SERVICE BULLETIN

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-002 003 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 003 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-010 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 193

5

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@A340

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-018 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 003 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(7) Subtask 574124-832-007-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 194

5

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@A340

SERVICE BULLETIN

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-003 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-011 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-019 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 195

5

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@A340

SERVICE BULLETIN

(b) For the inspection report, refer to Fig. A-FRAAA.

(8) Subtask 574124-832-008-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 196

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-004 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-012 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-020 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(9) Subtask 574124-832-011-003 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 197

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (88) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 198

5

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@A340

SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (64) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 003 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 003 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-015 003 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 003 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 199

5

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-011 003 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(10) Subtask 574124-832-012-003 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 200

5

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@A340

SERVICE BULLETIN

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (88) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (64) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 003 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 003 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 201

5

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@A340

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-016 003 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 003 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 003 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

**CONF 004

(1) Subtask 574124-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 202

5

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@A340

SERVICE BULLETIN

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-005 004 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(2) Subtask 574124-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 203

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@A340

SERVICE BULLETIN

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-006 004 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(3) Subtask 574124-832-003-004 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-011 004 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-004 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 204

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-012 004 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 574124-832-005-004 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 205

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@A340

SERVICE BULLETIN

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-001 004 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 004 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-009 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 206

5

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@A340

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-017 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 004 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(6) Subtask 574124-832-006-004 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCCAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 207

5

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@A340

SERVICE BULLETIN

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-002 004 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 004 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-010 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 208

5

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@A340

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-018 001 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 004 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAA.

(7) Subtask 574124-832-007-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 209

5

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@A340

SERVICE BULLETIN

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-003 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-011 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-019 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 210

5

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@A340

SERVICE BULLETIN

(b) For the inspection report, refer to Fig. A-FRAAA.

(8) Subtask 574124-832-008-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCDAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 211

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-004 001 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-012 001 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-020 001 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(9) Subtask 574124-832-011-004 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 212

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (91) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 213

5

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@A340

SERVICE BULLETIN

1 Washer Item (67) Discard

1 Nut Item (83) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (84) Discard

1 Washer Item (88) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (86) Discard

1 Washer Item (58) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 004 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 004 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 214

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@A340

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-015 004 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 004 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 004 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

(10) Subtask 574124-832-012-004 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 215

5

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@A340

SERVICE BULLETIN

References

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (91) Discard

1 Washer Item (67) Discard

1 Nut Item (83) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (84) Discard

1 Washer Item (88) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 216

5

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@A340

SERVICE BULLETIN

1 Screw Item (86) Discard

1 Washer Item (58) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 004 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 004 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAA.

2 If crack is found:

a Apply SUBTASK 574124-833-016 004 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 004 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 004 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAA.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 217

5

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@A340

SERVICE BULLETIN

**CONF 005

(1) Subtask 574124-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-007 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-005 005 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-007 003 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 218

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-832-002-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A340-57-4090 is accomplished:

1 Do SUBTASK 574124-832-008 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574124-832-006 005 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight and do SUBTASK

574124-832-008 003 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(3) Subtask 574124-832-003-005 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 219

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-011 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-005 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 574124-832-012 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 574124-832-005-005 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 220

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCCAB Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-001 005 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 221

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-005 005 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-007 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-009 003 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-017 002 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-005 005 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAB.

(6) Subtask 574124-832-006-005 - Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 222

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCCAB Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-002 005 Install New same Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 223

5

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-006 005 Do a Rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight and do

SUBTASK 574124-832-008 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Apply SUBTASK 574124-833-010 003 Oversize the Hole of the Area A

Pre Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-018 002 Install New Fastener Pre

Service Bulletin No. A340-57-4090 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-006 005 Do a Rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Fig. A-FRAAB.

(7) Subtask 574124-832-007-003 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 224

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 6.50

Minimum number of person 2

Subtask elapsed time 3.25

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCDAB Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-003 002 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, LH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 225

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574124-832-007 003 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-011 003 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-019 002 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-007 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(8) Subtask 574124-832-008-003 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 226

5

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@A340

SERVICE BULLETIN

References

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCDAB Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-004 002 Install New same Fastener Post

Service Bulletin No. A340-57-4090 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 003 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 227

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@A340

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-012 003 Oversize the Hole of the Area A

Post Service Bulletin No. A340-57-4090 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-020 002 Install New Fastener

Post Service Bulletin No. A340-57-4090 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-008 003 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(9) Subtask 574124-832-011-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 228

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 229

5

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@A340

SERVICE BULLETIN

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 005 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-015 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 005 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(10) Subtask 574124-832-012-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 230

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (73) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 231

5

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@A340

SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 005 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-016 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 005 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 232

5

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@A340

SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

**CONF 007

(1) Subtask 574124-832-001-002 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 574124-832-009 001 Do a Rototest Inspection of the Hole of the

Area A of the Frame 40, LH Side at the threshold given in the table 3 of the

Planning Information Paragraph E.(2).

(2) Subtask 574124-832-002-002 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 233

5

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@A340

SERVICE BULLETIN

(a) Do SUBTASK 574124-832-010 001 Do a Rototest Inspection of the Hole of the

Area A of the Frame 40, RH Side at the threshold given in the table 3 of the

Planning Information Paragraph E.(2).

(3) Subtask 574124-832-003-006 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 574124-832-011 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574124-832-004-006 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 574124-832-012 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 234

5

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@A340

SERVICE BULLETIN

(5) Subtask 574124-832-009-001 - Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCEAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the hole of the area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAB Sheet 01

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 235

5

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@A340

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 574124-833-005 001 Install New same Fastener of the

Area A in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-009 001 Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-013 001 Oversize the Hole of the Area A to

First Oversize in comparison with the current hole diameter, LH Side and

check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-021 001 Install New Fastener of

the Area A in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-009 001 Do a Rototest Inspection of the Hole of

the Area A of the Frame 40, LH Side at the interval given in the

table 4 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(6) Subtask 574124-832-010-001 - Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 236

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCEAA Sheet 01

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the hole of the area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAB Sheet 01

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-006 001 Install New same Fastener of the

Area A in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-010 001 Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

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SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 574124-833-014 001 Oversize the Hole of the Area A to

First Oversize in comparison with the current hole diameter, RH Side and

check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-022 001 Install New Fastener of

the Area A in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-010 001 Do a Rototest Inspection of the Hole of

the Area A of the Frame 40, RH Side at the interval given in

the table 4 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(7) Subtask 574124-832-011-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 238

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SERVICE BULLETIN

References

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 239

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SERVICE BULLETIN

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-007 005 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-015 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-023 005 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-011 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

(8) Subtask 574124-832-012-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 240

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SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAB

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FRAAB

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (73) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 241

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SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAB Sheet 01 and Fig. A-FCBAB Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 574124-833-008 005 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Fig. A-FRAAB.

2 If crack is found:

a Apply SUBTASK 574124-833-016 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 574124-833-024 005 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574124-832-012 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 242

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SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Fig. A-FRAAB.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 574124-700-001-002 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 243

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SERVICE BULLETIN

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 002

(1) Subtask 574124-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 244

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SERVICE BULLETIN

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 003

(1) Subtask 574124-700-001-003 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 245

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SERVICE BULLETIN

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 004

(1) Subtask 574124-700-001-004 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 246

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SERVICE BULLETIN

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 005

(1) Subtask 574124-700-001-005 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 247

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 248

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@A340

SERVICE BULLETIN

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 007

(1) Subtask 574124-700-001-007 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 249

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SERVICE BULLETIN

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF ALL

E. CLOSE-UP

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

NOTE: This paragraph is only applicable if no crack found after the inspection of the

holes.

**CONF 001

(1) Subtask 574124-410-001-002 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 250

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WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-002-002 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 251

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@A340

SERVICE BULLETIN

References

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 252

5

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@A340

SERVICE BULLETIN

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 574124-410-001-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 253

5

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@A340

SERVICE BULLETIN

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-002-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 254

5

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@A340

SERVICE BULLETIN

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 003

(1) Subtask 574124-410-001-003 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 255

5

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@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 256

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-410-002-003 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 257

5

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@A340

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 004

(1) Subtask 574124-410-001-004 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 258

5

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@A340

SERVICE BULLETIN

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-002-004 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 259

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 260

5

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@A340

SERVICE BULLETIN

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 005

(1) Subtask 574124-410-001-005 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 005 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 261

5

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@A340

SERVICE BULLETIN

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-002-005 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 005 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 262

5

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@A340

SERVICE BULLETIN

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 007

(1) Subtask 574124-410-001-007 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 263

5

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@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 264

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-410-002-007 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 265

5

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@A340

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 266

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SERVICE BULLETIN

Task 574124-833-801-001 - Repair

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

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.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 267

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NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

Task Associated Data

**CONF 001

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 002

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 003

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 004

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 005

Zone

130 137 138 192

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 268

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SERVICE BULLETIN

Manpower

TOTAL MANHOURS 52.00

ELAPSED TIME (HOURS) 44.00

**CONF 007

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 269

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SERVICE BULLETIN

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF 002

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF 003

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 270

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF 004

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 271

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SERVICE BULLETIN

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF 005

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 272

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SERVICE BULLETIN

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF 007

(1) Subtask 574124-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

**CONF ALL

B. PREPARATION

NOTE: If you intend to accomplish this Repair Task during the same layover period

as the associated Inspection, the subsequent Preparation procedure is not

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 273

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SERVICE BULLETIN

necessary.

NOTE: This PREPARATION procedure is already done in the INSPECTION task.

**CONF 001

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 274

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References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 275

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References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 276

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References

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 002

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 277

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SERVICE BULLETIN

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 278

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SERVICE BULLETIN

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 279

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2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 280

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@A340

SERVICE BULLETIN

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 003

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 281

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@A340

SERVICE BULLETIN

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 282

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@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 283

5

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 004

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 284

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@A340

SERVICE BULLETIN

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 285

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@A340

SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 286

5

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@A340

SERVICE BULLETIN

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 287

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@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 005

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 288

5

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@A340

SERVICE BULLETIN

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 289

5

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@A340

SERVICE BULLETIN

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 290

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 007

(1) Subtask 574124-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 291

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 28-25-00-650-801

Task 57-17-11-000-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(c) Do the de-fuelling of the center tank, refer to AMM Task 28-25-00-650-801.

(d) Remove the covers 147AZ and 148AZ (Refer to AMM Task 57-17-11-000-801).

(e) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 574124-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 574124-865-002-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 292

5

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@A340

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 574124-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 574124-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 293

5

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@A340

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574124-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 294

5

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@A340

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 574124-833-001-002 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 295

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(2) Subtask 574124-833-002-002 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 296

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-003-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 297

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-004-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 298

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 299

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(5) Subtask 574124-833-007-002 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 300

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-22A Item 59

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 301

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-18A Item 50

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(6) Subtask 574124-833-008-002 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 302

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 303

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Nut ASNA2531-5 Item 9

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-22A Item 59

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-18A Item 50

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 304

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(7) Subtask 574124-833-009-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 574124-833-010-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 305

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-011-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 306

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 574124-833-012-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 574124-833-015-002 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 307

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 574124-833-016-002 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 308

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 574124-833-017-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 309

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(14) Subtask 574124-833-018-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 310

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(15) Subtask 574124-833-019-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 311

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(16) Subtask 574124-833-020-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 312

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 313

5

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@A340

SERVICE BULLETIN

(17) Subtask 574124-833-023-002 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

9 ASNA2531-5 1 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 314

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Bolt MS21250-07022 Item 60

1 Washer ASNA2394EW7 Item 82

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 315

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@A340

SERVICE BULLETIN

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07018 Item 53

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(18) Subtask 574124-833-024-002 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A01R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

9 ASNA2531-5 1 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 316

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 317

5

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@A340

SERVICE BULLETIN

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Bolt MS21250-07022 Item 60

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07018 Item 53

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF 002

(1) Subtask 574124-833-001-001 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 318

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 319

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-833-002-001 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 320

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@A340

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-003-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 321

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-004-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 322

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(5) Subtask 574124-833-007-001 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A04R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

54 NSA5399-6-16A 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 323

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 324

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@A340

SERVICE BULLETIN

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-18A Item 50

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-16A Item 54

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(6) Subtask 574124-833-008-001 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 325

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A04R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 1 SCREW

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

54 NSA5399-6-16A 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 326

5

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@A340

SERVICE BULLETIN

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

1 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-18A Item 50

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 327

5

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@A340

SERVICE BULLETIN

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-16A Item 54

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(7) Subtask 574124-833-009-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 328

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@A340

SERVICE BULLETIN

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 574124-833-010-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-011-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 329

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 574124-833-012-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 330

5

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@A340

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 574124-833-015-001 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 331

5

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@A340

SERVICE BULLETIN

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 574124-833-016-001 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 574124-833-017-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 332

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 333

5

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@A340

SERVICE BULLETIN

(14) Subtask 574124-833-018-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 334

5

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@A340

SERVICE BULLETIN

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(15) Subtask 574124-833-019-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 335

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(16) Subtask 574124-833-020-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 336

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(17) Subtask 574124-833-023-001 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A04R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 6 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 337

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

53 MS21250-07018 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 338

5

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@A340

SERVICE BULLETIN

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y19 Item 10

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07018 Item 53

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07016 Item 55

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 339

5

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@A340

SERVICE BULLETIN

(18) Subtask 574124-833-024-001 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A04R06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 6 NUT

3 EN6115V6X16 1 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

53 MS21250-07018 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 340

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y19 Item 10

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07018 Item 53

1 Washer NSA5372EW716B Item 80

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 341

5

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@A340

SERVICE BULLETIN

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07016 Item 55

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF 003

(1) Subtask 574124-833-001-003 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 342

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(2) Subtask 574124-833-002-003 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 343

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-003-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 344

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-004-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 345

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 346

5

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@A340

SERVICE BULLETIN

(5) Subtask 574124-833-007-003 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A05R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

88 EN6115-5-19 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 347

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5-19 Item 88

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw MS21250-06016 Item 64

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 348

5

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@A340

SERVICE BULLETIN

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(6) Subtask 574124-833-008-003 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A05R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 349

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

88 EN6115-5-19 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 350

5

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@A340

SERVICE BULLETIN

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5-19 Item 88

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw MS21250-06016 Item 64

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 351

5

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@A340

SERVICE BULLETIN

(7) Subtask 574124-833-009-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 574124-833-010-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 352

5

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@A340

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-011-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 353

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 574124-833-012-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 574124-833-015-003 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 354

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 574124-833-016-003 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 355

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 574124-833-017-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 356

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(14) Subtask 574124-833-018-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 357

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(15) Subtask 574124-833-019-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 358

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(16) Subtask 574124-833-020-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 359

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 360

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(17) Subtask 574124-833-023-003 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A05R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 2 NUT

62 MS20002C6 2 WASHER

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 361

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw NSA5398-6-16A Item 66

1 Washer MS20002C6 Item 62

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 362

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@A340

SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(18) Subtask 574124-833-024-003 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A05R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 2 NUT

62 MS20002C6 2 WASHER

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 363

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 364

5

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@A340

SERVICE BULLETIN

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw NSA5398-6-16A Item 66

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF 004

(1) Subtask 574124-833-001-004 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 365

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 366

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-833-002-004 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 367

5

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@A340

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-003-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 368

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-004-001 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 369

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(5) Subtask 574124-833-007-004 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A06R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

86 NSA5399-6-25A 1 SCREW

91 EN6115-5X18 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 370

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 371

5

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@A340

SERVICE BULLETIN

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-23A Item 84

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-25A Item 86

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 372

5

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@A340

SERVICE BULLETIN

(6) Subtask 574124-833-008-004 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A06R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

86 NSA5399-6-25A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 373

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@A340

SERVICE BULLETIN

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 374

5

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@A340

SERVICE BULLETIN

5 Install the fastener at hole H262:

1 Screw NSA5399-6-23A Item 84

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-25A Item 86

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(7) Subtask 574124-833-009-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 375

5

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@A340

SERVICE BULLETIN

References

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 574124-833-010-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 376

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@A340

SERVICE BULLETIN

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-011-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 574124-833-012-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 377

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 574124-833-015-004 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 378

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@A340

SERVICE BULLETIN

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 574124-833-016-004 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 379

5

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@A340

SERVICE BULLETIN

(13) Subtask 574124-833-017-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 380

5

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@A340

SERVICE BULLETIN

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(14) Subtask 574124-833-018-001 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 381

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(15) Subtask 574124-833-019-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 382

5

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(16) Subtask 574124-833-020-001 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 383

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(17) Subtask 574124-833-023-004 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A06R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 384

5

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 EN6115-5Y18 1 SCREW

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

85 MS21250-07023 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 385

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07023 Item 85

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07025 Item 87

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 386

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(18) Subtask 574124-833-024-004 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A06R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

57 EN6115-5Y18 1 SCREW

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

85 MS21250-07023 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 387

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Washer NSA5368PD516B Item 67

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 388

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07023 Item 85

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07025 Item 87

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF 005

(1) Subtask 574124-833-001-005 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 389

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 390

5

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@A340

SERVICE BULLETIN

(2) Subtask 574124-833-002-005 - Install New same Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 391

5

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@A340

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-003-002 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 392

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-004-002 - Install New same Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 393

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Refer to Fig. A-FCDAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(5) Subtask 574124-833-007-005 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 394

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 395

5

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@A340

SERVICE BULLETIN

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(6) Subtask 574124-833-008-005 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 396

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 397

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@A340

SERVICE BULLETIN

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 398

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(7) Subtask 574124-833-009-003 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAB Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 399

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@A340

SERVICE BULLETIN

(8) Subtask 574124-833-010-003 - Oversize the Hole of the Area A Pre Service Bulletin

No. A340-57-4090 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAB Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-011-003 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 6.50

Minimum number of person 2

Subtask elapsed time 3.25

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 400

5

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@A340

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAB Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAB Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 574124-833-012-003 - Oversize the Hole of the Area A Post Service

Bulletin No. A340-57-4090 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAB Sheet 01

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 401

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAB Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 574124-833-015-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 402

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SERVICE BULLETIN

(12) Subtask 574124-833-016-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 574124-833-017-002 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 403

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(14) Subtask 574124-833-018-002 - Install New Fastener Pre Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 404

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAB

Removal/Installation of the Fastener Pre

Service Bulletin A340-57-4090 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 405

5

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@A340

SERVICE BULLETIN

(15) Subtask 574124-833-019-002 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 406

5

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@A340

SERVICE BULLETIN

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(16) Subtask 574124-833-020-002 - Install New Fastener Post Service Bulletin No.

A340-57-4090 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAB

Removal/Installation of the Fastener

Post Service Bulletin A340-57-4090 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAB Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 407

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(17) Subtask 574124-833-023-005 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 408

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 409

5

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@A340

SERVICE BULLETIN

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(18) Subtask 574124-833-024-005 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 410

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 411

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 412

5

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@A340

SERVICE BULLETIN

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF 007

(1) Subtask 574124-833-005-001 - Install New same Fastener of the Area A in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 413

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(2) Subtask 574124-833-006-001 - Install New same Fastener of the Area A in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 414

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(3) Subtask 574124-833-007-005 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 415

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 416

5

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@A340

SERVICE BULLETIN

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(4) Subtask 574124-833-008-005 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 417

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 418

5

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@A340

SERVICE BULLETIN

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 419

5

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@A340

SERVICE BULLETIN

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(5) Subtask 574124-833-013-001 - Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCEAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 420

5

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@A340

SERVICE BULLETIN

(6) Subtask 574124-833-014-001 - Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCEAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(7) Subtask 574124-833-015-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 421

5

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@A340

SERVICE BULLETIN

References

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(8) Subtask 574124-833-016-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 422

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(9) Subtask 574124-833-021-001 - Install New Fastener of the Area A in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 423

5

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@A340

SERVICE BULLETIN

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(10) Subtask 574124-833-022-001 - Install New Fastener of the Area A in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 574124A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 424

5

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(11) Subtask 574124-833-023-005 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 425

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 426

5

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@A340

SERVICE BULLETIN

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(12) Subtask 574124-833-024-005 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 427

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 574124A08R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 428

5

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@A340

SERVICE BULLETIN

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 429

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SERVICE BULLETIN

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 574124-700-002-002 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 430

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SERVICE BULLETIN

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 002

(1) Subtask 574124-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 431

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@A340

SERVICE BULLETIN

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 003

(1) Subtask 574124-700-002-003 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 432

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@A340

SERVICE BULLETIN

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 004

(1) Subtask 574124-700-002-004 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 433

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 434

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@A340

SERVICE BULLETIN

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 005

(1) Subtask 574124-700-002-005 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 435

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@A340

SERVICE BULLETIN

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF 007

(1) Subtask 574124-700-002-007 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Task 57-17-11-400-801

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 574124-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 574124-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 436

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@A340

SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

6 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the covers 147AZ and 148AZ (Refer to AMM Task

57-17-11-400-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

4 Do test procedure as specified after the Installation of the covers 147AZ and

148AZ (Refer to AMM Task 57-17-11-400-801).

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 574124-410-003-002 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 437

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WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-004-002 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 438

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SERVICE BULLETIN

References

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 439

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@A340

SERVICE BULLETIN

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 574124-410-003-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 440

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@A340

SERVICE BULLETIN

(c) On the RH side, install the air ventilation duct (Refer toAMM Task

21-20-00-410-001 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-001 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-004-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 441

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@A340

SERVICE BULLETIN

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 003

(1) Subtask 574124-410-003-003 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 442

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SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 443

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(2) Subtask 574124-410-004-003 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 444

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 004

(1) Subtask 574124-410-003-004 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 445

5

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@A340

SERVICE BULLETIN

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-004-004 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 446

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 447

5

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@A340

SERVICE BULLETIN

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 005

(1) Subtask 574124-410-003-005 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 005 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 448

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574124-410-004-005 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 005 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 449

5

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@A340

SERVICE BULLETIN

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

**CONF 007

(1) Subtask 574124-410-003-007 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 450

5

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@A340

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 451

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(2) Subtask 574124-410-004-007 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574124-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 452

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 574124-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 57-17-11-400-801

(a) Install the covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(b) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(c) Remove the access platform(s).

(d) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 453

5

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@A340

SERVICE BULLETIN

**CONF ALL

Z130

FR39.1

FR40

B

B

A

A

RH SIDE SHOWN

LH SIDE SYMMETRICAL

(11) (12)

(14)

(13)

B

F_SB_574124_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD CargoCompartment)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 454

5

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@A340

SERVICE BULLETIN

**CONF ALL

B

FR39.2

FR40.2

A

B

(26)

A Z192

F_SB_574124_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 455

5

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@A340

SERVICE BULLETIN

**CONF ALL

FR39.2

FR40.2

B

(41)

A

B

A Z192

F_SB_574124_5_BCAA_01_01

Figure A-FBCAA - Sheet 01

Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 456

5

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@A340

SERVICE BULLETIN

**CONF 001

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

A Z141 Z142 − 

F_SB_574124_5_CAAB_01_02

Figure A-FCAAB - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 457

5

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@A340

SERVICE BULLETIN

**CONF 001

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

01

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) 01

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

01

01

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

01

01

EN6115−5X18 SCREW

ASNA2531−5 NUT

EN6115−5Y18 SCREW

NUT

N

ASNA2531−5

91

9

57

9

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−18A SCREW

ASNA2394EW6 WASHER

ASNA0094−6 NUT

N MS21250−07018

50

58

52

53

N

82

90

02

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

ASNA2394EW7

NSA5057−7

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−22A SCREW

ASNA2394EW6 WASHER

ASNA0094−6 NUT

MS21250−07022

59

58

52

60

82

90

SCREW

WASHER

NUT

ASNA2394EW7

NSA5057−7

02

02

02

02

02

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(91)

(9)

(56)

(9)

(50)

(58)

(52)

(50)

(51)

(52)

(59)

(58)

(52)

(59)

(58)

(52)

ITEM REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

01

02

01

02

01

02

01

02

01

02

01

02

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.692 mm

(0.342 in)

8.732 mm

(0.343 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

F_SB_574124_5_CAAB_02_03

Figure A-FCAAB - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 458

5

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@A340

SERVICE BULLETIN

**CONF 002

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

A Z141 Z142 − 

F_SB_574124_5_CAAA_01_02

Figure A-FCAAA - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 459

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL PN DESCRIPTION REMARKS

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

STANDARD FASTENER

IN TRANSITION FIT

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

IN TRANSITION FIT

(1)

(2)

(1)

(2)

01

N

HEAD ON THE VISIBLE SIDE

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) FIRST OVERSIZE 01

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

(4)

(2)

(1)

(2)

01

01

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

(6)

(2)

(6)

(2)

01

01

8.692 mm

(0.342 in)

8.732 mm

(0.343 in)

EN6115−5X19 SCREW

ASNA2531−5 NUT

EN6115−5Y19 SCREW

NUT

N

ASNA2531−5

(8)

(9)

(8)

(9)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−18A SCREW

NSA5372EW616B WASHER

ASNA0094−6 NUT

N MS21250−07018

(50)

(51)

(52)

(50)

N

(51)

(52)

NEXT NOMINAL

02

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

NSA5372EW716B

NSA5057−7

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−16A SCREW

NSA5372EW616B WASHER

ASNA0094−6 NUT

MS21250−07016

(54)

(51)

(52)

(54)

(51)

(52)

SCREW

WASHER

NUT

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5372EW716B

NSA5057−7

02

02

02

02

02

NOTE:

01 DEPENDING ON INSPECTION RESULT

02

1

2

3

2

4

2

5

2

6

2

7

2

8

9

10

9

50

51

52

53

80

90

54

51

52

55

80

90

ITEM

INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

01

02

01

02

01

02

01

02

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

F_SB_574124_5_CAAA_02_03

Figure A-FCAAA - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 460

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

A Z141 Z142 − 

F_SB_574124_5_CAAC_01_02

Figure A-FCAAC - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 461

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 003

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

EN6115−5−19 SCREW

ASNA2531−5 NUT

EN6115−5X19 SCREW

NUT

N

ASNA2531−5

88

9

8

9

MS21250−06018 SCREW

WASHER

NSA5057−6 NUT

N NSA5398−6−18A

61

62

63

65

N

62

52

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

SCREW

WASHER

NUT

64

62

63

66

62

52

SCREW

WASHER

NUT

MS20002C6

ASNA0094−6

MS20002C6

MS21250−06016

NSA5057−6

NSA5398−6−16A

MS20002C6

ASNA0094−6

MS20002C6

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(88)

(9)

(88)

(9)

(61)

(62)

(63)

(61)

(62)

(63)

(64)

(62)

(63)

(64)

(62)

(63)

ITEM

01

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) 01

01

01

01

01

02

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

7.815 mm

(0.307 in)

7.849 mm

(0.309 in)

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

01

02

01

02

01

02

01

02

01

02

01

02

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

STANDARD FASTENER

IN TRANSITION FIT

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

STANDARD FASTENER

IN TRANSITION FIT

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

IN TRANSITION FIT

9.886 mm FIRST OVERSIZE

(0.389 in)

9.925 mm

(0.390 in)

IN TRANSITION FIT

9.886 mm FIRST OVERSIZE

(0.389 in)

9.925 mm

(0.390 in)

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

F_SB_574124_5_CAAC_02_06

Figure A-FCAAC - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 462

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

A Z141 Z142 − 

F_SB_574124_5_CAAD_01_03

Figure A-FCAAD - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 463

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 004

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

NSA5399−6−23A SCREW

ASNA2394EW6 WASHER

NSA5372EW616B

N

ASNA0094−6

84

58

51

52

85

82

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

EN6115−5X18 SCREW

NSA5368PD516B WASHER

NSA5050−5 NUT

N EN6115−5Y18

91

67

83

57

67

83

SCREW

WASHER

NUT

NSA5368PD516B

NSA5050−5

8.692mm

(0.342 in)

8.732 mm

(0.343 in)

8.211 mm

(0.323 in)

8.245 mm

(0.328 in)

8.296 mm

(0.326 in)

8.335 mm

(0.324 in)

80

90

WASHER

NUT

SCREW

WASHER

WASHER

NUT

MS21250−07023

ASNA2394EW7

NSA5372EW716B

NSA5057−7

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(91)

(67)

(83)

(91)

(67)

(83)

(84)

(58)

(51)

(52)

(84)

(58)

(51)

(52)

ITEM

01

01

01

01

01

01

02

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

01

02

01

02

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

F_SB_574124_5_CAAD_02_04

Figure A-FCAAD - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 464

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 004

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EXISTING HOLE DIAMETER

MIN MAX

N

SCREW

ASNA2394EW6 WASHER

86

58

51

87

82

80

SCREW

ASNA2394EW7 WASHER

MS21250−07025

(86) NSA5399−6−25A

(58)

ITEM

(51)

(86)

(58)

(51)

REMARKS

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

52 ASNA0094−6 NUT

90 NSA5057−7 NUT

(52)

(52)

NSA5372EW616B WASHER

NSA5372EW716B WASHER

F_SB_574124_5_CAAD_03_02

Figure A-FCAAD - Sheet 03

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 465

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

A Z141 Z142 − 

F_SB_574124_5_CAAF_01_03

Figure A-FCAAF - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 466

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

EN6115V6−19 SCREW

NUT

EN6115V6X19 SCREW

NUT

N

91

2

92

2

EN6115V6−22 SCREW

NUT

EN6115V6X22 SCREW

NUT

N

93

2

94

2

EN6115V6−24 SCREW

ASNA2531−6 NUT

EN6115V6X24 SCREW

NUT

N

ASNA2531−6

75

2

76

2

N

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

SCREW

WASHER

NUT

61

62

63

65

62

52

SCREW

WASHER

NUT

MS21250−06018

NSA5057−6

NSA5398−6−18A

MS20002C6

ASNA0094−6

MS20002C6

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

EN6115V5−20 SCREW

ASNA2531−5 NUT

EN6115V5X20 SCREW

NUT

N

ASNA2531−5

73

9

74

9

7.815 mm

(0.308 in)

7.849 mm

(0.309 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

(1)

(2)

(1)

(2)

(91)

(2)

(92)

(2)

(93)

(2)

(93)

(2)

(75)

(2)

(75)

(2)

(73)

(9)

(73)

(9)

(61)

(62)

(63)

(61)

ITEM

(62)

(63)

01

01

01

01

01

01

02

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

01

02

01

02

01

02

01

02

01

02

01

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

F_SB_574124_5_CAAF_02_05

Figure A-FCAAF - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 467

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR47

FR40

B

B

A

A Z141 Z142 − 

F_SB_574124_5_CBAA_01_01

Figure A-FCBAA - Sheet 01

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 468

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR40

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

NOTE:

DO A ROTOTEST

INSPECTION OF THE HOLE OF THE AREA A AS PER NTM TASK 51−10−01

DO A ROTOTEST

INSPECTION OF THE HOLES OF THE AREA B AS PER NTM TASK 51−10−01

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER

B 12, 13, 14, 21, 22, 23, 24, 261, 262, 263

A 260

F_SB_574124_5_CBAA_02_03

Figure A-FCBAA - Sheet 02

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 469

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

FR47

FR40

B

B

A

A Z141 Z142 − 

F_SB_574124_5_CBAB_01_00

Figure A-FCBAB - Sheet 01

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 470

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

FR40

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

NOTE:

DO A ROTOTEST

INSPECTION OF THE HOLE OF THE AREA A AS PER NTM TASK 51−10−01

DO A ROTOTEST

INSPECTION OF THE HOLES OF THE AREA B AS PER NTM TASK 51−10−01

AREA HOLE NUMBER

B 12, 13, 14, 21, 22, 23, 24, 261, 262, 263

A 260

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

H260

F_SB_574124_5_CBAB_02_01

Figure A-FCBAB - Sheet 02

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 471

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H260

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

(1)

(2)

(1)

(2)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

A 260

A Z141 Z142 − 

F_SB_574124_5_CCAA_01_03

Figure A-FCCAA - Sheet 01

Removal/Installation of the Fastener Pre Service Bulletin A340-57-4090 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 472

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

(1)

(2)

(1)

(2)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

NOTE:

AREA HOLE NUMBER

A 260

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

CENTER WING BOX LOWER PANEL REFERENCE

H260

F_SB_574124_5_CCAB_01_00

Figure A-FCCAB - Sheet 01

Removal/Installation of the Fastener Pre Service Bulletin A340-57-4090 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 473

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H260

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

EN6115V7−16 SCREW

ASNA2531−7 NUT

EN6115V7X16 SCREW

NUT

N

94

78

79

78

EXISTING HOLE DIAMETER

MIN MAX

10.972 mm

(0.432 in)

11.007 mm

(0.433in)

ASNA2531−7

(94)

(78)

(94)

(78)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

CENTER WING BOX LOWER PANEL REFERENCE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

NOTE:

AREA HOLE NUMBER

A 260

A Z141 Z142 − 

F_SB_574124_5_CDAA_01_03

Figure A-FCDAA - Sheet 01

Removal/Installation of the Fastener Post Service Bulletin A340-57-4090 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 474

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

EN6115V7−16 SCREW

ASNA2531−7 NUT

EN6115V7X16 SCREW

NUT

N

94

78

79

78

EXISTING HOLE DIAMETER

MIN MAX

10.972 mm

(0.432 in)

11.007 mm

(0.433in)

ASNA2531−7

(94)

(78)

(94)

(78)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

NOTE:

AREA HOLE NUMBER

A 260

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

CENTER WING BOX LOWER PANEL REFERENCE

H260

F_SB_574124_5_CDAB_01_00

Figure A-FCDAB - Sheet 01

Removal/Installation of the Fastener Post Service Bulletin A340-57-4090 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 475

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

(1)

(2)

(1)

(2)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

NOTE:

AREA HOLE NUMBER

A 260

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

CENTER WING BOX LOWER PANEL REFERENCE

H260

F_SB_574124_5_CEAA_01_04

Figure A-FCEAA - Sheet 01

Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 476

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 005

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

AND

(REFER TO SUBTASKS 574124−832−003 AND 574124−832−004 FOR AREA B)

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE

(REFER TO SUBTASKS 574124−832−011 AND 574124−832−012)

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

(REFER TO SUBTASK 574124−832−011

OF THE FASTENER HOLES OF THE

AREA B OF THE FRAME 40, LH AND RH SIDES

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 02

AREA B IN TRANSITION FIT, LH AND

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASKS 574124−832−001 AND 574124−832−002 FOR AREA A)

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER

HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

AND/OR 574124−832−012)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−007

AND/OR 574124−833−008)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

F_SB_574124_5_FAAA_01_02

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 477

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 005

QUESTION

ACTION

FINDING

CRACKS

OR

(REFER TO SUBTASKS 574124−832−005 AND 574124−832−006)

SB No A340−57−4090 OF THE FASTENER HOLE

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

A340−57−4090 NO YES ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 01

SB No.

CRACKS YES NO

(REFER TO SUBTASK 574124−832−007 AND/OR 574124−832−008)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA SHEET 03

OR

(REFER TO SUBTASK 574124−832−005 AND/OR 574124−832−006)

SB No A340−57−4090 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

APPLY SB No A340−57−4090

YES NO

SEE FIG. A−FFAAA

SHEET 03

(SB No A340−57−4090

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 03

(SB No A340−57−4090

NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENER PRE SB No A340−57−4090

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

DO A ROTOTEST INSPECTION PRE

SB No A340−57−4090 OF THE FASTENER HOLE

DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 574124−832−007 AND/OR 574124−832−008)

SB No A340−57−4090 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

INSTALL NEW SAME FASTENER POST SB No A340−57−4090

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION POST

BEFORE NEXT FLIGHT

NOTE:

01 THRESHOLD TO BE COUNTED FROM MSB 57−4090 EMBODIMENT

01

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−001 AND/OR 574124−833−002)

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−003 AND/OR 574124−833−004)

F_SB_574124_5_FAAA_02_02

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 478

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 005

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

NO YES

SEE FIG. A−FFAAA

SHEET 01 AND SHEET 02

INSTALL NEW FASTENER PRE OR POST

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−009 AND/OR 574124−833−010) OR

SEE FIG. A−FFAAA SHEET 02 

(SB No A340−57−4090

NOT ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 02

(SB No A340−57−4090

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 01

CONTACT AIRBUS

A340−57−4090

ACCOMPLISHED

SB No

SB No A340−57−4090 OF THE AREA A

(REFER TO SUBTASK 574124−833−011 AND/OR 574124−833−012)

(REFER TO SUBTASK 574124−832−005

SB No A340−57−4090 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION PRE

(REFER TO SUBTASK 574124−832−007

SB No A340−57−4090 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION POST

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−017 AND/OR 574124−833−018) OR

(REFER TO SUBTASK 574124−833−019 AND/OR 574124−833−020)

CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE AREA B

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−015 AND/OR 574124−833−016)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−023

(REFER TO SUBTASK 574124−832−011

OF THE FASTENER HOLES OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

BEFORE NEXT FLIGHT

AND/OR 5734124−832−006)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

AND/OR 574124−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

CONTACT AIRBUS

BEFORE NEXT FLIGHT

 AND/OR 574124−833−024)

AND/OR 574124−832−012)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLE OF THE AREA A PRE OR POST

SB No A340−57−4090 TO FIRST OVERSIZE IN COMPARISON WITH

CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREA B TO

FIRST OVERSIZE IN COMPARISON WITH THE

F_SB_574124_5_FAAA_03_03

Figure A-FFAAA - Sheet 03

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 479

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 007

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER

HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE AREA B

(REFER TO SUBTASKS 574124−832−011 AND 574124−832−012)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAB

SHEET 02

SEE FIG. A−FFAAB

SHEET 02 (AREA B)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−007 AND/OR 574124−833−008)

CRACKS NO YES FOUND

SEE FIG. A−FFAAB

SHEET 02

SEE FIG. A−FFAAB

SHEET 02 (AREA A)

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

(REFER TO SUBTASKS 574124−832−009 AND 574124−832−010)

OF THE FASTENER HOLE

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574124−832−009 AND/OR 574124−832−010)

OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

INSTALL NEW SAME FASTENER OF THE AREA A

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−005 AND/OR 574124−833−006)

DO A ROTOTEST INSPECTION

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASK 574124−832−011 AND/OR 574124−832−012)

OF THE FASTENER HOLES OF THE

AREA B OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASKS 574124−832−001 AND 574124−832−002 FOR AREA A) AND 

(REFER TO SUBTASKS 574124−832−003 AND 574124−832−004 FOR AREA B)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

F_SB_574124_5_FAAB_01_02

Figure A-FFAAB - Sheet 01

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 480

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 007

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

SEE FIG. A−FFAAB

SHEET 01

INSTALL NEW FASTENER

HOLE DIAMETER, LH AND RH SIDES BEFORE NEXT FLIGHT

OVERSIZE THE HOLE OF THE AREA A

TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT

(REFER TO SUBTASK 574124−833−013 AND/OR 574124−833−014)

SEE FIG. A−FFAAB SHEET 01

SEE FIG. A−FFAAB SHEET 01

CONTACT AIRBUS

OF THE AREA A IN TRANSITION FIT,

(REFER TO SUBTASK 574124−832−009

OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−833−021

CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE

CURRENT HOLE DIAMETER, LH AND RH SIDES

OVERSIZE THE HOLES OF THE AREA B TO

FIRST OVERSIZE IN COMPARISON WITH THE

(REFER TO SUBTASK 574124−833−015 AND/OR 574124−833−016)

AREA B IN TRANSITION FIT, LH AND RH SIDES

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574124−832−011

OF THE FASTENER HOLES OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

BEFORE NEXT FLIGHT

AND/OR 574124−833−022)

AND/OR 5734124−832−010)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

CONTACT AIRBUS

BEFORE NEXT FLIGHT

AND/OR 574124−832−012)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574124−833−023

AND/OR 574124−833−024)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

F_SB_574124_5_FAAB_02_03

Figure A-FFAAB - Sheet 02

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 481

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4124

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CRACKS AFTER

OVERSIZE

H12 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H13 YES NO YES NO YES NO YES NO

H14 YES NO YES NO YES NO YES NO

H21 YES NO YES NO YES NO YES NO

H22 YES NO YES NO YES NO YES NO

H23 YES NO YES NO YES NO YES NO

H24 YES NO YES NO YES NO YES NO

H260 YES NO YES NO YES NO YES NO

H261 YES NO YES NO YES NO YES NO

H262 YES NO YES NO YES NO YES NO

H263 YES NO YES NO YES NO YES NO

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

F_SB_574124_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 482

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 001 thru 004

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4124

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

INSPECTION

H12

RH SIDE

H13

H14

H21

H22

H23

H24

H260

H261

H262

H263

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

mm

FINAL

DIAMETER

in

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

F_SB_574124_5_RAAA_02_02

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 483

5

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@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

A Z141 Z142 − 

F_SB_574124_5_RAAA_03_00

Figure A-FRAAA - Sheet 03

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 484

5

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@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 260

HOLE 13

FR40 FRONT

FITTING

(8 mm)

(0.315 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 12 & 14

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

F_SB_574124_5_RAAA_04_01

Figure A-FRAAA - Sheet 04

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 485

5

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@A340

SERVICE BULLETIN

**CONF 001 thru 004

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 21, 22, 23 & 24

HOLE 262 HOLE 263

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB

GUSSET

(5 mm)

(0.197 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in) CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

CWB

GUSSET

(8 mm TO

8.5 mm)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

HOLE 261

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(6 mm)

(0.236 in)

FWD

FWD

(0.315 in to

0.334 in)

CWB

GUSSET

(11 mm TO

11.5 mm)

(0.433 in to

0.453 in)

SHIM

(6.5 mm)

(0.256 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

F_SB_574124_5_RAAA_05_01

Figure A-FRAAA - Sheet 05

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 486

5

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@A340

SERVICE BULLETIN

**CONF 005, 007

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4124

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CRACKS AFTER

OVERSIZE

H12 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H13 YES NO YES NO YES NO YES NO

H14 YES NO YES NO YES NO YES NO

H21 YES NO YES NO YES NO YES NO

H22 YES NO YES NO YES NO YES NO

H23 YES NO YES NO YES NO YES NO

H24 YES NO YES NO YES NO YES NO

H260 YES NO YES NO YES NO YES NO

H261 YES NO YES NO YES NO YES NO

H262 YES NO YES NO YES NO YES NO

H263 YES NO YES NO YES NO YES NO

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

F_SB_574124_5_RAAB_01_00

Figure A-FRAAB - Sheet 01

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 487

5

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@A340

SERVICE BULLETIN

**CONF 005, 007

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4124

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

INSPECTION

H12

RH SIDE

H13

H14

H21

H22

H23

H24

H260

H261

H262

H263

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

mm

FINAL

DIAMETER

in

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

F_SB_574124_5_RAAB_02_01

Figure A-FRAAB - Sheet 02

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 488

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

FR47

FR40

B

B A

A Z141 Z142 − 

FR40

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW LOOKING AFT

STGR38

STGR39

STGR40

STGR37

CENTER WING BOX LOWER PANEL REFERENCE

H260 H263

H262

H23 H14

H21 H13 H12

H24

H22

H261

F_SB_574124_5_RAAB_03_02

Figure A-FRAAB - Sheet 03

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 489

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

**CONF 005, 007

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 260

HOLE 13

FR40 FRONT

FITTING

(8 mm)

(0.315 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 12 & 14

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

F_SB_574124_5_RAAB_04_01

Figure A-FRAAB - Sheet 04

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 490

5

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@A340

SERVICE BULLETIN

**CONF 005, 007

HOLE 21, 23 & 24

NOTE:

THESE THICKNESSES ARE THEORETICAL

HOLE 22

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(12 mm)

(0.472 in)

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(6 mm)

(0.236 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FWD

F_SB_574124_5_RAAB_05_01

Figure A-FRAAB - Sheet 05

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 491

5

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@A340

SERVICE BULLETIN

**CONF 005, 007

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 262

HOLE 263

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in) CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

CWB

GUSSET

(8 mm TO

9 mm)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

HOLE 261

FWD

(0.315 in to

0.354 in)

CWB

GUSSET

(11 mm TO

12 mm)

(0.433 in to

0.472 in)

CWB

GUSSET

(12.5 mm TO

13.5 mm)

(0.492 in to

0.531 in)

F_SB_574124_5_RAAB_06_01

Figure A-FRAAB - Sheet 06

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 492

5

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@A340

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

MODIFICATION No.: None

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 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 1

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@A340

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 04/13 SERVICE BULLETIN No.: A340-57-4124

REVISION No.: 01 - Aug 22/13 Page: 1

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