# @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 ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No.: 56467S18944 This page transmits Revision No.03 of Service Bulletin No.A340-57-4106 ADDITIONAL WORK **CONF ALL NOTE: Additional work might be required by this revision for aircraft in configuration 002 of Service Bulletin No. A340-57-4106 revision No. 01 and revision No. 02 (POST MOD 44360 PRE MOD 49202), that is MSN from 176 to 483. Additional work is required for any of those aircraft if the SUBTASK 574106-831-005 002, 574106-831-010 001 or 574106-831-011 001 has been accomplished as per this Service Bulletin at revision No. 01 or revision No. 02 and if during the accomplishment of the subtask a crack was detected at hole 5 and a rototest inspection was not performed to the adjacent hole 6 before doing the cold working of the hole 6. No additional work is required by this revision for aircraft modified at initial issue. REASON Revision No. 03 issued to cover Post Mod 49202 MSNs, to update the accomplishment timescale, to amend the accomplishment instructions adding the missing rototest steps and to update the applicability of the Service Bulletin to Premod 55306 and 55792. CHANGES SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R Fig. A-FSBAA Fig. A-FSBAA Sheet 01 SHEET UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 1 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Configuration definition CONF 002 CONFIGURATION DEFINITION UPDATED R REASON History HISTORY UPDATED R Advantages ADVANTAGES UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL SET UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 574106- 831-801-001- MODIFICATION Subtask 574106-831-005-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 574106-831-005-002 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED R
Subtask 574106-831-010-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 574106-831-011-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R TASK 574106- 839-801-001-Administrative - ADDITIONAL WORK TASK SOLUTION UPDATED CAUTION UPDATED R Task associated data - 001 ELAPSED TIME UPDATED MAN HOURS UPDATED R Subtask 574106-839-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574106-839-002-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574106-839-002-002 SUBTASK SOLUTION ADDED N Subtask 574106-839-002-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Fig. A-FBCAA Fig. A-FBCAA Sheet 05 SHEET UPDATED R 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.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 2 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET HISTORY OF PREVIOUS REVISIONS Revision No. 01 issued to extend the effectivity to aircraft post mod. No. 44360S13013 and pre mod. No. 49202S16307 with specific Kit A03 and to amend accomplishment instruction for hole 5 without bush installed. Revision No. 02 issued to update the installation of the bolts and the washers. REVISION SEQUENCE ORIGINAL: Aug 30/07 REVISION No. : 01 - Jul 31/09 REVISION No. : 02 - Jun 15/11 REVISION No. : 03 - Sep 24/12

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 3 5

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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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. ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 56467S18944 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production solution configuration. The intention of the production solution was also proposed by Service Bulletin No. A340-57-4036 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod. No. 55306 S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and pre Mod. No. 55792 S18775 (REINFORCE FUSELAGE AT FR.40 (SERIAL SOLUTION)). This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam fitting at FR40. Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin A340-57-4089. ALI 57.11.63 is created for Post Mod. Service Bulletin configuration (Post Mod. No. 56467S18944). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 1 5

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# @A340 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES POTENTIAL AD NO A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574106A01R03 2 878.00 Bolts, nuts, washers Supplementary kit

574106A01S01 2 182.00 Bolts Supplementary kit

574106A01S02 2 1,180.00 Bolts, washers TOTAL 2,240.00 **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574106A03R04 2 5,580.00 Plugs, bolts, nuts, washers Supplementary kit

574106A03S01 2 1,460.00 Bolts, washers TOTAL 7,040.00 EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

83V AAW AFR ALK ARG CAL CCA CES CPA DLH FIN GAF GFA HFY IBE LAN MAU MDG MSR PAL QAF S3R SAA SAS SWR THT THY UAE VIR XAX NOTE: This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is embodied and modification No. 55306S18660 (FUSELAGE - CENTER FUSELAGE - REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and modification No. 55792S18775 (REINFORCE DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 2 5

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# @A340 SERVICE BULLETIN SUMMARY FUSELAGE AT FR40 (SERIAL SOLUTION)) are not embodied. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.005 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 574106-831-801-001: MODIFICATION TOTAL MANHOURS 65.00 ELAPSED TIME (HOURS) 38.00 Task 574106-839-801-001: Administrative - ADDITIONAL WORK TOTAL MANHOURS 0.00 **CONF 002 Task 574106-831-801-001: MODIFICATION TOTAL MANHOURS 93.50 ELAPSED TIME (HOURS) 42.00 Task 574106-839-801-001: Administrative - ADDITIONAL WORK TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 APPENDICES **CONF ALL APPENDIX 01 - Inspection Report
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 3 5

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# @A340 SERVICE BULLETIN SUMMARY
**CONF 001

FR40 FR47

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

STGR 1 Y−1959 FR40 DATUM

STGR1 Y1959

FASTENERS TO BE REPLACED OR MODIFIED FOR CONFIG. 01 (POST MOD. 41652 AND PRE MOD. 44360) 

## B **C A** 

**F W**  **D** 

### C **B B**  Z141−142 

### A

F_SB_574106_5_SAAA_01_00 Figure A-FSAAA - Sheet 01 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 4 5

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# @A340 SERVICE BULLETIN SUMMARY
**CONF 002

FR40 FR47

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

VIEW INSIDE CENTER TANK AT FR40 STGR 1 Y−1959 FR40 DATUM

STGR1 Y1959 

## A

**B C**  **F W**  **D** 

### C **B B**  Z141−142 

### A

FASTENERS TO BE REPLACED OR MODIFIED FOR CONFIG. 02 (POST MOD. 44360 AND PRE MOD. 55306 AND PRE MOD. 55792) F_SB_574106_5_SBAA_01_02 Figure A-FSBAA - Sheet 01 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 5 5

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# @A340 SERVICE BULLETIN SUMMARY

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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 ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No.: 56467S18944 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is embodied and modification No. 55306S18660 (FUSELAGE - CENTER FUSELAGE - 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)) are not embodied. (1) Models 340-212 340-213 340-311 340-312 340-313 (2) Effectivity by MSN 0114-0115 0117 0123 0125-0126 0128-0129 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233 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 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 1 5

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# @A340 SERVICE BULLETIN
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 83V 0235 0239 0280 0292 AAW 0151 AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 ALK 0367 0374 0381 ARG 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 DLH 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 FIN 0168 0174 GAF 0274 0355 GFA 0212 0215 0282 0554 HFY 0117 0133 IBE 0125 0134 0145 0146 0170 0193 0217 0221 0302 0318 0329 0332 0387 0414 0459 0474 0483 LAN 0167 0359 0363 0429 0442 MAU 0152 0194 0268 0793 0800 MDG 0210 0319 MSR 0156 0159 0178 PAL 0173 0176 0187 0196 QAF 0528 S3R 0204 SAA 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0413 0424 0430 0435 0450 0467 0470 SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561 0562 0585 0598 THT 0385 0395 0438 0446 0668 THY 0115 0180 0216 0257 0270 0331 UAE 0139 0149 0163 0166 0185 0190 0202 0236 VIR 0114 0164 0214 0225 XAX 0273 0278

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 2 5

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# @A340 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 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 001

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 0242 0243 0245 0246 0252 0257 0260 0263 0264 0268 0270 0273 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335 0347 0352 0354 0355 0359 0363 0367 0373 0374 0377 0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0414 0415 0424 0429 0430 0433 0434 0435 0438 0442 0446 0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 002

(5) Configuration definition **CONF 001 Config. 01 concerns aircraft on which modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is not embodied. **CONF 002 Config. 02 concerns aircraft on which modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 574106A01R03 2 Supplementary kit 574106A01S01 2 Supplementary kit 574106A01S02 2 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 574106A03R04 2 Supplementary kit 574106A03S01 2 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 3 5

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# @A340 SERVICE BULLETIN C. REASON (1) History During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production solution configuration. The intention of the production solution was also proposed by Service Bulletin No. A340-57-4036 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod. No. 55306 S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and pre Mod. No. 55792 S18775 (REINFORCE FUSELAGE AT FR.40 (SERIAL SOLUTION)). (2) Objective/Action This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam fitting at FR40. (3) Advantages Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin A340-57-4089. ALI 57.11.63 is created for Post Mod. Service Bulletin configuration (Post Mod. No. 56467S18944). (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 574106-831-801-001: MODIFICATION (1) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. (2) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. (3) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners, for aircraft with bush installed on hole 5. (4) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 4 5

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# @A340 SERVICE BULLETIN **CONF 002 Task 574106-831-801-001: MODIFICATION (1) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. (2) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. (3) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.) installed on hole 5. (4) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or = 15mm (0.591in.) installed on hole 5. (5) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Task 574106-839-801-001: Administrative - ADDITIONAL WORK (1) Additional Work **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale **CONF 001 AIRBUS strongly recommends not to perform modification before the FC/FH values given in the table below. In case of early embodiment, additional inspection of CWB lower panel might be required before DSG or ISG. CONDITION PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST: Flight Cycles (FC) Flight Hours (FH) A340-300 POST MOD. 41652 AND PRE MOD. 44360 10,250 63,200 A340-200 POST MOD. 41652 AND PRE MOD. 44360 10,250 63,200

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 5 5

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# @A340 SERVICE BULLETIN **CONF 002 AIRBUS strongly recommends not to perform modification before the FC/FH values given in the table below. In case of early embodiment, additional inspection of CWB lower panel might be required before DSG or ISG. CONDITION PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST: Flight Cycles (FC) Flight Hours (FH) A340-300 POST MOD. 44360, PRE MOD. 55306 AND PRE MOD. 55792 10,250 63,200 A340-200 POST MOD. 44360 10,250 63,200 **CONF ALL F. APPROVAL Approved under EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 574106-831-801-001: MODIFICATION Get Access 12.00 On Aircraft On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. 6.00 On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. 12.00 On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners, for aircraft with bush installed on hole 5. 12.00 On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. 6.00 Tests 2.00 Close-Up 15.00 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 6 5

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# @A340 SERVICE BULLETIN
Task 574106-831-801-001: MODIFICATION TOTAL MANHOURS 65.00 ELAPSED TIME (HOURS) 38.00 NOTE: The TOTAL MANHOURS for one aircraft modified is 53.00 hours. Task 574106-839-801-001: Administrative - ADDITIONAL WORK On Aircraft TOTAL MANHOURS 0.00 **CONF 002 Task 574106-831-801-001: MODIFICATION Get Access 12.00 On Aircraft On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. 6.00 On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. 17.50 On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.) installed on hole 5. 17.50
On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or = 15mm (0.591in.) installed on hole 5. 17.50
On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. 6.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 93.50 ELAPSED TIME (HOURS) 42.00 NOTE: The TOTAL MANHOURS for one aircraft modified is 58.50 hours. Task 574106-839-801-001: Administrative - ADDITIONAL WORK On Aircraft Additional Work 0.50 TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 **CONF ALL H. WEIGHT AND BALANCE Not Changed
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 7 5

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# @A340 SERVICE BULLETIN I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11 21-20-00 21-53-18 27-84-45 28-25-00 32-12-00 36-12-41 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 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Service Bulletin (SB) A340-57-4036 A340-57-4089 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11 21-20-00 21-53-18 27-84-45 28-25-00 32-12-00 36-12-41 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 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Service Bulletin (SB) A340-57-4036 A340-57-4089 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12 **CONF ALL K. PUBLICATION AFFECTED Not Changed L. INTERCHANGEABILITY/MIXABILITY Not Applicable DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 8 5

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# @A340 SERVICE BULLETIN M. SPARES None

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 9 5

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# @A340 SERVICE BULLETIN

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DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 10 5

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# @A340 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : Kit 574106A01R03 Supplementary kit 574106A01S01 Supplementary kit 574106A01S02 Kit 574106A03R04 Supplementary kit 574106A03S01 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability Kit Held by the Operator Supplementary Kits Required Latest Status of Kit INST/DISP 574106A01R01 574106A01S01 AND 574106A01S02 574106A01R03 574106A01R01 AND 574106A01S01 574106A01S02 574106A01R03 574106A01R02 574106A01S02 574106A01R03 574106A01R03 None 574106A01R03 NOTE: Kit 574106A01R03 does not require a Kit 574106A01S02 because Kit 574106A01S02 is included in Kit 574106A01R03. Kit Held by the Operator Supplementary Kits Required Latest Status of Kit INST/DISP 574106A03R03 574106A03S01 574106A03R04 574106A03R04 None 574106A03R04 NOTE: Kit 574106A03R04 does not require a Kit 574106A03S01 because Kit 574106A03S01 is included in Kit 574106A03R04. Kit 574106A01R03 Cost 439.00 USD Availability 180 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. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 11 5

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# @A340 SERVICE BULLETIN The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Supplementary kit 574106A01S01 Cost 91.00 USD Availability 180 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. Supplementary kit 574106A01S02 Cost 590.00 USD Availability 180 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 574106A03R04 Cost 2,790.00 USD Availability 180 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. Supplementary kit 574106A03S01 Cost 730.00 USD Availability 180 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: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 12 5

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# @A340 SERVICE BULLETIN C. LIST OF COMPONENTS Kit 574106A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 27 ASNA2531-6 1 NUT 31 ASNA2531-5 1 NUT 33 ASNA2529-6 1 NUT 35 F5332433420000 1 WASHER 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 60 EN6115-6Y17 1 BOLT 61 EN6115-6Y18 1 BOLT 62 EN6115V6Y15 1 BOLT 66 NSA5368-616A 1 WASHER 67 NSA5368-616B 1 WASHER 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER 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 574106A03R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 27 ASNA2531-6 2 NUT 29 EN6115-6Y10 1 BOLT 31 ASNA2531-5 1 NUT 33 ASNA2529-6 1 NUT 35 F5332433420000 1 WASHER 36 EN6115V6X6 1 BOLT 37 F5332433520000 1 PLUG 38 F5332433520200 1 PLUG 39 F5332433520400 1 PLUG 40 F5332433520600 1 PLUG 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 63 EN6115-6Y14 1 BOLT 64 EN6115-6Y11 1 BOLT 65 EN6115-6Y9 1 BOLT 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER 70 NSA5372-616A 2 WASHER 71 NSA5372-616B 2 WASHER
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 13 5

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# @A340 SERVICE BULLETIN NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Supplementary kit 574106A01S01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 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. Supplementary kit 574106A01S02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 60 EN6115-6Y17 1 BOLT 61 EN6115-6Y18 1 BOLT 62 EN6115V6Y15 1 BOLT 66 NSA5368-616A 1 WASHER 67 NSA5368-616B 1 WASHER 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER 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. Supplementary kit 574106A03S01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 63 EN6115-6Y14 1 BOLT 64 EN6115-6Y11 1 BOLT 65 EN6115-6Y9 1 BOLT 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER 70 NSA5372-616A 2 WASHER 71 NSA5372-616B 2 WASHER NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 14 5

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# @A340 SERVICE BULLETIN 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 Polysulfid 09-002 As required Interfay Sealant 09-005 As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting Fillet Consistency 09-016 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Solvent General Purpose 11-026 0 Chemical Conversion Coating Yellow Aluminum 13-002 0 Anti-Corrosion Primer (polyurethane) 16-001 As required Internal Top Coat 16-002 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools 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. - Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6. Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for cold working : DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 15 5

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# @A340 SERVICE BULLETIN NOTE: For definition of capital, durable and expendable tools, refer to SIL 51-012. Operators interested in obtaining the FTI tool kit should contact : Fatigue Technology Inc. 401 Andover Park West SEATTLE, WA 98188-7605 USA E.Mail : sales@fatiguetech.com E.Mail : aog@fatiguetech.com Phone : (1) 206 2462010 Fax : (1) 206 2449886 - Capital tooling : ref. FTI-A330-57-3098-1 This tool reference include all capital, durable and expendable tooling kits regardless of effectivity but capital tooling is normally already and previously bought by the operator as a long term investment or loaned from FTI. - Durable tooling : ref. DK-A330-00057-3098-1 - Expendable tooling : ref. EK-A330-57-3098-1 (3) Special Tools None

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 16 5

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# @A340 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 574106-831-801-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 65.00 ELAPSED TIME (HOURS) 38.00 **CONF 002 Manpower TOTAL MANHOURS 93.50 ELAPSED TIME (HOURS) 42.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 574106-831-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 17 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 Sealant-Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201 Consumable Material List (CML) Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12 (a) 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. (b) For the specification of the material numbers (Mat. No.) refer to the CML. (c) Clean the surfaces to be sealed with Solvent General Purpose 11-026 As required (d) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent General Purpose 11-026 As required (e) Drill and deburr the holes (Refer to SRM 51-44-11). (f) Remove and install the fasteners (Refer to SRM 51-42-11). (g) Apply Sealant-Brush Consistency 09-013 As required

on all the fasteners to be installed (wet assembly). (h) For the oversize and alternative fasteners (Refer to SRM 51-43-00). (i) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 18 5

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# @A340 SERVICE BULLETIN (j) Do the cold expansion of the holes (Refer to SRM 51-48-00). (k) Apply the sealant (Refer to SRM 51-76-12). (l) Install the plug with liquid nitrogen (Refer to PMS 01-05-05). (2) Subtask 574106-900-002-001 - Documentation Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 574106-831-001-001 - 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 Sealant-Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201 Consumable Material List (CML) Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12 (a) 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. (b) For the specification of the material numbers (Mat. No.) refer to the CML. (c) Clean the surfaces to be sealed with Solvent General Purpose 11-026 As required

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 19 5

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# @A340 SERVICE BULLETIN (d) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent General Purpose 11-026 As required (e) Drill and deburr the holes (Refer to SRM 51-44-11). (f) Remove and install the fasteners (Refer to SRM 51-42-11). (g) Apply Sealant-Brush Consistency 09-013 As required

on all the fasteners to be installed (wet assembly). (h) For the oversize and alternative fasteners (Refer to SRM 51-43-00). (i) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201). (j) Do the cold expansion of the holes (Refer to SRM 51-48-00). (k) Apply the sealant (Refer to SRM 51-76-12). (l) Install the plug with liquid nitrogen (Refer to PMS 01-05-05). (2) Subtask 574106-900-002-001 - Documentation 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 574106-831-003-001 - Preparation Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24, Page Block 201 21-20-00, Page Block 201 21-53-18, Page Block 401 27-84-45, Page Block 401 28-25-00, Page Block 301 32-12-00, Page Block 201 36-12-41, Page Block 401 53-35-13, Page Block 401 57-17-11, Page Block 401 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 20 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) Put the access platform(s) in position. (c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201).(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (e) Do the preparation procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (i) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (j) Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page Block 401). (k) Get access to the work area. **CONF 002 (1) Subtask 574106-831-003-001 - Preparation Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24, Page Block 201 21-20-00, Page Block 201 21-53-18, Page Block 401 27-84-45, Page Block 401 28-25-00, Page Block 301 32-12-00, Page Block 201 36-12-41, Page Block 401 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) Put the access platform(s) in position. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 21 5

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# @A340 SERVICE BULLETIN (c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201).(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (e) Do the preparation procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401). (g) Remove the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (i) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (j) Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page Block 401). (k) Get access to the work area. **CONF ALL C. PROCEDURE NOTE: For aircraft on which temporary repair (covered by Repair Design Approval Sheet (RAS)) have been done following accomplishment of Inspection Service Bulletin No. A340-57-4089, the operator must contact AIRBUS repair office in order to issue definitive RAS after embodiment of this Modification Service Bulletin. **CONF 001 (1) Subtask 574106-831-004-001 - On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 22 5

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# @A340 SERVICE BULLETIN
References Fig. A-FCAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access Sheet 01
Fig. A-FDAAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access Sheet 01
(a) On RH side, remove the air conditioning duct. Refer to Figure Fig. A-FCAAA 1 Remove : 1 Duct Item (8) Retain 1 Insulation Item (9) Retain 1 Nut Item (10) Retain 1 Bolt Item (11) Retain 1 Washer Item (12) Retain 2 Screw Item (13) Retain 2 Washer Item (14) Retain 2 Nut Item (15) Retain 1 Clamp Item (16) Retain 1 Clamp Item (17) Retain NOTE (01): Disconnect and move the rod Items (18) and (19) without removal. NOTE (02): Remove the Insulation Item (9) with associated clamp Item (17) from the duct Item (8) only if necessary. NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). (b) On RH side, remove the air ventilation duct. Refer to Figure Fig. A-FDAAA

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 23 5

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# @A340 SERVICE BULLETIN
1 Remove : 1 Duct Item (20) Retain 8 Clamp Item (21) Retain 4 Clamp Item (22) Retain 2 Sleeve Item (23) Retain 1 Sleeve Item (24) Retain (c) On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401). (d) Put the blanking plugs on the disconnected line ends. (2) Subtask 574106-831-005-001 - On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 574106A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 27 ASNA2531-6 1 NUT 31 ASNA2531-5 1 NUT 33 ASNA2529-6 1 NUT 35 F5332433420000 1 WASHER 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 60 EN6115-6Y17 1 BOLT 61 EN6115-6Y18 1 BOLT 62 EN6115V6Y15 1 BOLT 66 NSA5368-616A 1 WASHER 67 NSA5368-616B 1 WASHER 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 24 5

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# @A340 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid 09-002 As required Sealant-Brush Consistency 09-013 As required References Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FBAAA Replacement of the fasteners of the Keel Beam (hole 5 without bush) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.) shall be used. NOTE: The installed fasteners shall be checked in accordance with the requirements of SRM 51-42-11 Paragraph 7.C.(g).Table.14 to ensure that adequate thread protrusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g) Table.14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two kits Kit 574106A01R03 are necessary to modify one aircraft. (a) Inspect the hole 5. Refer to Figure Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 1 Remove : 1 Bolt Item (41) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 25 5

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# @A340 SERVICE BULLETIN
3 Do a rotating probe inspection (Refer to NTM 51-10-18) through all the layers. a If no crack is detected, do the operations given in paragraph 3.C.(2)(b). b If crack is detected do the operations given in paragraph 3.C.(2)(c). (b) No crack, oversize the hole 5 in the keel beam. Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 1 Ream the hole at the level of the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). 3 Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). 4 Clean the drilled area. 5 Install : 1 Bolt EN6115V6Y15 Item 62 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616A Item 68 or 1 Washer NSA5368PD616B Item 69 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (c) Crack detected, oversize the hole 5 in the keel beam. Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 26 5

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# @A340 SERVICE BULLETIN
1 Ream the hole 5 at the level of the keel beam only to a diameter comprised between 15mm (0.591in.) and 15.2mm (0.598in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 0.5mm (0.02in.) and 0.7mm (0.028in.). 2 Do a rotating probe inspection at the level of the keel beam only (Refer to NTM 51-10-18). a Crack finding, contact AIRBUS. b No crack finding, oversize the hole in the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). c Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). <1> Crack finding, contact AIRBUS. <2> No crack finding, do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). <3> Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) <4> Install : 1 Bolt EN6115V6Y15 Item 62 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616A Item 68 or 1 Washer NSA5368PD616B Item 69 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 27 5

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# @A340 SERVICE BULLETIN (d) Inspect holes 6 and 7 Refer to Figure Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (3) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraphes 3.C.(2)(e) and (f). (e) Do the cold working of the hole 6. Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 1 Ream the hole to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y17 Item 60 or 1 Bolt EN6115-6Y18 Item 61 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 28 5

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# @A340 SERVICE BULLETIN
1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616A Item 66 or 1 Washer NSA5368-616B Item 67 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (f) Install the fastener in hole 7. Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required NOTE (03): If necessary, contact AIRBUS for a specific washer solution. (g) For the report after modification, refer to APPENDIX01 - Inspection Report .
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 29 5

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# @A340 SERVICE BULLETIN (3) Subtask 574106-831-006-001 - On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners, for aircraft with bush installed on hole 5. Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 574106A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 27 ASNA2531-6 1 NUT 31 ASNA2531-5 1 NUT 33 ASNA2529-6 1 NUT 35 F5332433420000 1 WASHER 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 60 EN6115-6Y17 1 BOLT 61 EN6115-6Y18 1 BOLT 62 EN6115V6Y15 1 BOLT 66 NSA5368-616A 1 WASHER 67 NSA5368-616B 1 WASHER 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid 09-002 As required Sealant-Brush Consistency 09-013 As required References Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FBBAA Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 30 5

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# @A340 SERVICE BULLETIN After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.) shall be used. NOTE: The installed fasteners shall be checked in accordance with the requirements of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that adequate thread protrusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two kits Kit 574106A01R03 are necessary to modify one aircraft. NOTE: If the diameter of the bush is superior than 13mm (0.512in.) or if the bush is installed in other layers than keel beam fitting only, contact AIRBUS. (a) Inspect the hole 5. Refer to Figure Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 1 Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection (Refer to NTM 51-10-18) through all the layers. a If crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraph 3.C.(3)(b). (b) No crack finding, oversize the hole in the keel beam. Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 1 Ream the hole at the level of the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.)
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 31 5

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# @A340 SERVICE BULLETIN
2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). 3 Oversize the hole through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) 4 Install : 1 Washer F5332433420000 Item 35 1 Bolt EN6115V6Y15 Item 62 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616A Item 68 or 1 Washer NSA5368PD616B Item 69 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (c) Inspect holes 6 and 7. Refer to Figure Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (41) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 32 5

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# @A340 SERVICE BULLETIN b If no crack is detected, do the operations given in the paragraphes 3.C.(3)(d) and (e). (d) Do the cold working of the hole 6. Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 1 Ream the hole to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. Clean the drilled area. 2 Do the cold working of the hole (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 3 Ream the hole to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 4 Clean the drilled area. 5 Install : 1 Bolt EN6115-6Y17 Item 60 or 1 Bolt EN6115-6Y18 Item 61 1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616A Item 66 or 1 Washer NSA5368-616B Item 67 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 33 5

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# @A340 SERVICE BULLETIN (e) Install the fastener in hole 7. Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required NOTE (03): If necessary, contact AIRBUS for a specific washer solution. (f) For the report after modification, refer to APPENDIX01 - Inspection Report . (4) Subtask 574106-831-007-001 - On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401 Fig. A-FCAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access Sheet 01

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 34 5

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# @A340 SERVICE BULLETIN
References Fig. A-FDAAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access Sheet 01
(a) Remove the blanking plugs on the disconnected line ends. (b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401). (c) On RH side, install (if removed) the air ventilation duct. Refer to Figure Fig. A-FDAAA 1 Install : 1 Duct Item (20) 8 Clamp Item (21) 4 Clamp Item (22) 2 Sleeve Item (23) 1 Sleeve Item (24) NOTE: Items (20) thru (24) were retained at removal. (d) On RH side, install (if removed) the air conditioning duct. Refer to Figure Fig. A-FCAAA 1 Install : 1 Duct Item (8) 1 Insulation Item (9) 1 Nut Item (10) 1 Bolt Item (11) 1 Washer Item (12) 2 Screw Item (13) 2 Washer Item (14) 2 Nut Item (15) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 35 5

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# @A340 SERVICE BULLETIN 1 Clamp Item (16) 1 Clamp Item (17) NOTE (01): Reconnect the rod Items (18) and (19). NOTE (02): For the installation of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). NOTE (03): Items (8) thru (17) were retained at removal. **CONF 002 (1) Subtask 574106-831-004-002 - On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401 Fig. A-FCAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access Sheet 01
Fig. A-FDAAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access Sheet 01

NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02 embodiment recommendation. (a) On RH side, remove the air conditioning duct. Refer to Figure Fig. A-FCAAA 1 Remove : 1 Duct Item (8) Retain 1 Insulation Item (9) Retain 1 Nut Item (10) Retain 1 Bolt Item (11) Retain DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 36 5

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# @A340 SERVICE BULLETIN 1 Washer Item (12) Retain 2 Screw Item (13) Retain 2 Washer Item (14) Retain 2 Nut Item (15) Retain 1 Clamp Item (16) Retain 1 Clamp Item (17) Retain NOTE (01): Disconnect and move the rod Items (18) and (19) without removal. NOTE (02): Remove the Insulation Item (9) with associated clamp Item (17) from the duct Item (8) only if necessary. NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). (b) On RH side, remove the air ventilation duct. Refer to Figure Fig. A-FDAAA 1 Remove : 1 Duct Item (20) Retain 8 Clamp Item (21) Retain 4 Clamp Item (22) Retain 2 Sleeve Item (23) Retain 1 Sleeve Item (24) Retain (c) On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401). (d) Put the blanking plugs on the disconnected line ends.

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 37 5

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# @A340 SERVICE BULLETIN (2) Subtask 574106-831-005-002 - On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft without bush installed on hole 5. Manpower Resources Manhours 17.50 Minimum number of person 1 Subtask elapsed time 17.50 Skills AIRFRAME Material necessary to do the job Kit 574106A03R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 27 ASNA2531-6 2 NUT 29 EN6115-6Y10 1 BOLT 31 ASNA2531-5 1 NUT 33 ASNA2529-6 1 NUT 35 F5332433420000 1 WASHER 36 EN6115V6X6 1 BOLT 37 F5332433520000 1 PLUG 38 F5332433520200 1 PLUG 39 F5332433520400 1 PLUG 40 F5332433520600 1 PLUG 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 63 EN6115-6Y14 1 BOLT 64 EN6115-6Y11 1 BOLT 65 EN6115-6Y9 1 BOLT 68 NSA5368PD616A 1 WASHER 69 NSA5368PD616B 1 WASHER 70 NSA5372-616A 2 WASHER 71 NSA5372-616B 2 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid 09-002 As required Interfay Sealant 09-005 As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting Fillet Consistency 09-016 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 38 5

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# @A340 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti-Corrosion Primer (polyurethane) 16-001 As required Internal Top Coat 16-002 As required References Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FBCAA Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FBDAA Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.) shall be used. NOTE: The installed fasteners shall be checked in accordance with the requirements of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that adequate thread protrusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two kits Kit 574106A03R04 are necessary to modify one aircraft. (a) Inspect the hole 5. Refer to Figure Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02 1 Remove : 1 Bolt Item (3) Discard DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 39 5

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# @A340 SERVICE BULLETIN 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(2)(b). b If a crack is detected, do the operations given in paragraph 3.C.(2)(f). (b) No crack, oversize the hole 5 in the keel beam. Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05 1 Ream the hole 5 at the level of the keel beam only to a diameter comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). 3 Oversize the hole 5 through all the layers to a diameter comprised between 9.784mm (0.385in.) and 9.823mm (0.387in.) 4 Install : 1 Bolt EN6115V6X6 Item 36 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616A Item 68 or 1 Washer NSA5368PD616B Item 69 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 40 5

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# @A340 SERVICE BULLETIN (c) Inspect holes A, 6 and 7. Refer to Figure Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (3) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A, 6 and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(2)(d) and (e). (d) Do the cold working of the holes A and 6. Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05 1 Ream the holes A and 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the holes A and 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the holes A and 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 41 5

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# @A340 SERVICE BULLETIN
6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Bolt EN6115-6Y9 Item 65 or 1 Bolt EN6115-6Y10 Item 29 2 Nut ASNA2531-6 Item 27 2 Washer NSA5372-616A Item 70 or 2 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (e) Install the fastener in hole 7. Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA Sheet 04 and Fig. A-FBCAA Sheet 05 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 42 5

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# @A340 SERVICE BULLETIN NOTE (02): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (f) Crack detected at existing diameter. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Ream the hole 5 through all the layer at diameter 9.5mm (0.374in.). 2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(2)(g). b If a crack is detected at diameter 9.5mm (0.374in.), do the operations given in paragraph 3.C.(2)(l). (g) No crack detected at diameter 9.5mm (0.374in.) for hole 5. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraph 3.C.(2)(h). (h) Do the cold working of the hole 6. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 43 5

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# @A340 SERVICE BULLETIN
3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 11.5mm (0.4528in.) and 11.518mm (0.4535in.) 7 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. 8 Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum 13-002 As required

. 9 Install : 1 Plug F5332433520000 Item 37 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 37 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 37 and the structure apply : Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply :
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 44 5

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# @A340 SERVICE BULLETIN
Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 37 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 37 with : Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (i) Inspect holes A and 7. Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(2)(j) and (k). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 45 5

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# @A340 SERVICE BULLETIN (j) Do the cold working of the hole A. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (k) Install the fastener in hole 7. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 46 5

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# @A340 SERVICE BULLETIN
2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (l) Crack detected at diameter 9.5mm (0.374in.) for hole 5. 1 Ream the hole 5 through all the layers at diameter 11.1mm (0.437in.). 2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(2)(m). b If a crack is detected, do the operations given in paragraph 3.C.(2)(r). (m) No crack detected at diameter 11.1mm (0.437in.) for hole 5. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraph 3.C.(2)(n). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 47 5

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# @A340 SERVICE BULLETIN (n) Do the cold working of the hole 6. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 13.1mm (0.5157in.) and 13.118mm (0.5165in.). 7 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. 8 Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum 13-002 As required

. 9 Install : 1 Plug F5332433520200 Item 38 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 38 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 38 and the structure apply : DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 48 5

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# @A340 SERVICE BULLETIN Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply : Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 38 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 38 with : Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (o) Inspect holes A and 7. Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 49 5

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# @A340 SERVICE BULLETIN 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(2)(p) and (q). (p) Do the cold working of the hole A. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 50 5

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# @A340 SERVICE BULLETIN NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (q) Install the fastener in hole 7. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (r) Crack detected at diameter 11.1mm (0.437in.) for hole 5. 1 Ream the hole 5 through all the layers at diameter 13.1mm (0.516in.). 2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(2)(s). b If crack is detected, do the operations given in paragraph 3.C.(2)(x). (s) No crack detected at diameter 13.1mm (0.516in.) for hole 5. 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (3) Discard
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 51 5

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# @A340 SERVICE BULLETIN 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraph 3.C.(2)(t). (t) Do the cold working of the hole 6. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 15mm (0.5906in.) and 15.018mm (0.5913in.). 7 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. 8 Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum 13-002 As required

. 9 Install : 1 Plug F5332433520400 Item 39 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 52 5

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# @A340 SERVICE BULLETIN
1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 39 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 39 and the structure apply : Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply : Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 39 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 39 with : Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 53 5

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# @A340 SERVICE BULLETIN (u) Inspect holes A and 7. Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(2)(v) and (w). (v) Do the cold working of the hole A. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 54 5

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# @A340 SERVICE BULLETIN
1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (w) Install the fastener in hole 7. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (x) Crack detected at diameter 13.1mm (0.516in.) for hole 5. 1 Ream the hole 5 through all the layers at diameter of 15mm (0.591in.).

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 55 5

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# @A340 SERVICE BULLETIN
2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(2)(y). b If crack is detected, contact AIRBUS. (y) No crack detected at diameter 15mm (0.591in.) for hole 5. 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in paragraph 3.C.(2)(z). (z) Do the cold working of the hole 6. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA Sheet 04 and Fig. A-FBDAA Sheet 05 1 Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 17mm (0.6693in.) and 17.018mm (0.67in.). 7 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 56 5

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# @A340 SERVICE BULLETIN
8 Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum 13-002 As required

. 9 Install : 1 Plug F5332433520600 Item 40 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 40 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 40 and the structure apply : Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply : Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 40 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 40 with :
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 57 5

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# @A340 SERVICE BULLETIN
Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (aa) Inspect holes A and 7. Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(2)(ab) and (ac). (ab) Do the cold working of the hole A. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 58 5

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# @A340 SERVICE BULLETIN
4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (ac) Install the fastener in hole 7. Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 59 5

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# @A340 SERVICE BULLETIN NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (3) Subtask 574106-831-010-001 - On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.) installed on hole 5. Manpower Resources Manhours 17.50 Minimum number of person 1 Subtask elapsed time 17.50 Skills AIRFRAME Material necessary to do the job Kit 574106A03R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 27 ASNA2531-6 2 NUT 31 ASNA2531-5 1 NUT 39 F5332433520400 1 PLUG 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 63 EN6115-6Y14 1 BOLT 64 EN6115-6Y11 1 BOLT 70 NSA5372-616A 2 WASHER 71 NSA5372-616B 2 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid 09-002 As required Corrosion Inhibitive Interfay Sealant 09-005 As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting Fillet Consistency 09-016 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Internal Top Coat 16-002 As required
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 60 5

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# @A340 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FBEAA Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.) shall be used. NOTE: The installed fasteners shall be checked in accordance with the requirements of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that adequate thread protrusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02 embodiment recommendation. NOTE: Description below is given for one side of the aircraft, two kits Kit 574106A03R04 are necessary to modify one aircraft. (a) Inspect the hole 5. Refer to Figure Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02 1 Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard 2 Remove the sealant and clean the hole.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 61 5

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# @A340 SERVICE BULLETIN
3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(3)(b). b If a crack is detected, contact AIRBUS. (b) No crack detected at original diameter on hole 5. Refer to Figure Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (41) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If no crack is detected, do the operations given in paragraph 3.C.(3)(c). b If a crack is detected, contact AIRBUS. (c) Do the cold working of the hole 6. 1 Ream the hole 6 to the starting hole for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 15mm (0.5905in.) and 15.018mm (0.5913in.). 7 Clean the drilled area. 8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 62 5

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# @A340 SERVICE BULLETIN
9 Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum 13-002 As required

. 10 Install : 1 Plug F5332433520400 Item 39 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 39 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 39 and the structure apply : Corrosion Inhibitive Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply : Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 39 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 39 with : DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 63 5

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# @A340 SERVICE BULLETIN
Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (d) Inspect holes A and 7. Refer to Figure Fig. A-FBEAA Sheet 01Fig. A-FBEAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(3)(e) and (f). (e) Do the cold working of the hole A. Refer to Figure Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 03 and Fig. A-FBEAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 64 5

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# @A340 SERVICE BULLETIN
4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (f) Install the fastener in hole 7. Refer to Figure Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 03 and Fig. A-FBEAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 65 5

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# @A340 SERVICE BULLETIN NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (4) Subtask 574106-831-011-001 - On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or = 15mm (0.591in.) installed on hole 5. Manpower Resources Manhours 17.50 Minimum number of person 1 Subtask elapsed time 17.50 Skills AIRFRAME Material necessary to do the job Kit 574106A03R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 27 ASNA2531-6 2 NUT 31 ASNA2531-5 1 NUT 40 F5332433520600 1 PLUG 51 EN6115-5-13 1 BOLT 52 EN6115-5-14 1 BOLT 63 EN6115-6Y14 1 BOLT 64 EN6115-6Y11 1 BOLT 70 NSA5372-616A 2 WASHER 71 NSA5372-616B 2 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid 09-002 As required Corrosion Inhibitive Interfay Sealant 09-005 As required Sealant-Brush Consistency 09-013 As required Corrosion Inhibiting Fillet Consistency 09-016 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Internal Top Coat 16-002 As required
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 66 5

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# @A340 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FBFAA Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.) shall be used. NOTE: The installed fasteners shall be checked in accordance with the requirements of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that adequate thread protrusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02 embodiment recommendation. NOTE: Description below is given for one side of the aircraft, two kits Kit 574106A03R04 are necessary to modify one aircraft. (a) Inspect the hole 5. Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02 1 Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard 2 Remove the sealant and clean the hole.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 67 5

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# @A340 SERVICE BULLETIN
3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). a If no crack is detected, do the operations given in paragraph 3.C.(4)(b). b If a crack is detected, contact AIRBUS. (b) No crack detected at original diameter for hole 5 Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02 1 Remove the fastener of hole 6. a Remove: 1 Bolt Item (41) Discard 1 Nut Item (4) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating probe inspection through all the layers of hole 6 (Refer to NTM 51-10-01). a If no crack is detected, do the operations given in paragraph 3.C.(4)(c). b If a crack is detected, contact AIRBUS. (c) Do the cold working of the hole 6 1 Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. 4 Ream the hole 6 to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Ream the hole 5 through all the layers to a diameter comprised between 17mm (0.6693in.) and 17.018mm (0.67in.). 7 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 68 5

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# @A340 SERVICE BULLETIN
8 Protect the hole with : Chemical Conversion Coating Yellow Aluminum 13-002 As required

9 Install : 1 Plug F5332433520600 Item 40 1 Bolt EN6115-6Y11 Item 64 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Install the plug Item 40 with liquid nitrogen (Refer to PMS 01-05-05). NOTE (02): Between the plug Item 40 and the structure apply : Corrosion Inhibitive Interfay Sealant 09-005 As required NOTE (03): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (04): After assembly in the hole apply : Anti-Corrosion Primer (polyurethane) 16-001 As required
and Internal Top Coat 16-002 As required NOTE (05): In the hole on the edge of the plug Item 40 do a seal bead with : Corrosion Inhibiting Fillet Consistency 09-016 As required NOTE (06): Do a seal bead on the external edge of the plug Item 40 with :
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 69 5

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# @A340 SERVICE BULLETIN
Fuel Tank Sealant Polysulfid 09-002 As required and Adhesion Promoter For Polysulfide Sealant 09-028 As required
NOTE (07): Coat the nut and washer with : Fuel Tank Sealant Polysulfid 09-002 As required (d) Inspect holes A and 7. Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02 1 Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard 2 Remove the sealant and clean the holes. 3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). a If a crack is detected, contact AIRBUS. b If no crack is detected, do the operations given in the paragraphes 3.C.(4)(d) and (e). (e) Do the cold working of the hole A. Refer to Figure Fig. A-FBFAA Sheet 01, Fig. A-FBFAA Sheet 03 and Fig. A-FBFAA Sheet 04 1 Ream the hole A to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). Use tool list No. DK-A340-57-4106-1. 2 Clean the drilled area. 3 Do the cold working of the hole A (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1. DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 70 5

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# @A340 SERVICE BULLETIN
4 Ream the hole A to the final hole diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). Use tool list No. DK-A340-57-4106-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115-6Y14 Item 63 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616A Item 70 or 1 Washer NSA5372-616B Item 71 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (f) Install the fastener in hole 7. Refer to Figure Fig. A-FBFAA Sheet 01, Fig. A-FBFAA Sheet 03 and Fig. A-FBFAA Sheet 04 1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). 2 Install : 1 Bolt EN6115-5-13 Item 51 or 1 Bolt EN6115-5-14 Item 52 1 Nut ASNA2531-5 Item 31 NOTE (01): Before installation of the fasteners, apply : Sealant-Brush Consistency 09-013 As required (wet assembly). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 71 5

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# @A340 SERVICE BULLETIN NOTE (02): Coat the nut with : Fuel Tank Sealant Polysulfid 09-002 As required (5) Subtask 574106-831-007-001 - On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401 Fig. A-FCAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access Sheet 01
Fig. A-FDAAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access Sheet 01
(a) Remove the blanking plugs on the disconnected line ends. (b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401). (c) On RH side, install (if removed) the air ventilation duct. Refer to Figure Fig. A-FDAAA 1 Install : 1 Duct Item (20) 8 Clamp Item (21) 4 Clamp Item (22) 2 Sleeve Item (23) 1 Sleeve Item (24) NOTE: Items (20) thru (24) were retained at removal.

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 72 5

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# @A340 SERVICE BULLETIN (d) On RH side, install (if removed) the air conditioning duct. Refer to Figure Fig. A-FCAAA 1 Install : 1 Duct Item (8) 1 Insulation Item (9) 1 Nut Item (10) 1 Bolt Item (11) 1 Washer Item (12) 2 Screw Item (13) 2 Washer Item (14) 2 Nut Item (15) 1 Clamp Item (16) 1 Clamp Item (17) NOTE (01): Reconnect the rod Items (18) and (19). NOTE (02): For the installation of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). NOTE (03): Items (8) thru (17) were retained at removal. **CONF ALL D. TEST **CONF 001 (1) Subtask 574106-831-014-001 - Test Manpower Resources Skills NON SPECIFIC

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 73 5

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# @A340 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 21-20-00, Page Block 201 21-20-00, Page Block 201 21-53-18, Page Block 401 27-84-45, Page Block 201 27-84-45, Page Block 401 28-25-00, Page Block 301 36-12-41, Page Block 401 57-17-11, Page Block 401 57-17-11, Page Block 401 (a) Preparation 1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). 2 Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). 3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page Block 201). 4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (b) Tests 1 Do the test after the removal/installation of the pack discharge temperaturesensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401). 2 Do the test after the removal/installation of the APU bleed air ducts (Refer to AMM 36-12-41 Page Block 401). 3 Do the test after the removal/installation of the covers (147AZ and 148AZ) (Refer to AMM 57-17-11 Page Block 401). 4 Do the test after the removal/installation of the torque shaft assy (5010CW and 5070CW)(Refer to AMM 27-84-45 Page Block 401). 5 Do the test after the removal/installation of the air conditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). **CONF 002 (1) Subtask 574106-831-014-001 - Test Manpower Resources Skills NON SPECIFIC

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 74 5

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# @A340 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 21-20-00, Page Block 201 21-20-00, Page Block 201 21-53-18, Page Block 401 27-84-45, Page Block 201 27-84-45, Page Block 401 28-25-00, Page Block 301 36-12-41, Page Block 401 57-17-11, Page Block 401 57-17-11, Page Block 401 (a) Preparation 1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). 2 Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). 3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45 Page Block 201). 4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (b) Tests 1 Do the test after the removal/installation of the pack discharge temperaturesensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401). 2 Do the test after the removal/installation of the APU bleed air ducts (Refer to AMM 36-12-41 Page Block 401). 3 Do the test after the removal/installation of the covers (147AZ and 148AZ) (Refer to AMM 57-17-11 Page Block 401). 4 Do the test after the removal/installation of the torque shaft assy (5010CW and 5070CW)(Refer to AMM 27-84-45 Page Block 401). 5 Do the test after the removal/installation of the air conditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 574106-831-015-001 - Close-up Manpower Resources Skills NON SPECIFIC
DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 75 5

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# @A340 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-41-53 21-53-18, Page Block 401 32-12-00, Page Block 201 36-12-41, Page Block 401 53-35-13, Page Block 401 (a) Do the close-up procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401). (b) Do the close-up procedure as specified in removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page Block 401). (c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Remove the access platform(s). (g) Restore the systems and the aircraft to normal operating condition. **CONF 002 (1) Subtask 574106-831-015-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 21-53-18, Page Block 401 32-12-00, Page Block 201 36-12-41, Page Block 401 53-35-13, Page Block 401 (a) Do the close-up procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401). (b) Do the close-up procedure as specified in removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page Block 401). (c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 76 5

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# @A340 SERVICE BULLETIN (e) Make sure that the work areas are clean and clear of tools and other items of equipment. (f) Remove the access platform(s). (g) Restore the systems and the aircraft to normal operating condition.

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 77 5

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# @A340 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 78 5

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# @A340 SERVICE BULLETIN Task 574106-839-801-001 - Administrative - ADDITIONAL WORK **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 0.00 **CONF 002 Manpower TOTAL MANHOURS 0.50 ELAPSED TIME (HOURS) 0.50 **CONF ALL A. GENERAL **CONF 001 None **CONF 002 (1) Subtask 574106-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 None **CONF 002 None

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 79 5

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# @A340 SERVICE BULLETIN **CONF ALL C. PROCEDURE **CONF 001 None **CONF 002 (1) Subtask 574106-839-002-002 - Additional Work Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Additional work might be required by this revision for aircraft in configuration 002 of Service Bulletin No. A340-57-4106 revision No. 01 and revision No. 02 (POST MOD 44360 PRE MOD 49202), that is MSN from 176 to 483. Additional work is required for any of those aircraft if the SUBTASK 574106-831-005 002, 574106-831-010 001 or 574106-831-011 001 has been accomplished as per this Service Bulletin at revision No. 01 or revision No. 02 and if during the accomplishment of the subtask a crack was detected at hole 5 and a rototest inspection was not performed to the adjacent hole 6 before doing the cold working of the hole 6. Please contact AIRBUS for advice on the Additional Work. **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 None **CONF 002 None DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 80 5

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# @A340 SERVICE BULLETIN

**CONF ALL

FR39.2



### B FR40.2

542HH 

### A

**B (9)** 

**(17) (8)**  **(15) (18)** 

**(15) (13)**  **(14)**
**(13) (14)**  **(19)**
**(10) (11)**  **(12) (16)**  Z192 

### A

F_SB_574106_5_CAAA_01_00 Figure A-FCAAA - Sheet 01 Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 81 5

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# @A340 SERVICE BULLETIN

**CONF ALL



### B **C D**  Z191−Z192 FR40 FR47



### A **B A** 

**D C**  **D (21)**  **(21) (23)**  **(22) (22) (24)** 

**(20)**

F_SB_574106_5_DAAA_01_00 Figure A-FDAAA - Sheet 01 Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 82 5

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# @A340 SERVICE BULLETIN

**CONF 001



### A Z141−142 

### A FR40 FR47



### B **B**

**B**

FR40 DATUM

STGR1 

### C LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40

Y1959

F_SB_574106_5_BAAA_01_00 Figure A-FBAAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 without bush) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 83 5

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# @A340 SERVICE BULLETIN

**CONF 001

FR40 

### D 

### C

Y1959 VIEW INSIDE CENTER TANK AT FR40 

### BEFORE

**BEFORE**

**(1) (2)**  **(4)** SHIM GUSSET

CWB LOWER PANEL

KEEL BEAM FASTENER NOT AFFECTED 

### (3) **(41) D**  HOLE 5 HOLE 6 HOLE 7 STGR 1

STGR 1 SECTION



### D−D FR40 DATUM

F_SB_574106_5_BAAA_02_00 Figure A-FBAAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 without bush) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 84 5

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# @A340 SERVICE BULLETIN

**CONF 001

11.8mm MINIMUM (0.465in.) STGR1 

### 31 **27 35**  FR40

1 STGR1



### D **D C** 

Y1959

EXPANSION SLEEVE INSTALLATION ORIENTATION SCHEMATIC DIAGRAM FASTENER NOT AFFECTED VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STEP 1 DIA 15mm THRU 15.2mm (0.591in. THRU 0.598in.) 

### 33 HOLE 5 HOLE 6 HOLE 7

DETAIL

### E **AFTER**

**AFTER**

APPLY SEALANT MAT No. 09−002B NOTE : 1

STEP 2 DIA. 17mm THRU 17.2mm SECTION 

### D−D

**62**

(0.669in. THRU 0.677in.) 1 1

1

2 IF NECESSARY CONTACT AIRBUS FOR A SPECIFIC WASHER SOLUTION. 2 2



### 51 OR 

### 52 **68** OR 

### 69

**60** OR 

### 61 **66** OR 

### 67

F_SB_574106_5_BAAA_03_00 Figure A-FBAAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 without bush) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 85 5

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# @A340 SERVICE BULLETIN

**CONF 001



### 35

1mm THRU 1.2mm MAX. 

### AFTER

0.5mm THRU 0.7mm DETAIL 

### E

(0.02in. THRU 0.028in.)

(0.039in. THRU 0.047in.) MAX. (0.02in.x 0.02in.) CHAMFER 0.5mm x 0.5mm RADIUS 2mm (0.079in)

F_SB_574106_5_BAAA_04_00 Figure A-FBAAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 without bush) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 86 5

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# @A340 SERVICE BULLETIN

**CONF 001

MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER

F5332433420000

ASNA2529−6 BOLT WASHER

BOLT DESCRIPTION PN

7.849mm (0.309in.) REMARKS

NOMINAL NUT

MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

NUT 12−1−N 10.219mm (0.402in.) SECOND OVERSIZE SECOND OVERSIZE 

### 62 **35 33** 
**51** 7.809mm (0.307in.) 10.219mm (0.402in.)



### 61 **27** 10.177mm (0.401in.)

1 EN6115−6Y18 ASNA2531−6 9.53mm (0.375in.) 10.177mm (0.401in.) 9.60mm (0.378in.) STDN EN6115V6Y15



### 66 NSA5368−616A NSA5368PD616A WASHER 

### 68
**52** NUT 

### 31 ASNA2531−5

OR EN6115−5−13 EN6115−5−14 

### 69 OR NSA5368PD616B



### 67 NSA5368−616B 

### 60 EN6115−6Y17

WASHER BOLT

OR

F_SB_574106_5_BAAA_05_02 Figure A-FBAAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 without bush) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 87 5

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

# @A340 SERVICE BULLETIN

**CONF 001


### A FR40 FR47



### B **B**

**B**

FR40 DATUM

STGR1 

### C LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40

Y1959 

### A Z141−142

F_SB_574106_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 88 5

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

# @A340 SERVICE BULLETIN

**CONF 001

FR40 

### C

Y1959 VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM



### BEFORE

**(1) (41)**  **(2)**

DIA 13mm (0.512in.) 

### (5) **(3) (4)**  SHIM GUSSET

CWB LOWER PANEL

KEEL BEAM FASTENER NOT AFFECTED 

### D **D**

**D−D** SECTION HOLE 5 HOLE 6 HOLE 7 

### BEFORE

STGR 1

STGR 1

F_SB_574106_5_BBAA_02_00 Figure A-FBBAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 89 5

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

# @A340 SERVICE BULLETIN

**CONF 001

11.8mm MINIMUM (0.465in.) 

### 27 **62**
**35** FR40 

### C

EXPANSION SLEEVE INSTALLATION ORIENTATION SCHEMATIC DIAGRAM FASTENER NOT AFFECTED VIEW INSIDE CENTER TANK AT FR40



### 33 

### D−D SECTION

DETAIL

### E

DIA 17mm THRU 17.2mm

(0.669in. THRU 0.677in.) 

### AFTER **AFTER**

STGR 1 STGR1



### D **D** Y1959
FR40 DATUM

HOLE 5 HOLE 6 HOLE 7 1

1 APPLY SEALANT MAT No. 09−002B NOTE : 1 1

1 

### 31

2 IF NECESSARY CONTACT AIRBUS FOR A SPECIFIC WASHER SOLUTION. 2 2



### 51 OR 

### 52 **60** OR 

### 61 **66** OR 

### 67 **68** OR 

### 69

F_SB_574106_5_BBAA_03_00 Figure A-FBBAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 90 5

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

# @A340 SERVICE BULLETIN

**CONF 001



### 35

1mm THRU 1.2mm MAX. (0.02in.x 0.02in.) CHAMFER 0.5mm x 0.5mm 

### AFTER
DETAIL

### E

(0.039in. THRU 0.047in.) MAX. RADIUS 2mm (0.079in)

F_SB_574106_5_BBAA_04_00 Figure A-FBBAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 91 5

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

# @A340 SERVICE BULLETIN

**CONF 001

MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER

F5332433420000

ASNA2529−6 BOLT WASHER

BOLT DESCRIPTION PN

7.849mm (0.309in.) REMARKS

NOMINAL NUT

MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

NUT 12−1−N 10.219mm (0.402in.) SECOND OVERSIZE SECOND OVERSIZE 

### 62 **35 33** 
**51** 7.809mm (0.307in.) 10.219mm (0.402in.)



### 61 **27** 10.177mm (0.401in.)

1 EN6115−6Y18 ASNA2531−6 9.53mm (0.375in.) 10.177mm (0.401in.) 9.60mm (0.378in.) STDN EN6115V6Y15



### 66 NSA5368−616A NSA5368PD616A WASHER 

### 68
**52** NUT 

### 31 ASNA2531−5

OR EN6115−5−13 EN6115−5−14 

### 69 OR NSA5368PD616B



### 67 NSA5368−616B 

### 60 EN6115−6Y17

WASHER BOLT

OR

F_SB_574106_5_BBAA_05_01 Figure A-FBBAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 92 5

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

# @A340 SERVICE BULLETIN

**CONF 002


### A FR40 FR47



### B

**B B** 

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

STGR1 

### C Y1959 

### A Z141−142

F_SB_574106_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 93 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40
SECTION 

### E−E **C** VIEW SIDE CENTRE TANK AT FR 40 

### E

**E D**  **D**

KEEL BEAM CWB LOWER PANEL

FASTENER NOT AFFECTED STGR 1 

### (4) **(4) (2)** 

**(1) (3)**  **(3)** 

### BEFORE **BEFORE**

HOLE 7 HOLE A

HOLE 6
STGR 1 SECTION 

### D−D **(6)**

**(7)** 

### BEFORE HOLE 5

F_SB_574106_5_BCAA_02_00 Figure A-FBCAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 94 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

SECTION 

### E−E SECTION 

### D−D **C E** 

**E D** 
**D**

FASTENER NOT AFFECTED 

### AFTER

**AFTER**

**AFTER 63**  VIEW INSIDE CENTER TANK AT FR40

3 HOLE A HOLE 5
HOLE 6 HOLE 7 4

FR40

KEEL BEAM CWB LOWER PANEL STGR 1 

### 31 11.8mm MINIMUM (0.465in.) 

### 27 **33**

**35**
**36** DIA. 17mm THRU 17.2mm (0.669in. THRU 0.677in.) DETAIL 

### F STGR 1

1 APPLY SEALANT MAT No. 09−002B NOTE : 1 1 1 1 

### 27

OR 

### 51 **52** OR 

### 29 **65** OR 

### 70 **71** OR 

### 68 **69** OR 

### 70 **71**

F_SB_574106_5_BCAA_03_00 Figure A-FBCAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 95 5

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

# @A340 SERVICE BULLETIN

**CONF 002

(0.02in x 0.02in) 1mm THRU 1.2mm (0.039in THRU 0.047in) (0.072in)

CHAMFER 0.5mm x 0.5mm 

### 36 DETAIL 

### F

RADIUS 2mm 

### AFTER

**33 35** 

OR 

### 68 **69**

F_SB_574106_5_BCAA_04_00 Figure A-FBCAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 96 5

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

# @A340 SERVICE BULLETIN

**CONF 002



### 68 **33** NSA5368PD616A

ASNA2529−6 WASHER 9.823mm (0.387in.) FIRST OVERSIZE
NUT

MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

NSA5372−616B WASHER 12−1−N

12−1−N 9.60mm (0.378in.) 10.219mm (0.402in.)

9.60mm (0.378in.) 10.219mm (0.402in.) SECOND OVERSIZE

SECOND OVERSIZE 9.784mm (0.385in.)



### 63 **71** 10.177mm (0.401in.)

10.177mm (0.401in.) 3

4 STDN BOLT 9.53mm (0.375in.)

9.53mm (0.375in.) EN6115−6Y14

ASNA2531−6 NUT 

### 27 BOLT 7.849mm (0.309in.) NOMINAL 

### 51 7.809mm (0.307in.) 

### 52 NUT 

### 31 ASNA2531−5 OR EN6115−5−13 EN6115−5−14 MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER 

### 36 BOLT DESCRIPTION PN REMARKS EN6115V6X6 

### 35 F5332433420000 WASHER 

### 69 NSA5368PD616B OR

NSA5372−616A 

### 70 OR



### 65 **29** OR

NSA5372−616B WASHER 

### 71 NSA5372−616A 

### 70 OR
ASNA2531−6 NUT 

### 27 BOLT EN6115−6Y10 EN6115−6Y9

F_SB_574106_5_BCAA_05_02 Figure A-FBCAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 97 5

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

# @A340 SERVICE BULLETIN

**CONF 002


### A FR40 FR47



### B **B**

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

STGR1 

### C Y1959 

### A Z141−142

F_SB_574106_5_BDAA_01_00 Figure A-FBDAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 98 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40
SECTION 

### E−E SECTION 

### D−D **C** VIEW SIDE CENTRE TANK AT FR 40 

### E

**E D** 
**D**

KEEL BEAM CWB LOWER PANEL

FASTENER NOT AFFECTED STGR 1 

### (4) **(2)**

**(1) (3)**  **(3) (6)** 

**(7)**



### BEFORE **BEFORE BEFORE** 

HOLE 7 HOLE A

HOLE 6 HOLE 5

STGR 1

F_SB_574106_5_BDAA_02_00 Figure A-FBDAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 99 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

11.8mm MINIMUM 

### C **E**

**E**

**D**
**D**

KEEL BEAM CWB LOWER PANEL FASTENER NOT AFFECTED 

### AFTER

(0.465in.) STGR 1 

### 27 OR 

### 37
OR OR 

### 38 **39 40**  **31** VIEW INSIDE CENTER TANK AT FR40

3

2 HOLE A HOLE 5
HOLE 6 HOLE 7

DETAIL

### F STGR 1 SECTION 

### D−D **AFTER**

SECTION 

### AFTER **E−E 63**  **27**

3 3

3 3

APPLY MAT No. 09−002B 

### 51 **52** OR 

### 64 OR 

### 70 **71** OR 

### 70 **71**

F_SB_574106_5_BDAA_03_00 Figure A-FBDAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 100 5

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

# @A340 SERVICE BULLETIN

**CONF 002

ITEM DESCRIPTION PN HOLE Y DIAMETER 

### 37 **38 39**  **40** F5332433520000 F5332433520200 F5332433520400 F5332433520600 PLUG PLUG
PLUG PLUG 11.5mm (0.4528in.) 11.518mm (0.4535in.) 13.1mm (0.5157in.)

15mm (0.5906in.) 15.018mm (0.5913in.) 17mm (0.6693in.) 17.018mm (0.67in.)

APPLY MAT No. 09−005 1 2 3 4 

### 27

MIN MAX
13.118mm (0.5165in.) DETAIL 

### F

5 AFTER ASSEMBLY APPLY MAT No. 09−002B AND 09−028A APPLY MAT No. 09−002B APPLY MAT No. 09−016B OR OR OR 

### AFTER **37 38**  **39 40** 

NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C (0.02in x 0.02in) CHAMFER 0.5mm x 0.5mm

APPLY MAT No. 16−001B AFTER ASSEMBLY 6 1 2 3

4 5 6

OR 

### 70 **71**

**64**

F_SB_574106_5_BDAA_04_00 Figure A-FBDAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 101 5

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

# @A340 SERVICE BULLETIN

**CONF 002

MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER

BOLT DESCRIPTION PN

7.849mm (0.309in.) REMARKS

NOMINAL MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

12−1−N 10.219mm (0.402in.) SECOND OVERSIZE



### 51 7.809mm (0.307in.) 

### 63 **71**

**27** ASNA2531−6 NUT 12−1−N 10.219mm (0.402in.) SECOND OVERSIZE 9.53mm (0.375in.)

9.53mm (0.375in.) 9.60mm (0.378in.)

9.60mm (0.378in.) 2 3 STDN

10.177mm (0.401in.)

10.177mm (0.401in.) BOLT

BOLT EN6115−6Y14

ASNA2531−6 NUT 

### 27 WASHER NSA5372−616B



### 52 NUT 

### 31 ASNA2531−5 EN6115−5−13 EN6115−5−14 OR 

### 70 NSA5372−616A OR



### 71 WASHER NSA5372−616B 

### 70 NSA5372−616A OR 

### 64 EN6115−6Y11

F_SB_574106_5_BDAA_05_01 Figure A-FBDAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 102 5

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

# @A340 SERVICE BULLETIN

**CONF 002


### A FR40 FR47



### B **B**

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

STGR1 

### C Y1959 

### A Z141−142

F_SB_574106_5_BEAA_01_00 Figure A-FBEAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 103 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40

SECTION 

### E−E **C E** 

**E D** 
**D**

KEEL BEAM CWB LOWER PANEL

FASTENER NOT AFFECTED 

### (4) **(2)**

**(1)** 

### BEFORE **BEFORE**

STRG 1 FR40 DATUM VIEW INSIDE CENTER TANK AT FR40



### (3)

(0.512in.) 

### (5) DIA 13mm 

### (41) HOLE A HOLE 5
HOLE 6 HOLE 7 STGR 1 SECTION 

### D−D **(6)**

**(7)** 

### BEFORE

F_SB_574106_5_BEAA_02_00 Figure A-FBEAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 104 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

11.8mm MINIMUM 

### C **E**

**E**

**D**
**D**

KEEL BEAM CWB LOWER PANEL FASTENER NOT AFFECTED 

### AFTER

(0.465in.) STGR 1 

### 27 **39 31**  VIEW INSIDE CENTER TANK AT FR40

3

2 HOLE A HOLE 5
HOLE 6 HOLE 7

DETAIL 

### F STGR 1

SECTION 

### AFTER SECTION 

### D−D **AFTER**

**E−E 63**  **27**

3 3

3 3

APPLY MAT No. 09−002B 

### 51 **52** OR 

### 64 **70 71**  OR 

### 70 **71** OR

F_SB_574106_5_BEAA_03_00 Figure A-FBEAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 105 5

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

# @A340 SERVICE BULLETIN

**CONF 002

ITEM DESCRIPTION PN HOLE Y DIAMETER 

### 39 F5332433520400 PLUG 15mm (0.5906in.) 15.018mm (0.5913in.) 

### 27 **39**

MIN MAX DETAIL

### F **AFTER**

(0.02in x 0.02in) CHAMFER 0.5mm x 0.5mm

APPLY MAT No. 09−005 1 2 3 4 5 AFTER ASSEMBLY APPLY MAT No. 09−002B AND 09−028A APPLY MAT No. 09−002B APPLY MAT No. 09−016B NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C APPLY MAT No. 16−001B AFTER ASSEMBLY 6 1 2 3

4 5 6


### 70 **71** OR



### 64

F_SB_574106_5_BEAA_04_00 Figure A-FBEAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 106 5

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

# @A340 SERVICE BULLETIN

**CONF 002

MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER

BOLT DESCRIPTION PN

7.849mm (0.309in.) REMARKS

NOMINAL MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

12−1−N 10.219mm (0.402in.) SECOND OVERSIZE



### 51 7.809mm (0.307in.) 

### 63 **71**

**27** ASNA2531−6 NUT 12−1−N 10.219mm (0.402in.) SECOND OVERSIZE 9.53mm (0.375in.)

9.53mm (0.375in.) 9.60mm (0.378in.)

9.60mm (0.378in.) 2 3 STDN

10.177mm (0.401in.)

10.177mm (0.401in.) BOLT

BOLT EN6115−6Y14

ASNA2531−6 NUT 

### 27 WASHER NSA5372−616B



### 52 NUT 

### 31 ASNA2531−5 EN6115−5−13 EN6115−5−14 OR 

### 70 NSA5372−616A OR



### 71 WASHER NSA5372−616B 

### 70 NSA5372−616A OR 

### 64 EN6115−6Y11

F_SB_574106_5_BEAA_05_01 Figure A-FBEAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 107 5

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

# @A340 SERVICE BULLETIN

**CONF 002


### A FR40 FR47



### B **B**

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 FR40 DATUM

STGR1 

### C Y1959 

### A Z141−142

F_SB_574106_5_BFAA_01_00 Figure A-FBFAA - Sheet 01 Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 108 5

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

# @A340 SERVICE BULLETIN

**CONF 002

FR40 DATUM

FR40 SECTION 

### E−E SECTION 

### C **E**

**E D** 
**D**

KEEL BEAM CWB LOWER PANEL FASTENER NOT AFFECTED

STGR 1 

### (4) **(4) (2)** 

**(1) (3)**  **(6)**

**(7)** 

### D−D

13mm DIA 15mm (0.512in.) (0.591in.) 

### (41) **(5)** 

### BEFORE **BEFORE BEFORE**  VIEW INSIDE CENTER TANK AT FR40

HOLE A HOLE 5
HOLE 6 HOLE 7Y1959

STGR 1

F_SB_574106_5_BFAA_02_00 Figure A-FBFAA - Sheet 02 Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 109 5

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

# @A340 SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM



### 31 **27 40**  FR40

11.8mm MINIMUM 

### C **E**

**E D** 
**D**

KEEL BEAM CWB LOWER PANEL FASTENER NOT AFFECTED

(0.465in.)

STGR 1 3

2 HOLE A HOLE 5
HOLE 6 HOLE 7 VIEW INSIDE CENTER TANK AT FR40

DETAIL

### F SECTION 

### AFTER

**AFTER** STGR 1



### E−E SECTION 

### D−D **AFTER**

**63 27** 

3 3

3 3

APPLY MAT No. 09−002B 

### 51 **52** OR 

### 64 **70 71**  OR 

### 70 **71** OR

F_SB_574106_5_BFAA_03_00 Figure A-FBFAA - Sheet 03 Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 110 5

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

# @A340 SERVICE BULLETIN

**CONF 002

ITEM DESCRIPTION PN HOLE Y DIAMETER 

### 40 F5332433520600 PLUG 17mm (0.6693in.) 17.018mm (0.67in.) 

### 27 **40**

MIN MAX 

### F DETAIL

(0.02in x 0.02in) CHAMFER 0.5mm x 0.5mm

APPLY MAT No. 09−005 1 2 3 4 5 AFTER ASSEMBLY APPLY MAT No. 09−002B AND 09−028A APPLY MAT No. 09−002B APPLY MAT No. 09−016B NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C APPLY MAT No. 16−001B AFTER ASSEMBLY 6 1 2 3

4 5 6 

### 70 **71** OR



### 64 **AFTER**

F_SB_574106_5_BFAA_04_00 Figure A-FBFAA - Sheet 04 Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 111 5

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

# @A340 SERVICE BULLETIN

**CONF 002

MIN. MAX. HOLE SYMBOL ITEM HOLE DIAMETER

BOLT DESCRIPTION PN

7.849mm (0.309in.) REMARKS

NOMINAL MIN. MAX. HOLE SYMBOL ITEM DESCRIPTION PN REMARKS MIN. MAX. STARTING HOLE DIAMETER FINAL HOLE DIAMETER

12−1−N 10.219mm (0.402in.) SECOND OVERSIZE



### 51 7.809mm (0.307in.) 

### 63 **71**

**27** ASNA2531−6 NUT 12−1−N 10.219mm (0.402in.) SECOND OVERSIZE 9.53mm (0.375in.)

9.53mm (0.375in.) 9.60mm (0.378in.)

9.60mm (0.378in.) 2 3 STDN

10.177mm (0.401in.)

10.177mm (0.401in.) BOLT

BOLT EN6115−6Y14

ASNA2531−6 NUT 

### 27 WASHER NSA5372−616B



### 52 NUT 

### 31 ASNA2531−5 EN6115−5−13 EN6115−5−14 OR 

### 70 NSA5372−616A OR



### 71 WASHER NSA5372−616B 

### 70 NSA5372−616A OR 

### 64 EN6115−6Y11

F_SB_574106_5_BFAA_05_01 Figure A-FBFAA - Sheet 05 Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm (0.591 in.)) without crack detected) DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 112 5

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# @A340 SERVICE BULLETIN APPENDIX 01 - Inspection Report **CONF ALL (1) REPORT The results of the accomplishment of this Service Bulletin, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department AI/SEES1, on the attached inspection report sheet.

DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 1 5

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# @A340 SERVICE BULLETIN APPENDIX 01 - Inspection Report
**CONF ALL

A340−57−4106 SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : FINDINGS : YES NO DATE OF INSPECTION INSPECTION METHOD : SPECIAL DETAILED

HOLE 5 LH SIDE NO CRACK CRACK DIAMETER
HOLE 6 LH HOLE 7 LH HOLE A LH HOLE 5 RH HOLE 6 RH HOLE 7 RH HOLE A RH

PLEASE PRECISE OTHER FINDINGS : LH RH HOLE 5 HOLE 6 HOLE 7 HOLE A NOMINAL DIAMETER HOLE 5 HOLE 6 HOLE 7 HOLE A FIRST OVERSIZE HOLE 5 HOLE 6 HOLE 7 HOLE A SECOND OVERSIZE INSTALLATION OF THE FASTENER AT : **INSPECTION REPORT**

F_SB_574106_5_AAAA_01_00 Figure A-FAAAA - Sheet 01 Inspection Report DATE: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 2 5

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40 MODIFICATION No.: 56467S18944 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: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 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: Aug 30/07 SERVICE BULLETIN No.: A340-57-4106 REVISION No.: 03 - Sep 24/12 Page: 1 5

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