# @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 KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). MODIFICATION No.: None This page transmits Revision No.05 of Service Bulletin No.A340-57-4089 ADDITIONAL WORK **CONF ALL NOTE: No additional work is required by this revision for aircraft modified by any previous issue. REASON The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649. Revision No. 05 issued to update the threshold and intervals and to add the grace period value. CHANGES SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R 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
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R Fig. A-FSAAA Fig. A-FSAAA Sheet 01 SHEET UPDATED R Fig. A-FSAAB Fig. A-FSAAB Sheet 01 SHEET UPDATED R Fig. A-FSAAC Fig. A-FSAAC Sheet 01 SHEET UPDATED R Fig. A-FSAAD Fig. A-FSAAD Sheet 01 SHEET UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 005 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 007 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 008 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R REASON Objective/Action OBJECTIVE/ACTION UPDATED R Advantages ADVANTAGES UPDATED R COMPLIANCE Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
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 PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability Kits price and availability updated. R TOOLING TOOLING UPDATED R Tooling - Price and Availability TOOLING - PRICE AND AVAILABILITY PARAGRAPH ADDED N Tools TOOLS PARAGRAPH ADDED N Special Tools SPECIAL TOOLS PARAGRAPH ADDED N ACCOMPLISHMENT INSTRUCTIONS TASK574089- 832-801-001-INSPECTION TASK SOLUTION UPDATED NOTE UPDATED R Task associated data - 003 MAN HOURS UPDATED R Task associated data - 007 MAN HOURS UPDATED R Task associated data - 008 MAN HOURS UPDATED R Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-941-001-002 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. Config. 004 deleted. R Subtask 574089-010-001-001 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-010-002-001 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-832-007-001 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-832-008-001 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-001-001 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 574089-410-002-001 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-010-001-002 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-010-002-002 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-832-007-002 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-832-008-002 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-001-002 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-410-002-002 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-010-001-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-010-002-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-832-007-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-832-008-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-001-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-410-002-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-010-002-003 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-832-008-003 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-002-003 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-010-001-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-010-002-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 574089-832-007-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-832-008-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-001-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-410-002-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-010-001-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-010-002-004 Config. 004 deleted. Removal procedure of the air conditioning duct deleted. R
Subtask 574089-832-007-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-832-008-004 Config. 004 deleted. Reference to NTM 51-10-01 Part 6 added. R Subtask 574089-410-001-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R
Subtask 574089-410-002-004 Config. 004 deleted. Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Fig. A-FBAAA Fig. A-FBAAA Sheet 01 SHEET UPDATED R Fig. A-FBAAB Fig. A-FBAAB Sheet 01 SHEET UPDATED R Fig. A-FBAAC Fig. A-FBAAC Sheet 01 SHEET UPDATED R Fig. A-FBAAD Fig. A-FBAAD Sheet 01 SHEET UPDATED R Fig. A-FFAAA Fig. A-FFAAA Sheet 01 SHEET UPDATED R Fig. A-FFAAA Sheet 02 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAB Fig. A-FFAAB Sheet 01 SHEET UPDATED R Fig. A-FFAAB Sheet 02 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAB Sheet 03 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAC Fig. A-FFAAC Sheet 01 SHEET UPDATED R Fig. A-FFAAC Sheet 02 SHEET UPDATED R Fig. A-FFAAD
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 5 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-FFAAD Sheet 01 SHEET UPDATED R Fig. A-FFAAD Sheet 02 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAD Sheet 03 SRM 51-41-11 becomes 51-44-11. R Fig. A-FCAAA Fig. A-FCAAA Sheet 01 SHEET UPDATED R Fig. A-FCAAB Fig. A-FCAAB Sheet 01 SHEET UPDATED R Fig. A-FCAAC Fig. A-FCAAC Sheet 01 SHEET UPDATED R Fig. A-FCAAD Fig. A-FCAAD Sheet 01 SHEET UPDATED R Fig. A-FCAAD Sheet 02 SHEET UPDATED R Appendix 01 - Inspection Report Fig. A-FRAAA FIGURE SOLUTION ADDED N Fig. A-FRAAA Sheet 01 SHEET ADDED N Fig. A-FRAAB FIGURE SOLUTION ADDED N Fig. A-FRAAB Sheet 01 SHEET ADDED N Fig. A-FRAAC FIGURE SOLUTION ADDED N Fig. A-FRAAC Sheet 01 SHEET ADDED N Fig. A-FAA FIGURE DELETED FOR APPLICABLE MSN 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 Revision No. 01 issued to add aircraft MSN 0007 for operator AFR, to add aircraft MSN 0008 for operator SAA, to add aircraft MSN 0024 for operator DLH and to add MSN 0204 for operator B3R. Revision No. 02 issued to inform the operators that this Service Bulletin is rendered mandatory. The inspection requirements of this Service Bulletin are cancelled by accomplishment of Service Bulletin No. A340-57-4098 (FUSELAGE - CENTER FUSELAGE - MODIFY FASTENING SYSTEM IN FR40 / KEEL BEAM JUNCTION AREA) which is scheduled early 2006 on A340 aircraft PRE MOD 41652S11819. Revision No. 03 issued to extend the effectivity of this Service Bulletin and propose modification Service Bulletin to cancel repetitive inspection requirements. The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649. Revision No. 04 issued to include minor improvements after validation : to update the flow chart for the Config. 003, 007 and 008, to delete the access procedure of the FWD cargo compartment, to delete the removal/installation procedures of the air conditioning duct, to delete the Config. 004 (MSN 0007 scrapped). DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION SEQUENCE ORIGINAL: Oct 30/03 REVISION No.: 01 - Mar 02/04 REVISION No.: 02 - Jan 24/06 REVISION No.: 03 - Jul 31/09 REVISION No.: 04 - May 31/11 REVISION No. : 05 - Nov 13/12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 7 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 8 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 KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A340 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame FR40, initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD No. 41652S12091 (serial Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) configuration. Results for this configuration have been extended to POST MOD No. 43577S12677 (retrofit Mod.) (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION) configuration which is similar. This Service Bulletin requires a special detailed inspection on A340 aircraft PRE MOD 55306S18660 and PRE MOD 55792S18775. Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of FR40 datum after fastener removal (Rotating Probe Inspection following NTM 51-10-01 Part 6) and subsequent action. For the Config. 1 and 5 accomplishment of Service Bulletin No. A340-57-4098 (Mod No. 54459S18477) cancels the Inspection requirements of this Service Bulletin No. A340-57-4089. For the Config. 2,3,7 and 8, accomplishment of Service Bulletin No. A340-57-4106 (Mod No. 56467S18944) cancels the Inspection requirements of this Service Bulletin No. A340-57-4089. Accomplishment of this Service Bulletin will permit early detection of cracking in the keel beam and will avoid extensive repair and aircraft down time.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A340 SERVICE BULLETIN SUMMARY 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 DE-FUELLING/VENTILATING YES NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A01R00 2 534.00 Screw, Washer, Nut **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A01R00 2 534.00 Screw, Washer, Nut **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A02R01 2 414.00 Screw, Washer, Nut **CONF 005 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A01R00 1 267.00 Screw, Washer, Nut **CONF 007 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A02R01 2 414.00 Screw, Washer, Nut

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A340 SERVICE BULLETIN SUMMARY **CONF 008 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574089A02R01 2 414.00 Screw, Washer, Nut EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

47W 56W 83V AAW ABQ AFR AIB ALK ARG CAL CCA CES CPA DGA DLH FIN GAF GFA HFY I2L IBE IRC KAC KNE LAN M3R MAU MDG MSR NMB PAL QAF RJA S3R SAA SAS SFB SWR TAP THT THY UAE VCV VIR XAX NOTE: This Service Bulletin has been validated on A340 aircraft 0402. NOTE: A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS World - Maintenance and Engineering - Service Bulletin Information. NOTE: The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.005 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHERS Operator Information Telex(OIT) No. 999.0083/03 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A340 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 002 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 003 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 005 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 27.00 ELAPSED TIME (HOURS) 25.00 **CONF 007 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 008 Task 574089-832-801-001: INSPECTION TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 APPENDICES **CONF ALL Appendix 01 - Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

F_SB_574089_5_SAAA_01_02 Figure A-FSAAA - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 5 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47



### B **B**



## A

**B**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 − Z141 Z142 

### A

F_SB_574089_5_SAAB_01_01 Figure A-FSAAB - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A340 SERVICE BULLETIN SUMMARY

**CONF 005

RH SIDE SHOWN FR40 FR47

− Z141 Z142 

### A **B**



## A

AREA TO INSPECT Y1959

STGR1 FR40 DATUM



## B
F_SB_574089_5_SAAC_01_01 Figure A-FSAAC - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 7 5

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# @A340 SERVICE BULLETIN SUMMARY
**CONF 003, 007 thru 008

LH SIDE SHOWN RH SIDE SYMMETRICAL FR40 FR47



### B **B**



## A

DATUM Y2390 Y1959

AREA TO INSPECT STGR1 FR40

**F W**  **D**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 − Z141 Z142 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959 FR40DATUM



## B

STGR1 

### C



## C

F_SB_574089_5_SAAD_01_01 Figure A-FSAAD - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 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 KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). 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 has been validated on A340 aircraft MSN 0402

. NOTE: A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS World - Maintenance and Engineering - Service Bulletin Information. NOTE: This Service Bulletin is only applicable to aircraft on which modification No. 55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and modification No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) is not embodied. (1) Models 340-211 340-212 340-213 340-311 340-312 340-313 (2) Effectivity by MSN 0002-0005 0009 0011 0014-0015 0018-0019 0021-0026 0032 0034 0041 0044 0046 0048 0051 0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085 0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128-0129 0131 0133-0137 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A340 SERVICE BULLETIN
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 0235-0237 0239 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 0377-0379 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 47W 0009 56W 0003 0011 0015 0018 0019 0021 83V 0235 0239 0280 0292 AAW 0151 ABQ 0257 AFR 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 AIB 0332 ALK 0032 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 CES 0129 0131 0141 0161 0182 CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228 DGA 0075 0081 DLH 0024 0053 0056 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 I2L 0216 IBE 0005 0088 0125 0134 0145 0146 0170 0193 0217 0221 0318 0329 0387 0414 0459 0474 0483 IRC 0002 KAC 0089 0090 0101 0104 KNE 0004 LAN 0167 0359 0363 0429 0442 M3R 0061 MAU 0076 0152 0194 0268 0793 0800 MDG 0210 0319 MSR 0156 0159 0178
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A340 SERVICE BULLETIN
OPERATOR MSN NMB 0051 PAL 0173 0176 0187 0196 QAF 0026 0528 RJA 0014 0022 S3R 0204 SAA 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0413 0424 0430 0435 0450 0467 0470 SFB 0046 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 0190 0202 0236 VCV 0302 VIR 0114 0164 0214 0225 XAX 0273 0278 (4) Configuration by MSN MSN CONFIGURATION 0002 0003 0004 0005 0009 0011 0014 0015 0018 0019 0021 0022 0023 0025 0026 0032 0034 0041 0044 0046 0048 0051 0053 0056 0057 0058 0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0085 0088 0089 0090 0091 0093 0094 0101 0104 001

0024 005 0114 0115 0117 0123 0125 0126 0128 0129 0131 0133 0134 0135 0136 0137 0139 0141 0142 0145 0146 0147 0149 0150 0151 0152 0154 0156 0157 0158 0159 0160 0161 0163 0164 0166 0167 0168 0169 0170 0173 0174 0175 002

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 0235 0236 0237 0239 0245 0246 0252 0257 0260 0263 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 003

0242 0243 0264 007 0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 008

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A340 SERVICE BULLETIN (5) Configuration definition **CONF 001 Config. 001 is valid for aircraft model A340-200 and A340-300 on which Service Bulletin No. A340-57-4036 or Mod. No. 43577S12677 has been accomplished and on which Service Bulletin No.A340-57-4098 (Mod. No.54459S18477) has not been accomplished and Mod. No. 41652S12091 is not embodied. **CONF 002 Config. 002 is valid for aircraft model A340-200 and A340-300 on which Mod. No. 41652S12091 is embodied and on which Service Bulletin No. A340-57-4106 (Mod. No.56467S18944) has not been accomplished and Mod. No. 44360S13013 or Mod. No. 44360S13482 are not embodied. **CONF 003 Config. 003 is valid for aircraft model A340-200 and A340-300 on which Mod. No. 44360S13013 or Mod. No. 44360S13482 is embodied and Service Bulletin No. A340-57-4106 (Mod. No.56467S18944) has not been accomplished and Mod. No. 46650H13983 and Mod. No. 49202S16307 are not embodied. **CONF 005 Config. 005 is valid for aircraft model A340-300 on RH side only and on which a specific repair with titanium repair (Refer to Repair drawing R57115053 or R57115051 or R57115047) has been embodied on the LH side only and on which Service Bulletin No. A340-57-4036 (Mod. No.43577S12677) has been accomplished and on which Service Bulletin No. A340-57-4098 (Mod. No.54459S18477) has not been accomplished and Mod. No. 41652S12091 is not embodied. **CONF 007 Config. 007 is valid for aircraft model A340-300 on which Mod. No. 44360S13013 or Mod. No. 44360S13482 and Mod. No. 46650H13983 are embodied and Service Bulletin No. A340-57-4106 (Mod. No.56467S18944) has not been accomplished and Mod. No. 49202S16307 is not embodied. **CONF 008 Config. 008 is valid for aircraft model A340-300 on which Mod. No. 49202S16307 is embodied and on which Service Bulletin No. A340-57-4106 (Mod. No.56467S18944) has not been accomplished. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 574089A01R00 2 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 574089A01R00 2 Consumable CMLA01 1
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A340 SERVICE BULLETIN
**CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 574089A02R01 2 Consumable CMLA01 1 **CONF 005 MATERIAL QTY PER A/C SEE NOTES Kit 574089A01R00 1 Consumable CMLA01 1 **CONF 007 MATERIAL QTY PER A/C SEE NOTES Kit 574089A02R01 2 Consumable CMLA01 1 **CONF 008 MATERIAL QTY PER A/C SEE NOTES Kit 574089A02R01 2 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a structural A340 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame FR40, initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD No. 41652S12091 (serial Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) configuration. Results for this configuration have been extended to POST MOD No. 43577S12677 (retrofit Mod.) (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION) configuration which is similar. (2) Objective/Action This Service Bulletin requires a special detailed inspection on A340 aircraft PRE MOD 55306S18660 and PRE MOD 55792S18775. Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of FR40 datum after fastener removal (Rotating Probe Inspection following NTM 51-10-01 Part 6) and subsequent action.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 5 5

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# @A340 SERVICE BULLETIN (3) Advantages For the Config. 1 and 5 accomplishment of Service Bulletin No. A340-57-4098 (Mod No. 54459S18477) cancels the Inspection requirements of this Service Bulletin No. A340-57-4089. For the Config. 2,3,7 and 8, accomplishment of Service Bulletin No. A340-57-4106 (Mod No. 56467S18944) cancels the Inspection requirements of this Service Bulletin No. A340-57-4089. Accomplishment of this Service Bulletin will permit early detection of cracking in the keel beam and will avoid extensive repair and aircraft down time. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 574089-832-801-001: INSPECTION (1) Remove the Fastener on the LH Side (2) Remove the Fastener on the RH Side (3) Do a special detailed inspection of the hole at FR40, on the LH Side (4) Do a special detailed inspection of the hole at FR40, on the RH Side (5) Install the Fastener on the LH Side (6) Install the Fastener on the RH Side **CONF 002 Task 574089-832-801-001: INSPECTION (1) Remove the Fastener on the LH Side (2) Remove the Fastener on the RH Side (3) Do a special detailed inspection of the hole at FR40, on the LH Side (4) Do a special detailed inspection of the hole at FR40, on the RH Side (5) Install the Fastener on the LH Side (6) Install the Fastener on the RH Side

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A340 SERVICE BULLETIN
**CONF 003 Task 574089-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a special detailed inspection of the holes at FR40, on the LH Side (4) Do a special detailed inspection of the holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF 005 Task 574089-832-801-001: INSPECTION (1) Remove the Fastener on the RH Side (2) Do a special detailed inspection of the hole at FR40, on the RH Side (3) Install the Fastener on the RH Side **CONF 007 Task 574089-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a special detailed inspection of the holes at FR40, on the LH Side (4) Do a special detailed inspection of the holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF 008 Task 574089-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a special detailed inspection of the holes at FR40, on the LH Side (4) Do a special detailed inspection of the holes at FR40, on the RH Side
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 7 5

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# @A340 SERVICE BULLETIN (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 001 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 11,400 (01) SR: 43,100 (01) SR: 9,650 SR: 36,500 SR: 2,900 (01) SR: 10,900 (01) SR: 1,900 SR: 7,250 LR: 10,400 (01) LR: 67,800 (01) LR: 8,800 LR: 57,400 LR: 2,600 (01) LR: 17,200 (01) LR: 1,750 LR: 11,400 Table 1 : Accomplishment Timescale table

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 8 5

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# @A340 SERVICE BULLETIN
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,350 FC - 69,870 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 8,760 FC - 59,160 FH NOTE (01): On aircraft pre Mod. No. 41652S12091, the threshold is only valid from accomplishment of Service Bulletin No. A340-57-4036 or embodiment of the Mod. No. 43577S12677. NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs.
CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 001 A340-57-4098 9,900 61,800

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 9 5

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# @A340 SERVICE BULLETIN
**CONF 002 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 002 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 12,100 SR: 45,600 SR: 8,600 SR: 32,400 SR: 3,550 SR: 14,300 SR: 1,800 SR: 7,150 LR: 11,000 LR: 71,800 LR: 7,800 LR: 50,900 LR: 2,950 LR: 20,200 LR: 1,450 LR: 10,100 Table 1 : Accomplishment Timescale table
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,960 FC - 74,040 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 7,780 FC - 52,510 FH

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 10 5

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# @A340 SERVICE BULLETIN
NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 002 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 003 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 003 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 12,100 SR: 45,600 SR: 8,600 SR: 32,400 SR: 5,050 SR: 19,000 SR: 2,150 SR: 8,250 LR: 11,000 LR: 71,800 LR: 7,800 LR: 50,900 LR: 4,550 LR: 29,900 LR: 1,950 LR: 12,900 Table 1 : Accomplishment Timescale table DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 11 5

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# @A340 SERVICE BULLETIN

NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,960 FC - 74,040 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 7,780 FC - 52,510 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 003 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 005 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 12 5

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# @A340 SERVICE BULLETIN Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 005 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 11,400 (01) SR: 43,100 (01) SR: 9,650 SR: 36,500 SR: 2,900 (01) SR: 10,900 (01) SR: 1,900 SR: 7,250 LR: 10,400 (01) LR: 67,800 (01) LR: 8,800 LR: 57,400 LR: 2,600 (01) LR: 17,200 (01) LR: 1,750 LR: 11,400 Table 1 : Accomplishment Timescale table
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,350 FC - 69,870 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 8,760 FC - 59,160 FH NOTE (01): On aircraft pre Mod. No. 41652S12091, the threshold is only valid from accomplishment of Service Bulletin No. A340-57-4036 or embodiment of the Mod. No. 43577S12677. NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 13 5

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# @A340 SERVICE BULLETIN
CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 005 A340-57-4098 9,900 61,800

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 007 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 007 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 12,100 SR: 45,600 SR: 8,600 SR: 32,400 SR: 5,050 SR: 19,000 SR: 2,150 SR: 8,250 LR: 11,000 LR: 71,800 LR: 7,800 LR: 50,900 LR: 4,550 LR: 29,900 LR: 1,950 LR: 12,900 Table 1 : Accomplishment Timescale table
NOTE: Grace Period for the threshold (whichever occurs first) :
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 14 5

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# @A340 SERVICE BULLETIN
- 24 months from the Service Bulletin Revision No. 05 issuance - 16,950 FC - 33,900 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 12,020 FC - 24,040 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 007 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 008 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold / interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary. As a consequence, the selection of SR or LR threshold and subsequent intervals can be changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 15 5

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# @A340 SERVICE BULLETIN Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first : CONFIG. MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) 008 Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 16,600 SR: 62,600 SR: 8,600 SR: 32,400 SR: 10,000 SR: 40,200 SR: 2,150 SR: 8,250 LR: 15,100 LR: 98,400 LR: 7,800 LR: 50,900 LR: 8,350 LR: 56,600 LR: 1,950 LR: 12,900 Table 1 : Accomplishment Timescale table
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 15,020 FC - 101,410 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 7,780 FC - 52,510 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONFIG. SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) 008 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 16 5

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# @A340 SERVICE BULLETIN
**CONF ALL F. APPROVAL The technical content of this document is approved under authority of Design Organization Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 574089-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fastener on the LH Side 1.00 Remove the Fastener on the RH Side 1.00 Do a special detailed inspection of the hole at FR40, on the LH Side 1.00 Do a special detailed inspection of the hole at FR40, on the RH Side 1.00 Install the Fastener on the LH Side 1.00 Install the Fastener on the RH Side 1.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 002 Task 574089-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fastener on the LH Side 1.00 Remove the Fastener on the RH Side 1.00 Do a special detailed inspection of the hole at FR40, on the LH Side 1.00 Do a special detailed inspection of the hole at FR40, on the RH Side 1.00

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 17 5

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# @A340 SERVICE BULLETIN
Task 574089-832-801-001: INSPECTION Install the Fastener on the LH Side 1.00 Install the Fastener on the RH Side 1.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 003 Task 574089-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a special detailed inspection of the holes at FR40, on the LH Side 3.00 Do a special detailed inspection of the holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 005 Task 574089-832-801-001: INSPECTION Get Access 10.00 On Aircraft Remove the Fastener on the RH Side 1.00 Do a special detailed inspection of the hole at FR40, on the RH Side 1.00 Install the Fastener on the RH Side 1.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 27.00 ELAPSED TIME (HOURS) 25.00 **CONF 007 Task 574089-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 18 5

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# @A340 SERVICE BULLETIN
Task 574089-832-801-001: INSPECTION Do a special detailed inspection of the holes at FR40, on the LH Side 3.00 Do a special detailed inspection of the holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 008 Task 574089-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a special detailed inspection of the holes at FR40, on the LH Side 3.00 Do a special detailed inspection of the holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 19 5

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# @A340 SERVICE BULLETIN Service Bulletin (SB) A340-57-4036 A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 002 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 Service Bulletin (SB) A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 003 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 Service Bulletin (SB) A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 005 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 Service Bulletin (SB) A340-57-4036 A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 20 5

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# @A340 SERVICE BULLETIN
**CONF 007 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 Service Bulletin (SB) A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 008 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 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 51-10-06 Service Bulletin (SB) A340-57-4098 A340-57-4106 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571150 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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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 : Kit 574089A01R00 Kit 574089A02R01 AIRBUS Material logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 For ordering by E-mail :airbus.kit@airbus.com (2) Price and Availability

Kit 574089A01R00 Cost 267.00 USD Availability 60 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 574089A02R01 Cost 207.00 USD Availability 60 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 23 5

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# @A340 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 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 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 3 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required (2) Components None

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# @A340 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6. Tools necessary to do the check by ROTOTEST : Instrument : Rototest B588 and rotor standard. Probe RS35 dia. 6.2 mm (0.244 in.). Probe RS50 dia. 7.8 mm (0.307 in.). Calibration standard : 99A53003001001-103 and 99A53003001001-106. Supplier : ROHMANN Gmbh Rudolf Diesel Str.13 67227 FRANKENTHAL Tel.0 62 33 - 7881 Telex 468602 esro d GERMANY (2) Tools None (3) Special Tools None

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# @A340 SERVICE BULLETIN

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# @A340 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 574089-832-801-001 - INSPECTION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START A REFUEL/DEFUEL PROCEDURE. IN THIS SAFE AREA, DO NOT LET PERSONS: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR THE TASK. AIRCRAFT FUEL IS FLAMMABLE. WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE. 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 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 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 002 Zone 141 142 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 27 5

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# @A340 SERVICE BULLETIN
Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 35.00 ELAPSED TIME (HOURS) 30.00 **CONF 003 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 005 Zone 142 Access Panel 148AZ Manpower TOTAL MANHOURS 27.00 ELAPSED TIME (HOURS) 25.00 **CONF 007 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00 **CONF 008 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 35.00

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# @A340 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 574089-910-001-001 - Standard Practices 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). 5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

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# @A340 SERVICE BULLETIN
7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). 9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 574089-910-001-001 - Standard Practices 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 30 5

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# @A340 SERVICE BULLETIN
1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). 5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11). 7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). 9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 003 (1) Subtask 574089-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

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# @A340 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). 5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11). 7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). 9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required

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# @A340 SERVICE BULLETIN
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 005 (1) Subtask 574089-910-001-001 - Standard Practices 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 33 5

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# @A340 SERVICE BULLETIN
5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11). 7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). 9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 007 (1) Subtask 574089-910-001-001 - Standard Practices 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML)
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# @A340 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). 5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11). 7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). 9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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# @A340 SERVICE BULLETIN
**CONF 008 (1) Subtask 574089-910-001-001 - Standard Practices 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 Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 1 For the specification of the material numbers (Mat. No.) refer to the CML. 2 Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required
3 Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required
4 Drill and deburr the holes (Refer to SRM 51-44-11). 5 Remove and install the fasteners (Refer to SRM 51-42-11). 6 Torque the standard threaded fasteners (Refer to AMM 20-21-11). 7 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. 8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).
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# @A340 SERVICE BULLETIN
9 On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required
10 Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 574089-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 574089-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 37 5

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# @A340 SERVICE BULLETIN (g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). **CONF 002 (1) Subtask 574089-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). **CONF 003 (1) Subtask 574089-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 38 5

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# @A340 SERVICE BULLETIN (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). **CONF 005 (1) Subtask 574089-941-001-002 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access cover 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Remove the access panels 192GB and 192JB (Refer to AMM 53-35-13 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 39 5

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# @A340 SERVICE BULLETIN
**CONF 007 (1) Subtask 574089-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). **CONF 008 (1) Subtask 574089-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 40 5

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# @A340 SERVICE BULLETIN (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 574089-010-001-001 - Remove the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove : Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw Item (7) Discard
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 41 5

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# @A340 SERVICE BULLETIN

or 1 screw Item (10) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 574089-010-002-001 - Remove the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove : Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard 1 nut Item (9) Discard and if installed DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 42 5

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# @A340 SERVICE BULLETIN 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 574089-832-007-001 - Do a special detailed inspection of the hole at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4098 Fig. A-FBAAA Area to Inspect Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 (a) For the inspection area, refer to Fig. A-FBAAA Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet 01, Fig. A-FFAAA Sheet 02

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-001 001 Install the Fastener on the LH Side

.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 43 5

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# @A340 SERVICE BULLETIN
2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 574089-832-008-001 - Do a special detailed inspection of the hole at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4098 Fig. A-FBAAA Area to Inspect Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 (a) For the inspection area, refer to Fig. A-FBAAA Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet 01, Fig. A-FFAAA Sheet 02

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-002 001 Install the Fastener on the RH Side

. 2 If a crack is found: - Contact Airbus before next flight.
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 44 5

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# @A340 SERVICE BULLETIN (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 574089-410-001-001 - Install the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 45 5

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# @A340 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 9:
a Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11. b Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 9:
a Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 nut NAS1726-5E Item 9 1 screw NSA5357-5-18 Item 10 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 46 5

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# @A340 SERVICE BULLETIN (6) Subtask 574089-410-002-001 - Install the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 47 5

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# @A340 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 9:
a Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11. b Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 9:
a Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 nut NAS1726-5E Item 9 1 screw NSA5357-5-18 Item 10 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 48 5

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# @A340 SERVICE BULLETIN
**CONF 002 (1) Subtask 574089-010-001-002 - Remove the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove : Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard or 1 screw Item (11) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 49 5

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# @A340 SERVICE BULLETIN (2) Subtask 574089-010-002-002 - Remove the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove : Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard or 1 screw Item (11) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 50 5

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# @A340 SERVICE BULLETIN (3) Subtask 574089-832-007-002 - Do a special detailed inspection of the hole at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAB Area to Inspect Sheet 01 Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAB Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet 01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-001 002 Install the Fastener on the LH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 51 5

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# @A340 SERVICE BULLETIN (4) Subtask 574089-832-008-002 - Do a special detailed inspection of the hole at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAB Area to Inspect Sheet 01 Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAB Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet 01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-002 002 Install the Fastener on the RH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 52 5

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# @A340 SERVICE BULLETIN (5) Subtask 574089-410-001-002 - Install the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 53 5

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# @A340 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Do a check of the diameter of the hole, refer to the table 9 and 10 of the SRM 51-44-11. <1> If the diameter do not respect the tolerance of the table 9: - The diameter is included between the First oversize and the Second oversize: . Ream the Hole to Second oversize, refer to table 10 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
- The diameter is included between the Nominal diameter and the First oversize: . Ream the Hole to First oversize, refer to table 9 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required <2> If the diameter respect the tolerance of the table 9: - Install: DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 54 5

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# @A340 SERVICE BULLETIN

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw EN6115V5-18 Item 11 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 574089-410-002-002 - Install the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 55 5

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# @A340 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Do a check of the diameter of the hole, refer to the table 9 and 10 of the SRM 51-44-11. <1> If the diameter do not respect the tolerance of the table 9: - The diameter is included between the First oversize and the Second oversize: DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 56 5

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# @A340 SERVICE BULLETIN . Ream the Hole to Second oversize, refer to table 10 of the SRM 51-44-11 and install: Refer toFig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
- The diameter is included between the Nominal diameter and the First oversize: . Ream the Hole to First oversize, refer to table 9 of the SRM 51-44-11 and install: Refer toFig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required <2> If the diameter respect the tolerance of the table 9: - Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 57 5

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# @A340 SERVICE BULLETIN
Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw EN6115V5-18 Item 11 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. **CONF 003 (1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 58 5

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# @A340 SERVICE BULLETIN
References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 59 5

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# @A340 SERVICE BULLETIN Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 60 5

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# @A340 SERVICE BULLETIN 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01 Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH Side

.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 61 5

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# @A340 SERVICE BULLETIN
2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01 Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH Side

.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 62 5

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# @A340 SERVICE BULLETIN
2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 63 5

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# @A340 SERVICE BULLETIN (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 64 5

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# @A340 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 65 5

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# @A340 SERVICE BULLETIN Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 66 5

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# @A340 SERVICE BULLETIN
And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 or 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 67 5

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# @A340 SERVICE BULLETIN
And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. **CONF 005 (1) Subtask 574089-010-002-003 - Remove the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard 1 nut Item (9) Discard and if installed DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 68 5

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# @A340 SERVICE BULLETIN 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 574089-832-008-003 - Do a special detailed inspection of the hole at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-002 003 Install the Fastener on the RH Side

.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 69 5

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# @A340 SERVICE BULLETIN
2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (3) Subtask 574089-410-002-003 - Install the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574089A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 70 5

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# @A340 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 9:
a Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11. b Install: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 9:
a Install: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 71 5

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# @A340 SERVICE BULLETIN
**CONF 007 (1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 72 5

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# @A340 SERVICE BULLETIN

or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 73 5

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# @A340 SERVICE BULLETIN 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 74 5

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# @A340 SERVICE BULLETIN
References Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 75 5

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# @A340 SERVICE BULLETIN
References Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 76 5

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# @A340 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 77 5

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# @A340 SERVICE BULLETIN

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 78 5

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# @A340 SERVICE BULLETIN (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 79 5

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# @A340 SERVICE BULLETIN (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 80 5

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# @A340 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 or 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. **CONF 008 (1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 81 5

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# @A340 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 82 5

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# @A340 SERVICE BULLETIN (2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fasteners installed, remove from the hole A : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fasteners installed, remove from the hole B : Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 83 5

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# @A340 SERVICE BULLETIN 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01 Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 84 5

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# @A340 SERVICE BULLETIN

or - Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A340-57-4106 Fig. A-FBAAD Area to Inspect Sheet 01 Fig. A-FFAAD Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAD Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet 01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in Planning Information Paragraph E.(2).
or

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 85 5

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# @A340 SERVICE BULLETIN
- Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH Side

. 2 If a crack is found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 86 5

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# @A340 SERVICE BULLETIN
References Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 87 5

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# @A340 SERVICE BULLETIN
1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 88 5

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# @A340 SERVICE BULLETIN Material necessary to do the job Kit 574089A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAD Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11. 1 If the diameter do not respect the tolerance of the table 8:
a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 89 5

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# @A340 SERVICE BULLETIN
And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02 1 screw EN6115V5-9 Item 14 or 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 90 5

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# @A340 SERVICE BULLETIN
And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2), refer to NTM 51-10-06 Part 6. **CONF ALL D. TEST **CONF 001 (1) Subtask 574089-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 002 (1) Subtask 574089-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 91 5

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# @A340 SERVICE BULLETIN (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 003 (1) Subtask 574089-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 005 (1) Subtask 574089-710-001-002 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access cover (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 92 5

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# @A340 SERVICE BULLETIN
**CONF 007 (1) Subtask 574089-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 008 (1) Subtask 574089-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 93 5

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# @A340 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 574089-832-034-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 002 (1) Subtask 574089-832-034-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 94 5

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# @A340 SERVICE BULLETIN
**CONF 003 (1) Subtask 574089-832-034-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 005 (1) Subtask 574089-832-034-002 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 192GB and 192JB (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 007 (1) Subtask 574089-832-034-001 Manpower Resources Skills NON SPECIFIC
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 95 5

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# @A340 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 008 (1) Subtask 574089-832-034-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 96 5

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# @A340 SERVICE BULLETIN

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 F_SB_574089_5_BAAA_01_02 Figure A-FBAAA - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 97 5

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# @A340 SERVICE BULLETIN

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47



### B **B**



## A

**B**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 − Z141 Z142 

### A

F_SB_574089_5_BAAB_01_01 Figure A-FBAAB - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 98 5

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# @A340 SERVICE BULLETIN

**CONF 005

RH SIDE SHOWN FR40 FR47

− Z141 Z142 

### A **B**



## A

AREA TO INSPECT Y1959

STGR1 FR40 DATUM



## B
VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 F_SB_574089_5_BAAC_01_01 Figure A-FBAAC - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 99 5

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# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

FR40 FR47



### B **B**



## A − Z141 Z142 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL DATUM Y2390 Y1959

AREA TO INSPECT STGR1 FR40

**F W**  **D**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959 FR40DATUM



## B

STGR1 

### C



## C

F_SB_574089_5_BAAD_01_01 Figure A-FBAAD - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 100 5

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# @A340 SERVICE BULLETIN

**CONF 001

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAA. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION FINDING YES

REFER TO FIGURE A−FFAAA SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 574089−010−001−001 AND ON THE RH SIDE REFER TO SUBTASK 574089−010−002−001

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 574089−832−008−001 REFER TO SUBTASK 574089−832−007−001 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAA_01_01

Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 101 5

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

# @A340 SERVICE BULLETIN

**CONF 001

OR

DO A CHECK OF THE DIAMETER OF THE HOLE

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 9 OF THE SRM 51−44−11. FROM FIGURE A−FFAAA SHEET 1

CLEAN THE HOLE

NO YES

INSTALL NEW SAME DIAMETER FASTENER :

NSA5357−5−18 AND NAS1726−5E. REFER TO THE TABLE 9 OF THE SRM 51−44−11. REAM HOLE TO SECOND OVERSIZE. REFER TO THE TABLE 10 OF THE SRM 51−44−11.

INSTALL SECOND OVERSIZE FASTENER : NSA5359−5−18, NSA5368PD516B AND

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A340−57−4098 BEFORE THE THRESHOLDS

APPLY MOD SERVICE BULLETIN No. A340−57−4098

NAS1726−5E.

QUESTION ACTION FINDING DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

F_SB_574089_5_FAAA_02_01 Figure A-FFAAA - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 102 5

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# @A340 SERVICE BULLETIN

**CONF 002

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAB. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION FINDING YES

REFER TO FIGURE A−FFAAB SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 574089−010−001−002 AND ON THE RH SIDE REFER TO SUBTASK 574089−010−002−002

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 574089−832−008−002 REFER TO SUBTASK 574089−832−007−002 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAB_01_01

Figure A-FFAAB - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 103 5

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# @A340 SERVICE BULLETIN

**CONF 002

OR

DO A CHECK OF THE DIAMETER OF THE HOLE

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAB SHEET 1

CLEAN THE HOLE

NO YES APPLY MOD SERVICE BULLETIN No. A340−57−4106

QUESTION ACTION FINDING REFER TO FIGURE A−FFAAB SHEET 3 INSTALL NEW SAME DIAMETER FASTENER : EN6115V5−18 AND NAS1726−5E. REFER TO THE TABLE 8 OF THE SRM 51−44−11.

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A340−57−4106 BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

F_SB_574089_5_FAAB_02_01 Figure A-FFAAB - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 104 5

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# @A340 SERVICE BULLETIN

**CONF 002

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH

THE TABLE 9 AND 10 OF THE SRM 51−44−11. FROM FIGURE A−FFAAB SHEET 2

NO YES

INSTALL NEW SAME DIAMETER FASTENER :

NSA5357−5−18 AND NAS1726−5E. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

REAM HOLE TO SECOND OVERSIZE. REFER TO THE TABLE 10 OF THE SRM 51−44−11.

INSTALL SECOND OVERSIZE FASTENER : NSA5359−5−18, NSA5368PD516B AND

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. NAS1726−5E.

QUESTION ACTION FINDING OR

FIRST OVERSIZE DIAMETER

REAM HOLE TO FIRST OVERSIZE. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

INSTALL FIRST OVERSIZE FASTENER : NSA5357−5−18 AND NAS1726−5E.

DIAMETER NOMINAL DIAMETER

FIRST OVERSIZE SECOND OVERSIZE

F_SB_574089_5_FAAB_03_01 Figure A-FFAAB - Sheet 03 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 105 5

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# @A340 SERVICE BULLETIN

**CONF 005

CRACK REMOVE THE FASTENER ON THE RH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAC. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION FINDING YES

REFER TO FIGURE A−FFAAC SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 574089−010−002−003

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 574089−832−008−003 THE HOLE AT FR40, ON THE RH SIDE

F_SB_574089_5_FAAC_01_01 Figure A-FFAAC - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 106 5

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# @A340 SERVICE BULLETIN

**CONF 005

OR

DO A CHECK OF THE DIAMETER OF THE HOLE

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 9 OF THE SRM 51−44−11. FROM FIGURE A−FFAAC SHEET 1

CLEAN THE HOLE

NO YES

INSTALL NEW SAME DIAMETER FASTENER :

NSA5357−5−18 AND NAS1726−5E. REFER TO THE TABLE 9 OF THE SRM 51−44−11. REAM HOLE TO SECOND OVERSIZE. REFER TO THE TABLE 10 OF THE SRM 51−44−11.

INSTALL SECOND OVERSIZE FASTENER : NSA5359−5−18, NSA5368PD516B AND

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. NAS1726−5E.

QUESTION ACTION FINDING IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A340−57−4098 BEFORE THE THRESHOLDS

APPLY MOD SERVICE BULLETIN No. A340−57−4098 DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

F_SB_574089_5_FAAC_02_01 Figure A-FFAAC - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 107 5

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# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLES A AND B ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAD. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION FINDING YES

REFER TO FIGURE A−FFAAD SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 574089−010−001−004 AND ON THE RH SIDE REFER TO SUBTASK 574089−010−002−004

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 574089−832−008−004 REFER TO SUBTASK 574089−832−007−004 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAD_01_02

Figure A-FFAAD - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 108 5

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# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

OR

DO A CHECK OF THE DIAMETER OF THE HOLES

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAD SHEET 1

CLEAN THE HOLES

NO YES

REFER TO FIGURE A−FFAAD SHEET 3 REFER TO FIGURE A−FFAAD SHEET 3

QUESTION ACTION FINDING APPLY MOD SERVICE BULLETIN No. A340−57−4106 IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A340−57−4106 BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

F_SB_574089_5_FAAD_02_04 Figure A-FFAAD - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 109 5

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# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

FROM FIGURE A−FFAAD SHEET 2

INSTALL NEW SAME DIAMETER FASTENERS : EN6115V5−14 AND NAS1726−5E FOR HOLE A. REAM HOLES TO FIRST OVERSIZE. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

INSTALL FIRST OVERSIZE FASTENERS : NSA5357−5−14 AND NAS1726−5E FOR HOLE A.

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. INSTALL NSA5357−5−9 AND

QUESTION ACTION FINDING NAS1726−5E FOR HOLE B. INSTALL EN6115V5−9 OR EN6115V5−10 AND NAS1726−5E FOR HOLE B. REFER TO THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAD SHEET 2

F_SB_574089_5_FAAD_03_02 Figure A-FFAAD - Sheet 03 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 110 5

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# @A340 SERVICE BULLETIN

**CONF 001

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47



### B **B**



## A

**B**

VIEW FROM INSIDE CENTER TANK AT FR40 

### C − Z141 Z142 

### A

F_SB_574089_5_CAAA_01_01 Figure A-FCAAA - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 111 5

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# @A340 SERVICE BULLETIN

**CONF 001

Y1959

DATUM

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED OR DEPENDS ON AIRCRAFT CONFIGURATION F

APPLY MAT No. 09−001

F VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY FR40

**NOTE:** 01 (7) (8) (9) 7 8 9 (10) (8) (9) 10 8 9

(8) 8 01

STGR1



## C **F W**  **D**

F_SB_574089_5_CAAA_02_01 Figure A-FCAAA - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 112 5

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# @A340 SERVICE BULLETIN

**CONF 002

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47



### B **B**



## A

**B**

VIEW FROM INSIDE CENTER TANK AT FR40 

### C − Z141 Z142 

### A

F_SB_574089_5_CAAB_01_01 Figure A-FCAAB - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 113 5

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# @A340 SERVICE BULLETIN

**CONF 002

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED APPLY MAT No. 09−001

F VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY **NOTE:** 01 (8) 8 

## C OR DEPENDS ON AIRCRAFT CONFIGURATION (7) (8) (9) 7 8 9 (10) (8) (9) 10 8 9 01

STGR1 OR(11) (8) (9) 11 8 9 Y1959
DATUM

F FR40

**F W**  **D**

F_SB_574089_5_CAAB_02_01 Figure A-FCAAB - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 114 5

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# @A340 SERVICE BULLETIN

**CONF 005

RH SIDE SHOWN FR40 FR47



### B



## A

VIEW FROM INSIDE CENTER TANK AT FR40 − Z141 Z142 

### A

Y1959

STGR1 FR40 DATUM



### C



## B

F_SB_574089_5_CAAC_01_01 Figure A-FCAAC - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 115 5

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# @A340 SERVICE BULLETIN

**CONF 005

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED OR DEPENDS ON AIRCRAFT CONFIGURATION

APPLY MAT No. 09−001

F VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY **NOTE:** 01 (7) (8) (9) 7 8 9 (10) (8) (9) 10 8 9

(8) 8 01



## C Y1959

DATUM FR40

STGR1 F

**F W**  **D**

F_SB_574089_5_CAAC_02_01 Figure A-FCAAC - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 116 5

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

# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

FR40 FR47



### B **B**



## A − Z141 Z142 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL DATUM Y2390 Y1959

STGR1 FR40

**F W**  **D**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959 FR40DATUM



## B

STGR1 

### C



## C **D**

F_SB_574089_5_CAAD_01_01 Figure A-FCAAD - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 117 5

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# @A340 SERVICE BULLETIN

**CONF 003, 007 thru 008

F F HOLE B HOLE A

VIEW INSIDE CENTER TANK AT FR40

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED APPLY MAT No. 09−001

F **NOTE:** 01 01

OR DEPENDS ON AIRCRAFT CONFIGURATION (9) (16) 9 16 (9) (14) 9 14 OR DEPENDS ON AIRCRAFT CONFIGURATION (9) (15) 9 15 (9) (13) 9 13

**F W**  **D** (8) 8 (8) 8 (8) 8 (8) 8



## D

ITEM AND ONLY IF NECESSARY (8) 8

F_SB_574089_5_CAAD_02_03 Figure A-FCAAD - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 118 5

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# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report **CONF ALL (1) The results of the inspection, including no findings, replacement or action to be done, must be forwarded to Airbus department SEES1, on the attached inspection report sheet.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 1 5

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

# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF 001 thru 002

SIDE

LH RH NO CRACK CRACK DIAMETER

LH RH

LH RH HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE SECOND OVERSIZE INSTALLATION OF THE FASTENER AT:

PLEASE PRECISE OTHER FINDINGS : **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−57−4089

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

SIDE

SIDE

F_SB_574089_5_RAAA_01_00 Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF 005

SIDE RH NO CRACK CRACK DIAMETER

RH

RH HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE SECOND OVERSIZE INSTALLATION OF THE FASTENER AT:

PLEASE PRECISE OTHER FINDINGS : **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−57−4089

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

SIDE

SIDE

F_SB_574089_5_RAAB_01_00 Figure A-FRAAB - Sheet 01 Inspection Report
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report
**CONF 003, 007 thru 008

SIDE NO CRACK CRACK DIAMETER

LH RH

LH RH HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE INSTALLATION OF THE FASTENER AT: HOLE A HOLE A RH RH LH LH HOLE B HOLE B

HOLE A HOLE B

HOLE A HOLE A HOLE B HOLE B

PLEASE PRECISE OTHER FINDINGS : **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A340−57−4089

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

F_SB_574089_5_RAAC_01_00 Figure A-FRAAC - Sheet 01 Inspection Report
DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). 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: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 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: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089 REVISION No.: 05 - Nov 13/12 Page: 1 5

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