# 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. 01 of Service Bulletin No. A340-57-4106. A D D I T I O N A L WO R K Additional work is required by this revision for aircraft modified by any previous issue. If this Service Bulletin has been accomplished per any previous issue (s) it is necessary to do the additional work as described in this revision. R E A S O N 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. The ADDITIONAL WORK is for aircraft in Config. 01 and is only necessary on those MSN on which a crack was detected at hole 5 before oversizing of the keel beam (Refer for details to para. 3.B (1)(b) step 3). C H A N G E S SUMMARY : - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Text updated. Price of Kit A01 updated. Kit A01S01 and A03 added in evaluation table. - EFFECTIVITY

. Operators AJM, ALK, CAL, CCA, OAL, S3R, SAS and THT added. Operators updated. Note updated. - MATERIAL INFORMATION

. Kit A01S01, A03 and Config. 02 added. PLANNING INFORMATION : DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- EFFECTIVITY

. Para. 1.A. Effectivity extended and updated. Notes updated. - REASON

. Para. 1.C. Text updated. - DESCRIPTION

. Para. 1.D. Config. 02 and ADDITIONAL WORK added. - COMPLIANCE

. Para. 1.E. Sentence added. - MANPOWER

. Para. 1.G. Manpower for Config. 02 added. MATERIAL INFORMATION : - MATERIAL - PRICE AND AVAILABILITY

. Para. 2.A. Price and availability of Kit A01 updated. Kit A01S01 and Kit A03 added. - LIST OF COMPONENTS

. Para. 2.C. Kit A01 updated. Kits A0S01 and A03 added. - LIST OF MATERIALS - OPERATOR SUPPLIED

. Para. 2.D. MAT No. 09-005, 09-016B, 09-028A, 16-001B and 16-002C added. ACCOMPLISHMENT INSTRUCTIONS : - Preparation

. Para. 3.A.(1) Config. 02 added. - MODIFICATION

. Para. 3.B. Note added. Para. (1)(b)3b, rotating probe inspection added. Config. 02 added. Alternative bolt EN6115-5-13 and EN6115-5-14 added. ADDITIONAL WORK added. - TESTS

. Para. 3.C. Config. 02 added. - CLOSE-UP

. Para. 3.D. Config. 02 added. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- ILLUSTRATIONS

. Figure 3, Sheets 03 and 04 updated. . Figure 4, Sheets 03 and 04 updated. . Figure 5 added. . Figure 6 added. . Figure 7 added. . Figure 8 added. APPENDIX 1 : - Figure 1

. Inspection report updated. F I L I N G I N S T R U CT I O N S 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. H I S T O R Y O F P R E V I O U S R E V I S I O N S No previous revisions. R E V I S I O N S E Q U E N C E ORIGINAL : Aug 30/07 REVISION No. : 01 - Jul 31/09

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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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 MODIFICATION No. :**  56467S18944 R E A S O N/D E S C R I PT I O N/O P E RA T I O N A L C O N S E Q U E N C E S 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 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. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) including mandatory and recommended thresholds and repetitive inspection intervals. 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 for aircraft on which Mod. No. 41652S11819 (FUSELAGE-STRUCTURE A340 COMMONALITY ITEMS) is embodied and Mod. No. 44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR) is not embodied and for aircraft on which Mod. 44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR) is embodied and Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied. ALI 57.11.63 is created for Post Mod. SB configuration (Post Mod. No. 56467S18944).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN SUMMARY

EVALUATION TABLE COMPLIANCE Recommended CANCELS INSPECTION SB Yes POTENTIAL AD No A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) A01R02 304 KIT PRICE (USD) A03R03 2,243 KIT PRICE (USD) A01S01 83

MODIFICATION CLASSIFICATION MAJOR 56467S18944
MINOR None
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. **E F**  **F E**  **C T**  **I V**  **I T** **Y** This Service Bulletin is applicable to these operators : AAW ACA AFR ALK CAL CCA CES CPA DLH ETD GFA IBE LAN MAU MSR OAL PAL S3R SAS SWR THT THY UAE VIR 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. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied. C O N C U R R E N T R E Q U I R E M E N T S None DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN SUMMARY

R E F E R E N C E S/R E P E R C U S S I O N S TFU : 57.11.00.005 OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None N A T U R E O F T H E WO R K AIRCRAFT : YES EQUIPMENT : NO HARD : NO SOFT : NO OBRM : NO M A N POW E R Config. 01
**TOTAL MANHOURS 53.0 ELAPSED TIME (HOURS) 38.0**  Config. 02
**TOTAL MANHOURS 58.5 ELAPSED TIME (HOURS) 42.0**  M A T E R I A L I N FO R M A T I O N AIRCRAFT DATA Config. 01 Kit 574106A01R02 Bolts, nuts and washer DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN SUMMARY
Config. 01 Kit 574106A01S01 Bolts Config. 02 Kit 574106A03R03 Plugs, bolts, nuts and washers A P P E N D I C E S Appendix 1 - REPORT

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 6 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51 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. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. E**  **F F**  **E C** **T I**  **V I**  **T Y**  (1) Models 340-212 340-213 340-311 340-312 340-313 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft 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 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. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

(b) 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 AAW 0151 ACA 0273 0278 AFR 0168 0174 0186 0207 0210 0237 0245 0246 0260 0307 0310 0319 0373 0377 0399 ALK 0367 0374 CAL 0402 0406 0411 0415 0433 CCA 0192 0199 0201 0242 0243 0264 CES 0129 0131 0141 0161 0182 CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228 0381 DLH 0135 0158 0213 0233 0252 0274 0297 0304 0321 0325 0327 0335 0347 0352 0354 0355 0379 0390 0434 0447 ETD 0117 GFA 0133 0212 0215 0282 IBE 0125 0134 0145 0146 0170 0193 0197 0217 0221 0302 0318 0329 0332 0378 0387 0414 0459 0474 0483 LAN 0167 0359 0363 0429 0442 MAU 0152 0194 0268 MSR 0156 0159 0178 OAL 0235 0239 0280 0292 PAL 0173 0176 0187 0196 S3R 0204 SAS 0413 0424 0430 0435 0450 0467 0470 SWR 0150 0154 0169 0175 0179 0263 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

OPERATOR MSN THT 0385 0395 0438 0446 THY 0115 0180 0216 0257 0270 0331 UAE 0139 0149 0163 0166 0185 0190 0202 0236 VIR 0114 0164 0214 0225 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 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 0173-0175 KIT No. QTY PER A/C CONFIGURATION 574106A01R02 2 01 The Kits and configurations applicable to these MSNs are given at the end of this list 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 KIT No. QTY PER A/C CONFIGURATION 574106A03R03 2 02 NOTE : Config. 01 concerns aircraft on which modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is not embodied. NOTE : Config. 02 concerns aircraft on which modification No. 44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is embodied. (3) Spares None **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

**C. R E** **A S**  **O N**  (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 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. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) including mandatory and recommended thresholds and repetitive inspection intervals. (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 for aircraft on which Mod. No. 41652S11819 (FUSELAGE-STRUCTURE A340 COMMONALITY ITEMS) is embodied and Mod. No. 44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR) is not embodied and for aircraft on which Mod. 44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR) is embodied and Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied. ALI 57.11.63 is created for Post Mod. SB configuration (Post Mod. No. 56467S18944). (4) Operational/Maintenance Consequences None **D. D E**  **S C**  **R I**  **P T**  **I O**  **N** To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. (b) 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. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

(c) 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. (d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. (2) Config. 02 (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. (b) 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. (c) 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. (d) 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. (e) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. (3) ADDITIONAL WORK (a) ADDITIONAL WORK concerns aircraft on which this Service Bulletin has been accomplished at the original issue and on which a crack was found at first rototest inspection (before keel beam reaming - Refer for details to Paragraph. 3.B (1)(b) step 3). For the accomplishment of the ADDITIONAL WORK, the operator must contact AIRBUS to get instructions. **E. C O**  **M P**  **L I**  **A N**  **C E**  (1) Classification Recommended (2) Accomplishment Timescale (a) For aircraft in Config. 01 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.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

Aircraft A340-300 A340-200 Post Mod. No. 41652S11819 and pre Mod. No. 44360S13013 A340-300 Post Mod. No. 41652S11819 and pre Mod. No. 44360S13013 Recommended NOT before FC or FH Recommended NOT before FC or FH Proposed Compliance 11,170FC / 40,390FH 11,170FC / 40,390FH (b) For aircraft in Config. 02 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. Aircraft A340-300 A340-200 Post Mod. No. 44360S13013 and pre Mod. No. 49202S16307 A340-300 Post Mod. No. 44360S13013 and pre Mod. No. 49202S16307 WV027 Recommended NOT before FC or FH Proposed Compliance 11,170FC / 40,390FH 16,350 FC / 32,700FH

**F. A P**  **P R** **O V**  **A L**  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. M A**  **N P**  **O W**  **E R**  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. Config. 01 Get access 12.0 Removal of the ducts 6.0 Removal of fastener, hole 5 1.0 Rotating probe inspection hole 5 1.0 Installation of the fastener, hole 5 2.5 Removal of fasteners, holes 6 and 7 2.0 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

Rotating probe inspection holes 6 and 7 1.5 Cold expansion hole 6 1.5 Installation of fasteners, holes 6 and 7 2.5 Installation of the ducts 6.0 Test 2.0 Close-up 15.0 **TOTAL MANHOURS 53.0 ELAPSED TIME (HOURS) 38.0**  Config. 02 Get access 12.0 Removal of the ducts 6.0 Removal of fastener, hole 5 1.0 Rotating probe inspection hole 5 1.0 Installation of the plug (if necessary) 3.0 Installation of the fastener, hole 5 2.5 Removal of fasteners, holes A, 6 and 7 3.0 Rotating probe inspection holes A, 6, 7 2.0 Cold expansion holes A and 6 2.0 Installation of fasteners, holes A, 6, 7 3.0 Installation of the ducts 6.0 Test 2.0 Close-up 15.0 **TOTAL MANHOURS 58.5 ELAPSED TIME (HOURS) 42.0**  **H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Not changed
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

**I. E L**  **E C** **T R**  **I C** **A L**  **L O** **A D**  **D A** 

**T**

**A** Not changed **J. R E**  **F E**  **R E**  **N C**  **E S**  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 Testing Manual (NTM) : 51-10-01 51-10-18 Service Information Letter (SIL) : 51-012 Structural Repair Manual (SRM) : 51-42-11 51-43-00 51-44-11 51-48-00 51-76-12 PMS 01-05-05 Service Bulletin No. A340-57-4036 Service Bulletin No. A340-57-4089 Appendix 1 **K. P U**  **B L**  **I C** **A T**  **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  Not changed **L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** Not applicable

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# A340 SERVICE BULLETIN

**2. M A**  **T E**  **R I**  **A L**  **I N**  **F O**  **R M**  **A T**  **I O**  **N A. M**  **A T**  **E R**  **I A**  **L -**  **P R**  **I C**  **E A** **N D**  **A V** 

**A I**  **L A**  **B I**  **L I** **T Y**  (1) Material 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 : AIRBUS SPARES SUPPORT AND SERVICES Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability Kit 574106A01R02 Cost : 304.00 US dollars Availability : 60 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 574106A01S01 Cost : 83.00 US dollars Availability : 60 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

Kit Held by the Operator Supplementary Kits Required Latest Status of Kit INST/DISP 574106A01R01 574106A01S01 574106A01R02 574106A01R02 NONE 574106A01R02 NOTE : Kit 574106A01R02 does not require an Kit 574106A01S01 because Kit 574106A01S01 is included in Kit 574106A01R02. Kit 574106A03R03 Cost : 2,243.00 US dollars Availability : 60 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. **B. I N**  **D U**  **S T**  **R Y**  **S U**  **P P** **O R** **T I**  **N F** **O R**  **M A**  **T I**  **O N**  This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy. **C. L I**  **S T**  **O F**  **C O**  **M P** **O N**  **E N**  **T S**  Kit 574106A01R02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 25 EN6115-6Y-20 1 Bolt 26 NSA5368-616D 1 Washer 27 ASNA2531-6 1 Nut 31 ASNA2531-5 1 Nut 32 EN6115-5-12 1 Bolt 33 ASNA2529-6 1 Nut 34 EN6115V6Y-16 1 Bolt 35 F5332433420000 1 Washer 42 NSA5368PD616D 1 Washer 51 EN6115-5-13 1 Bolt 52 EN6115-5-14 1 Bolt NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number to part number relationship. Kit 574106A01S01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 10 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

51 EN6115-5-13 1 Bolt 52 EN6115-5-14 1 Bolt NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number to part number relationship. Kit 574106A03R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 27 ASNA2531-6 2 Nut 28 EN6115-6Y-16 1 Bolt 29 EN6115-6Y-10 1 Bolt 30 EN6115-6Y-8 1 Bolt 31 ASNA2531-5 1 Nut 32 EN6115-5-12 1 Bolt 33 ASNA2529-6 1 Nut 35 F5332433420000 1 Washer 36 EN6115V6X-6 1 Bolt 37 F5332433520000 1 Plug 38 F5332433520200 1 Plug 39 F5332433520400 1 Plug 40 F5332433520600 1 Plug 42 NSA5368PD616D 1 Washer 50 NSA5372-616D 2 Washer 51 EN6115-5-13 1 Bolt 52 EN6115-5-14 1 Bolt NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number to part number relationship. **D. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Fuel Tank Sealant Polysulfide Mat. No. 09-002B As required Corrosion Inhibitive Interfay Sealant Mat. No. 09-005 As required Corrosion Inhibiting Brush Consistency Mat. No. 09-013B As required Corrosion Inhibiting Fillet Consistency Mat. No. 09-016B As required Adhesion Promoter For Polysulfide Sealant Mat. No. 09-028A As required Solvent General Purpose Mat. No. 11-026 As required DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Chemical Conversion Coating Yellow Aluminum Mat. No. 13-002 As required Polyurethane Primer Mat. No. 16-001B As required Internal Top Coat Mat. No. 16-002C As required (2) Components None **E. P A**  **R T** **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** None **F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A** **N D**  **A V** 

**A I**  **L A**  **B I**  **L I** **T Y**  (1) To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. (a) Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6. (b) Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6. (2) Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for cold working : NOTE : For definition of capital, durable and expendable tools, refer to SIL 51-012. - Capital tooling : ref. FTI-A340-57-4106-1 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-A340-57-4106-1 NOTE : In this durable tool, there is the minimum quantity necessary to accomplish this Service Bulletin on one aircraft. In case of accomplishment of this Service Bulletin on more than one aircraft, operator can define the quantity of durable tool to be ordered by reference to SIL 51-012. - Expendable tooling : ref. EK-A340-57-4106-1 NOTE : In this expendable tool, there is the minimum quantity necessary to accomplish this Service Bulletin on one aircraft. One expendable tool has to be ordered for each aircraft where this Service Bulletin is accomplished. Operators interested in obtaining the FTI tool kit should contact :

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

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 **G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  None

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. (1) Preparation (a) Config. 01 thru Config. 02 1 Make sure that the aircraft is grounded (Refer to AMM 12-34-24, Page block 201). 2 Put the access platform(s) in position. 3 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00, Page block 201). 4 Do the preparation procedure as specified in removal/installation of the air-conditioning distribution ducts (Refer to AMM 21-20-00, Page block 201). 5 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). 6 Do the preparation procedure as specified in removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41, Page block 401). 7 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). 8 Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11, Page block 401). 9 Defuel the center tank (Refer to AMM 28-25-00, Page block 301).
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

1 0 Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45, Page block 401). 1 1 Get access to the work area. (2) Standard Practices (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with Solvent General Purpose (Mat. No. 11-026). (c) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent General Purpose (Mat. No. 11-026). (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) on all the fasteners to be installed (wet assembly). (g) For the oversize and alternative fasteners (Refer to SRM 51-43-00). (h) Torque the standard threaded fasteners (Refer to AMM 20-21-11, Page block 201). (i) Do the cold expansion of the holes (Refer to SRM 51-48-00). (j) Apply the sealant (Refer to SRM 51-76-12). (k) Install the plug with liquid nitrogen (Refer to PMS 01-05-05). **B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  NOTE : For aircraft on which temporary repair (covered by Repair Design Approval Sheet (RAS)) have been done following accomplishment of Inspection Service Bulletin A340-57-4089, the operator must contact AIRBUS repair office in order to issue definitive RAS after embodiment of this Modification Service Bulletin. (1) Config. 01 (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. Refer to Figures 1 and 2 1 On RH side, remove the air conditioning duct. Refer to Figure 1
a 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

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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). 2 On RH side, remove the air ventilation duct. Refer to Figure 2
a 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 3 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). 4 Put the blanking plugs on the disconnected line ends. (b) 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. Refer to Kit 574106A01R02 Refer to Figure 3 NOTE : Description below is given for one side of the aircraft, two Kit 574106A01R02 are necessary to modify one aircraft. 1 Inspect the hole 5. Refer to Figure 3, Sheets 1 and 2
a Remove : 1 Bolt Item (41) Discard 1 Nut Item (4) Discard

b Remove the sealant and clean the hole.
c Do a rotating probe inspection (Refer to NTM 51-10-01) through all the layers. - If no crack is detected, do the operations given in paragraph (1)(b)2. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

- If crack is detected do the operations given in paragraph (1)(b)3. 2 No crack, oversize the hole 5 in the keel beam. Refer to Figure 3, Sheets 1, 3 and 4
a 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.). b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.).
c Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.). d Clean the drilled area.
e Install : 1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 3 Crack detected, oversize the hole 5 in the keel beam. Refer to Figure 3, Sheets 1, 3 and 4
a 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.). b Do a rotating probe inspection at the level of the keel beam only (Refer to NTM 51-10-18). - Crack finding, contact AIRBUS. - 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.). - Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-01) . Crack finding, contact AIRBUS. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

. No crack finding, do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). . Oversize the hole 5 through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) . Install : 1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 4 Inspect holes 6 and 7 Refer to Figure 3, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (3) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in paragraphes (1)(b)5 and 6. 5 Do the cold working of the hole 6. Refer to Figure 3, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-20 Item 25 1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616D Item 26 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 6 Install the fastener in hole 7. Refer to Figure 3, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). NOTE(03) If necessary, contact AIRBUS for a specific washer solution. 7 For the report after modification, refer to Appendix 1. (c) 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. Refer to Figure 4
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

NOTE(01) Description below is given for one side of the aircraft, two Kit 574106A01R02 are necessary to modify one aircraft. NOTE(02) If the diameter of the bush is >13mm (0.512in.) or if the bush is installed in other layers than keel beam fitting only, contact AIRBUS. 1 Inspect the hole 5. Refer to Figure 4, Sheets 1 and 2
a Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard

b Remove the sealant and clean the hole.
c Do a rotating probe inspection (Refer to NTM 51-10-18) through all the layers. - If crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in paragraph (1)(c)2. 2 No crack finding, oversize the hole in the keel beam. Refer to Figure 4, Sheets 1, 3 and 4
a 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.) b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.).
c Oversize the hole through all the layers to a diameter comprised between 10.177mm (0.401in.) and 10.219mm (0.402in.) d Install : 1 Bolt EN6115V6Y-16 Item 34 1 Washer F5332433420000 Item 35 1 Nut ASNA2529-6 Item 33 1 Washer NSA5368PD616D Item 42 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 3 Inspect holes 6 and 7. Refer to Figure 4, Sheets 1 and 2 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

a Remove : 1 Nut Item (2) Discard 1 Nut Item (4) Discard 1 Bolt Item (1) Discard 1 Bolt Item (41) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (1)(c)4 and 5. 4 Do the cold working of the hole 6. Refer to Figure 4, Sheets 1, 3 and 4
a 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. b 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.
c 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. d Clean the drilled area.
e Install : 1 Bolt EN6115-6Y-20 Item 25 1 Nut ASNA2531-6 Item 27 1 Washer NSA5368-616D Item 26 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 5 Install the fastener in hole 7. Refer to Figure 4, Sheets 1, 3 and 4
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). NOTE(03) If necessary, contact AIRBUS for a specific washer solution. 6 For the report after modification, refer to Appendix 1. (d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Refer to Figures 1 and 2 1 Remove the blanking plugs on the disconnected line ends. 2 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). 3 On RH side, install (if removed) the air ventilation duct. Refer to Figure 2
a 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. 4 On RH side, install (if removed) the air conditioning duct. Refer to Figure 1
a Install : 1 Duct Item (8) DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

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. (2) Config. 02 NOTE : Refer to paragraph E.(2) Accomplishment Timescale for Config. 02 embodiment recommendation. (a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and FR40, for access. Refer to Figures 1 and 2 1 On RH side, remove the air conditioning duct. Refer to Figure 1
a 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). 2 On RH side, remove the air ventilation duct. Refer to Figure 2 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

a 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 3 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). 4 Put the blanking plugs on the disconnected line ends. (b) 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. Refer to Kit 574106A03R03 Refer to Figures 5 and 6 NOTE(01) Description below is given for one side of the aircraft, two Kit 574106A03R03 are necessary to modify one aircraft. 1 Inspect the hole 5. Refer to Figure 5, Sheets 1 and 2
a Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard

b Remove the sealant and clean the hole.
c Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-01). - If no crack is detected, do the operations given in paragraph (2)(b)2. - If a crack is detected, do the operations given in paragraph (2)(b)6. 2 No crack, oversize the hole 5 in the keel beam. Refer to Figure 5, Sheets 1, 3 and 4
a 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.). b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.).
c Oversize the hole 5 through all the layers to a diameter comprised between 9.784mm (0.385in.) and 9.823mm (0.387in.) d Install : DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

1 Bolt EN6115V6X-6 Item 36 1 Washer F5332433420000 Item 35 1 Washer NSA5368PD616D Item 42 1 Nut ASNA2529-6 Item 33 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 3 Inspect holes A, 6 and 7. Refer to Figure 5, Sheets 1 and 2
a 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

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A, 6 and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(b)4 and 5. 4 Do the cold working of the holes A and 6. Refer to Figure 5, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

f Install : 1 Bolt EN6115-6Y-16 Item 28 1 Bolt EN6115-6Y-8 Item 30 2 Nut ASNA2531-6 Item 27 2 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nuts with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 5 Install the fastener in hole 7. Refer to Figure 5, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 6 Crack detected at existing diameter. Refer to Figure 6, Sheets 1, 3 thru 5
a Ream the hole 5 through all the layer at diameter 9.5mm (0.374in.). b Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-01). - If no crack is detected, do the operations given in paragraph (2)(b)7. - If a crack is detected at diameter 9.5mm (0.374in.), do the operations given in paragraph (2)(b)11. 7 No crack detected at diameter 9.5mm (0.374in.) for hole 5. Refer to Figure 6, Sheets 1, 3 thru 5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

a Remove the fastener of hole 6. - Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard

b 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.
c Clean the drilled area. d 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.
e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 11.5mm (0.4528in.) and 11.518mm (0.4535in.) h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). j Install : 1 Plug F5332433520000 Item 37 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 37 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 37 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole.
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 28 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

NOTE(05) Do a seal bead with Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 37. NOTE(06) Do a seal bead on the external edge of the plug Item 37 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A). NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 8 Inspect holes A and 7. Refer to Figure 6, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(b)9 and 10. 9 Do the cold working of the hole A. Refer to Figure 6, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 0 Install the fastener in hole 7. Refer to Figure 6, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 1 Crack detected at diameter 9.5mm (0.374in.) for hole 5.
a Ream the hole 5 through all the layers at diameter 11.1mm (0.437in.). b Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-01). - If no crack is detected, do the operations given in paragraph (2)(b)12. - If a crack is detected, do the operations given in paragraph (2)(b)16. 1 2 No crack detected at diameter 11.1mm (0.437in.) for hole 5. Refer to Figure 6, Sheets 1, 3 thru 5
a Remove the fastener of hole 6. - Remove: 1 Bolt Item (3) Discard DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

1 Nut Item (4) Discard

b 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.
c Clean the drilled area. d 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.
e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 13.1mm (0.5157in.) and 13.118mm (0.5165in.). h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole 5 with Chemical Conversion Coating Yellow AluminumChemical Conversion Coating Yellow Aluminum (Mat. No. 13-00213-002). j Install : 1 Plug F5332433520200 Item 38 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 38 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 38 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole. NOTE(05) Do a seal bead withCorrosion Inhibitingfillet ConsistencyCorrosion Inhibiting Fillet Consistency (Mat. No. 09-016B09-016B) in the hole on the edge of the plug Item 38.
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

NOTE(06) Do a seal bead on the external edge of the plug Item 38 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A). NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 3 Inspect holes A and 7. Refer to Figure 6, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(b)14 and 15. 1 4 Do the cold working of the hole A. Refer to Figure 6, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 5 Install the fastener in hole 7. Refer to Figure 6, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 6 Crack detected at diameter 11.1mm (0.437in.) for hole 5.
a Ream the hole 5 through all the layers at diameter 13.1mm (0.516in.). b Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-01). - If no crack is detected, do the operations given in paragraph (2)(b)17. - If crack is detected, do the operations given in paragraph (2)(b)21. 1 7 No crack detected at diameter 13.1mm (0.516in.) for hole 5.
a Remove the fastener of hole 6. - Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.). DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

Use tool list No. DK-A340-57-4106-1.
c Clean the drilled area. d 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.
e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 15mm (0.5906in.) and 15.018mm (0.5913in.). h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). j Install : 1 Plug F5332433520400 Item 39 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 39 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 39 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole. NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 39. NOTE(06) Do a seal bead on the external edge of the plug Item 39 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A). NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 1 8 Inspect holes A and 7. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

Refer to Figure 6, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(b)19 and 20. 1 9 Do the cold working of the hole A. Refer to Figure 6, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 2 0 Install the fastener in hole 7. Refer to Figure 6, Sheets 1, 3 and 4 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 2 1 Crack detected at diameter 13.1mm (0.516in.) for hole 5.
a Ream the hole 5 through all the layers at diameter of 15mm (0.591in.). b Perform a rotating probe inspection through all the layers of hole 5.(Refer to NTM 51-10-01). - If no crack is detected, do the operations given in paragraph (2)(b)22. - If crack is detected, contact AIRBUS. 2 2 No crack detected at diameter 15mm (0.591in.) for hole 5.
a Remove the fastener of hole 6. - Remove: 1 Bolt Item (3) Discard 1 Nut Item (4) Discard

b 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.
c Clean the drilled area. d 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. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 17mm (0.6693in.) and 17.018mm (0.67in.). h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). j Install : 1 Plug F5332433520600 Item 40 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 40 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 40 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole. NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 40. NOTE(06) Do a seal bead on the external edge of the plug Item 40 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A). NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 2 3 Inspect holes A and 7. Refer to Figure 6, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(b)24 and 25. 2 4 Do the cold working of the hole A. Refer to Figure 6, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 2 5 Install the fastener in hole 7. Refer to Figure 6, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). (c) 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. Refer to Kit 574106A03R03 Refer to Figure 7 NOTE(01) Description below is given for one side of the aircraft, two Kit 574106A03R03 are necessary to modify one aircraft. 1 Inspect the hole 5. Refer to Figure 7, Sheets 1 and 2
a Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard

b Remove the sealant and clean the hole.
c Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). - If no crack is detected, do the operations given in paragraph (2)(c)2. - If a crack is detected, contact AIRBUS. 2 No crack detected at original diameter on hole 5. Refer to Figure 7, Sheets 1 and 2
a Remove the fastener of hole 6. - Remove: 1 Bolt Item (41) Discard 1 Nut Item (4) Discard
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

b 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.
c Clean the drilled area. d 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.
e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 15mm (0.5905in.) and 15.018mm (0.5913in.). h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). j Install : 1 Plug F5332433520400 Item 39 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 39 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 39 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole. NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 39. NOTE(06) Do a seal bead on the external edge of the plug Item 39 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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# A340 SERVICE BULLETIN

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 3 Inspect holes A and 7. Refer to Figure 7, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(c)4 and 5. 4 Do the cold working of the hole A. Refer to Figure 7, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly).
DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 41 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 5 Install the fastener in hole 7. Refer to Figure 7, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). (d) 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. Refer to Kit 574106A03R03 Refer to Figure 8 NOTE(01) Description below is given for one side of the aircraft, two Kit 574106A03R03 are necessary to modify one aircraft. 1 Inspect the hole 5. Refer to Figure 8, Sheets 1 and 2
a Remove : 1 Bolt Item (3) Discard 1 Nut Item (4) Discard 1 Bush Item (5) Discard

b Remove the sealant and clean the hole.
c Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM 51-10-18). - If no crack is detected, do the operations given in paragraph (2)(d)2. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 42 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

- If a crack is detected, contact AIRBUS. 2 No crack detected at original diameter for hole 5 Refer to Figure 8, Sheets 1 and 2
a Remove the fastener of hole 6. - Remove: 1 Bolt Item (41) Discard 1 Nut Item (4) Discard

b 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.
c Clean the drilled area. d 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.
e 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. f Clean the drilled area. g Ream the hole 5 through all the layers to a diameter comprised between 17mm (0.6693in.) and 17.018mm (0.67in.). h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. i Protect the hole with Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002). j Install : 1 Plug F5332433520600 Item 40 1 Bolt EN6115-6Y-10 Item 29 1 Washer NSA5372-616D Item 50 1 Nut ASNA2531-6 Item 27 NOTE(01) Install the plug Item 40 with liquid nitrogen (Refer to PMS 01-05-05). NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005) between the plug Item 40 and the structure. NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 43 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top Coat (Mat. No. 16-002C) after assembly in the hole. NOTE(05) Do a seal bead with Corrosion Inhibiting Fillet Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 40. NOTE(06) Do a seal bead on the external edge of the plug Item 40 withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A). NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 3 Inspect holes A and 7. Refer to Figure 8, Sheets 1 and 2
a Remove : 1 Nut Item (2) Discard 1 Nut Item (6) Discard 1 Bolt Item (1) Discard 1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.
c Do a rotating probe inspection through all the layers of holes A and 7 (Refer to NTM 51-10-01). - If a crack is detected, contact AIRBUS. - If no crack is detected, do the operations given in the paragraphes (2)(d)4 and 5. 4 Do the cold working of the hole A. Refer to Figure 8, Sheets 1, 3 and 4
a 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. b Clean the drilled area.
c 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. d 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.
e Clean the drilled area. DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 44 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

f Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5. g Install : 1 Bolt EN6115-6Y-16 Item 28 1 Nut ASNA2531-6 Item 27 1 Washer NSA5372-616D Item 50 NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). 5 Install the fastener in hole 7. Refer to Figure 8, Sheets 1, 3 and 4
a Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and 7.849mm (0.309in.). b Install : 1 Bolt EN6115-5-12 Item 32 or depending on the thickness of the structure : 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 Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) (wet assembly). NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No. 09-002B). (e) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Refer to Figures 1 and 2 1 Remove the blanking plugs on the disconnected line ends. 2 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). 3 On RH side, install (if removed) the air ventilation duct. Refer to Figure 2
a Install : 1 Duct Item (20) DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 45 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

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. 4 On RH side, install (if removed) the air conditioning duct. Refer to Figure 1
a 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. (3) ADDITIONAL WORK (a) Aircraft which has got the task Paragraph 3.B (1)(b) step 3 accomplished at the original Service Bulletin issue contact AIRBUS for advise on the ADDITIONAL WORK. **C. T E**  **S T**  (1) Config. 01 thru Config. 02 (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). DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 46 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

(b) Tests 1 Do the test after the removal/installation of the pack discharge temperature-sensor (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). **D. C L** **O S**  **E U**  **P** (1) Config. 01 thru Config. 02 (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. **E. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 47 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 1, Sheet 1 Config. 01 thru 02 : 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. : 01 - Jul 31/09 Page : 48 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 2, Sheet 1 Config. 01 thru 02 : 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. : 01 - Jul 31/09 Page : 49 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 3, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 50 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 3, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 51 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 3, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 52 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 3, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 53 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 4, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 54 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 4, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 55 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 4, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 56 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 4, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 57 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 5, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 58 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 5, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 59 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 5, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 60 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 5, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 61 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 6, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 62 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 6, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 63 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 6, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 64 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 6, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 65 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 6, Sheet 5 Config. 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. : 01 - Jul 31/09 Page : 66 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 7, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 67 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 7, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 68 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 7, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 69 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 7, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 70 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 7, Sheet 5 Config. 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. : 01 - Jul 31/09 Page : 71 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 8, Sheet 1 Config. 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. : 01 - Jul 31/09 Page : 72 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 8, Sheet 2 Config. 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. : 01 - Jul 31/09 Page : 73 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 8, Sheet 3 Config. 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. : 01 - Jul 31/09 Page : 74 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 8, Sheet 4 Config. 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. : 01 - Jul 31/09 Page : 75 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN

Figure 8, Sheet 5 Config. 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. : 01 - Jul 31/09 Page : 76 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN APPENDIX 1

**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 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. : 01 - Jul 31/09 Page : 1 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 1 Inspection Report DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 2 Printed in France © AIRBUS 2008 All rights reserved

# 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 P l e as e co m p l ete t h e a p p ro p r i ate i te m (A o r B ) : A - SB W I L L B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. B - SB H AS B E E N embodied on aircraft: ............................................................................................................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. Operator comments:..............................................................................................................

..............................

............................................................................................................................... ..............................................

............................................................................................................................... .............................................. From Airline: ...................................................................................................................

..................................... Name/Title: ....................................................................................................................

...................................... Signature:..................... Date: ..................................................... I f op e rat i o n a l d o c u m e n tat i o n i s affe cte d ( s e e Pa rag ra p h 1

. K of t h i s S B ) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m p o rt a n t I n fo r m at i o n : 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. P l e as e re t u r n t h i s co m p l ete d s h e et to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 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. : 01 - Jul 31/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved

# A340 SERVICE BULLETIN REPORTING QUALITY

**TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR.40**  **MODIFICATION No. :** 56467S18944 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 futher 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 4 3 2 1 -Quality rating of the Accomplishment Instructions 4 3 2 1 -Quality rating of the Illustrations 4 3 2 1 -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 X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-up X Publication X Tooling X Illustrations C o m m e n ts :

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEMB 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. : 01 - Jul 31/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved