# @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



# MANDATORYMANDATORYMANDATORY
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 5

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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 5

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# @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 5

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# @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 5

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# @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 5

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# @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 5

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# @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 5

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# @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 5

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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 5

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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 574124-833-023-002 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 5

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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 574124-833-023-001 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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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# @A340
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 5

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# @A340
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 18 5

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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. 

# MANDATORYMANDATORYMANDATORY
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 5

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# @A340
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 Kit574124A01R05 2 5,800.00 Screws, Washers, Nuts Kit574124A02R05 2 360.00 Screws, Washers, Nuts Kit574124A03R04 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 Kit574124A04R06 2 5,380.00 Screws, Washers, Nuts Kit574124A02R05 2 360.00 Screws, Washers, Nuts Kit574124A03R04 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 Kit574124A05R05 2 5,080.00 Screws, Washers, Nuts Kit574124A02R05 2 360.00 Screws, Washers, Nuts Kit574124A03R04 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 5

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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 Kit574124A06R04 2 6,560.00 Screws, Washers, Nuts Kit574124A02R05 2 360.00 Screws, Washers, Nuts Kit574124A03R04 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 Kit574124A08R00 2 4,600.00 Screws, Washers, Nuts Kit574124A02R05 2 360.00 Screws, Washers, Nuts Kit574124A03R04 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 Kit574124A08R00 2 4,600.00 Screws, Washers, Nuts Kit574124A03R04 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 5

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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 5

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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 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 H263 H260 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT − Z141 Z142

H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, B 260 A 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 5

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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 260 A 24, 261, 262, 263

STGR38

STGR39

STGR40 STGR37

CENTER WING BOX LOWER PANEL REFERENCE H263 H260 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 5

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# @A340
SERVICE BULLETIN SUMMARY

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DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 8 5

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# @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



# MANDATORYMANDATORYMANDATORY
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 5

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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 5

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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 5

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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 5

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# @A340
SERVICE BULLETIN
(6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit574124A01R05 2 Kit574124A02R05 2 Kit574124A03R04 2 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit574124A04R06 2 Kit574124A02R05 2 Kit574124A03R04 2 Consumable CMLA01 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit574124A05R05 2 Kit574124A02R05 2 Kit574124A03R04 2 Consumable CMLA01 1 **CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit574124A06R04 2 Kit574124A02R05 2 Kit574124A03R04 2 Consumable CMLA01 1 **CONF 005 MATERIAL QTY PER A/C SEE NOTES Kit574124A08R00 2 Kit574124A02R05 2 Kit574124A03R04 2 Consumable CMLA01 1 **CONF 007 MATERIAL QTY PER A/C SEE NOTES Kit574124A08R00 2 Kit574124A03R04 2 Consumable CMLA01 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 5 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 thisInspection 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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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

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# @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

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# @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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 None None No crack found 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 574124-832-007 001 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 None None No crack found 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 574124-832-007 001 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 None None No crack found 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 574124-832-007 001 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 None None No crack found 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 574124-832-007 001 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 1: Special Detailed Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 None None No crack found

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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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

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# @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 Compliance Time Condition Action 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 Compliance Time Condition Action 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

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# @A340
SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Before next flight None None No crack found

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

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# @A340
SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Before next flight None None No Crack found 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

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# @A340
SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Before next flight None None No crack found

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

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# @A340
SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Side Compliance Time Condition Action 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 Before next flight None None No Crack found 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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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# @A340
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: Kit574124A01R05 Kit574124A02R05 Kit574124A03R04 Kit574124A04R06 Kit574124A05R05 Kit574124A06R04 Kit574124A08R00 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

Kit574124A01R05 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. Kit574124A02R05 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. Kit574124A03R04 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. Kit574124A04R06 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 5

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# @A340
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. Kit574124A05R05 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. Kit574124A06R04 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. Kit574124A08R00 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 5

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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 5

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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 5

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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 REVISION No.: 01 - Aug 22/13 Page: 115 5

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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-upand in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup.

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(3) Special Tools None

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 117 5

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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 REVISION No.: 01 - Aug 22/13 Page: 119 5

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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

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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.

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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 REVISION No.: 01 - Aug 22/13 Page: 122 5

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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 REVISION No.: 01 - Aug 22/13 Page: 123 5

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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 REVISION No.: 01 - Aug 22/13 Page: 124 5

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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 REVISION No.: 01 - Aug 22/13 Page: 125 5

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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 REVISION No.: 01 - Aug 22/13 Page: 127 5

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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) Retain2 Recirculation filterhousing Item (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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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: 130 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 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 REVISION No.: 01 - Aug 22/13 Page: 131 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: 132 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: 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) Retain2 Recirculation filterhousing Item (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

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: 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) Retain2 Recirculation filterhousing Item (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

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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: 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) Retain2 Recirculation filterhousing Item (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 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: 148 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) Retain2 Recirculation filterhousing Item (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 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: 150 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. **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 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: 152 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: 153 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) Retain2 Recirculation filterhousing Item (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 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: 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 5

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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 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 574124-832-008 001 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 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 574124-832-011 002 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 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-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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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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 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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# @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

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# @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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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# @A340
SERVICE BULLETIN

References Fig. A-FRAAA Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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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-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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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# @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

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# @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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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

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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 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 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, 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 5

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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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 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 Sheet01 Sheet02
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 Sheet01

Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 5

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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

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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 Sheet01 Sheet02
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 Sheet01

Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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

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# @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 Sheet01

Fig. A-FCBAB Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet01 Sheet02
Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 5

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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 Sheet01 Sheet02
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 Sheet01

Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 5

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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 Sheet01 Sheet02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 228 5

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# @A340
SERVICE BULLETIN

References Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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

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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-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 Sheet01 Sheet02
Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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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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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(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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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 Sheet01 Sheet02
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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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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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

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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 Sheet01 Sheet02
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 Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 REVISION No.: 01 - Aug 22/13 Page: 237 5

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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 Sheet01 Sheet02

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 238 5

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SERVICE BULLETIN

References Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 5

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- 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 5

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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 Sheet01 Sheet02
Fig. A-FRAAB Inspection Report Sheet01 Sheet02 Sheet03 Sheet04 Sheet05 Sheet06 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 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: 242 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 5

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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 574124-700-001 002 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 5

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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 removal2 Recirculation filterhousing Item (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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(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 systemsand 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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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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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 removal2 Recirculation filterhousing Item (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 systemsand 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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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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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 removal2 Recirculation filterhousing Item (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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(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 systemsand 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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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

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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 574124-700-001 004 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 removal2 Recirculation filterhousing Item (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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(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 systemsand 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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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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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 removal2 Recirculation filterhousing Item (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 systemsand 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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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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(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 removal2 Recirculation filterhousing Item (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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(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 systemsand the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 266 5

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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 5

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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 5

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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 5

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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. **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 5

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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 5

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(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 5

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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. **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 5

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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 5

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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 5

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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) Retain2 Recirculation filterhousing Item (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 5

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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 5

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- 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 5

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(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 5

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2 Duct Item (12) Retain2 Recirculation filterhousing Item (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 5

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(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 5

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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 5

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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) Retain2 Recirculation filterhousing Item (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 5

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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 5

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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) Retain2 Recirculation filterhousing Item (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 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 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) Retain2 Recirculation filterhousing Item (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

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# @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

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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 574124-861-002-001 - 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) Retain2 Recirculation filterhousing Item (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

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# @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

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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: 297 5

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# @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

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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: 299 5

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# @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

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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 EN6115-5X18 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

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# @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

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# @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

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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 EN6115-5X18 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

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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: 305 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: 306 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 574124-833-015-002 - 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

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# @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

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# @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

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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: 311 5

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# @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

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: 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 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 MS21250-07018 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

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-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

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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: 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 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: 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 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, 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 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 EN6115-5X19 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 5

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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

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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 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

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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 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 5

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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

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# @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

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# @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

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# @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

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# @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

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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

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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

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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

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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: 360 5

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# @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

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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 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 5

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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 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, 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 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 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 5

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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 5

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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

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# @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

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# @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

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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

(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

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# @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

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# @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 Sheet01

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 Sheet01

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 Sheet01

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

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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 574124-833-004-002 - 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 Sheet01

DATE: Apr 04/13 SERVICE BULLETIN No.: A340-57-4124 REVISION No.: 01 - Aug 22/13 Page: 393 5

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# @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 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: 398 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

(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 Sheet01

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 5

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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 Sheet01

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 Sheet01

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 Sheet01

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 5

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# @A340
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

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# @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 Sheet01

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

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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 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 Sheet01

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 Sheet01

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 Sheet01

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

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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

(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

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# @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

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# @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

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# @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

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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

(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

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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, 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

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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: 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 5

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# @A340
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 5

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# @A340
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 5

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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 5

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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 5

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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 5

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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 5

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(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 5

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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 5

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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 5

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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 removal2 Recirculation filterhousing Item (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 5

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(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 systemsand 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 5

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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 5

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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 removal2 Recirculation filterhousing Item (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 systemsand 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 5

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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

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(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 removal2 Recirculation filterhousing Item (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

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(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 systemsand 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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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

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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 574124-700-001 004 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 removal2 Recirculation filterhousing Item (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 systemsand 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

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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 574124-410-004-005 - 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 removal2 Recirculation filterhousing Item (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 systemsand 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

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# @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 removal2 Recirculation filterhousing Item (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

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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 574124-942-002-001 - 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 systemsand 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 01Removal/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 FR39.2FR40.2



## 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

FR39.2FR40.2



### 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:** DEPENDING ON INSPECTION RESULT 01 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 H24H22 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

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# @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:** DEPENDING ON INSPECTION RESULT 01 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

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# @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

H23 H24 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

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# @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:** DEPENDING ON INSPECTION RESULT 01 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 FIRST OVERSIZE 9.886 mm (0.389 in) 9.925 mm (0.390 in)

IN TRANSITION FIT FIRST OVERSIZE 9.886 mm (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

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# @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

H23 H24 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:** DEPENDING ON INSPECTION RESULT 01 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 WASHER ASNA2394EW7 MS21250−07025 NSA5399−6−25A (86) (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:** DEPENDING ON INSPECTION RESULT 01 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) ASNA0094−6 NUT 52

90 NUT NSA5057−7 (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

H23 H24 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:** DEPENDING ON INSPECTION RESULT 01 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 H263 H260 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 H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, 261, 262, 263 B 260 A

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 12, 13, 14, 21, 22, 23, 24, 261, 262, 263 B 260 A STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H14 H22 H21 H13 H12 H23 H24 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

DEPENDING ON INSPECTION RESULT 01 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 260 A 

### 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

DEPENDING ON INSPECTION RESULT 01 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 260 A 

### 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

DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 06AAA1 (WET ASSEMBLY) **NOTE:**

AREA HOLE NUMBER 260 A 

### 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

DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 06AAA1 (WET ASSEMBLY) **NOTE:**

AREA HOLE NUMBER 260 A 

### 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

DEPENDING ON INSPECTION RESULT 01 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 260 A 

### 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

NO YES

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: THRESHOLD TO BE COUNTED FROM MSB 57−4090 EMBODIMENT 01 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

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# @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 YES NO 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

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# @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

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# @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 NO H12 CRACKS CRACKS AFTER OVERSIZE YES NO YES NO YES NO RH SIDE

YES NO 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 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

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# @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 H263 H260 H262 H261

H23 H14 H24H22 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

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

# @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

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

# @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 NO H12 CRACKS CRACKS AFTER OVERSIZE YES NO YES NO YES NO RH SIDE

YES NO 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 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

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

# @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 H263 H260 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

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) 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 5

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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 5

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