# A330 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. A330-57-3098. 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. Kits A01S01 and A03 added in evaluation table. - EFFECTIVITY

. Operators ACA, ACI, AFR, ALK, BMA, CRL, CYP, EDW, EEZ, EIN, ETD, FWI, GFA, GRL, HVN, IAC, JST, MON, MPD, MYT, OBS, PAL, QAF, QTR, SAS, SWR, TAM, TAP, TCX, TSC, UAE, USA and VKG added. Note updated. - MANPOWER

. Manpower for Config. 02 added. - MATERIAL INFORMATION DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
. Kit A01S01, A03 and Config. 02 added. PLANNING INFORMATION : - EFFECTIVITY

. Para. 1.A. Aircraft model 330-201, 330-202, 330-203, 330-223, 330-243, 330-301, 330-321, 330-323 and 330-343 added. 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 A01S01 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. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- CLOSE-UP

. Para. 3.D. Config. 02 added. - ILLUSTRATIONS

. Figure 3, Sheets 03 and 04 updated. . Figure 4, Sheets 03 and 04 updated. . Figure 5 added. . Figure 6 added. . Figure 7 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. : A330-57-3098

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# A330 SERVICE BULLETIN

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# A330 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 A330-57-3032 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). The Inspection Service Bulletin requires a detailed inspection on A330 aircraft pre Mod. No. 55306S18660 (FUSELAGE-CENTER FUSELAGE-REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) 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 A330-57-3081 for aircraft on which 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).

EVALUATION TABLE COMPLIANCE Recommended CANCELS INSPECTION SB Yes POTENTIAL AD No A/C OPERATION AFFECTED No DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN SUMMARY

EVALUATION TABLE 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 : ACA ACI ADH AFR ALK BMA CPA CRL CYP EDW EEZ EIN FWI GFA GIA GRL HDA HVN IAC JST KAL LTU MAS MON MPD OBS PAL QAF QTR SAS SSV SWR TAM TAP TCX THA TSC UAE USA VKG XLF 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 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 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN SUMMARY

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 573098A01R02 Bolts, nuts and washer Config. 01 Kit 573098A01S01 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN SUMMARY

Bolts Config. 02 Kit 573098A03R03 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. : A330-57-3098

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# A330 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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

# A330 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 330-201 330-202 330-203 330-223 330-243 330-301 330-321 330-322 330-323 330-341 330-342 330-343 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0113 0116 0118-0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171 0172 0177 0181 0183 0184 0188 0189 0191 0195 0198 0200 0203 0205 0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240 0241 0244 0247-0251 0253-0256 0258 0259 0261 0262 0265-0267 0269 0271 0272 0275-0277 0279 0281 0283-0288 0290 0291 0293-0296 0299-0301 0303 0305 0306 0308 0309 0311-0317 0320 0322-0324 0326 0328 0330 0333 0334 0337-0340 0342-0346 0348-0351 0353 0356-0358 0361 0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386 0388 0389 0392 0393 0396-0398 0400 0401 0403-0405 0407-0409 0412 0418-0423 0425 0427 0428 0432 0437 0439 0441 0443 0444 0448 0451 0452 0454-0456 0458 0461-0463 0465 0466 0469 0472 0473 0476 0477 0479-0481 0484 0486 0487 0489-0491 0493 0494 0496-0498 0500-0510 0512 0522 NOTE : This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

A340 COMMONALITY ITEMS) is embodied and modification No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied. (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 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 ADH 0272 0339 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 ALK 0303 0306 0311 0313 BMA 0398 0401 0404 CPA 0113 0118 0121 0155 0244 0386 0389 0393 0418 0420 0421 0423 0439 CRL 0285 0320 CYP 0505 EDW 0369 EEZ 0358 0364 EIN 0269 0330 0397 FWI 0240 0253 GFA 0276 0281 0286 0287 0334 0340 GIA 0138 0140 0144 0148 0153 0165 GRL 0230 HDA 0132 0177 0234 0405 0407 0479 0512 HVN 0255 0262 IAC 0353 0362 JST 0506 0508 0522 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

OPERATOR MSN KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 LTU 0120 0127 0171 0403 0432 0444 0454 0469 0476 0493 MAS 0116 0119 0143 0290 0296 0300 MON 0261 0265 MPD 0205 0211 OBS 0461 PAL 0183 0184 0188 0189 0191 0198 0200 0203 QAF 0487 QTR 0441 0463 0473 0489 0504 SAS 0496 0497 SSV 0357 SWR 0229 0249 0275 0288 0291 0294 0299 0322 0324 0343 0366 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 TAP 0181 0195 0223 0305 0308 0312 0317 TCX 0254 0266 0301 0349 0356 0427 0456 THA 0122 0209 0224 0231 0346 TSC 0250 0271 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0365 0372 0382 0384 0392 0396 0409 0437 0451 0452 0455 0462 0491 0494 0509 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0309 XLF 0501 (c) Effectivity by MSN and Kit/Configuration The Kits and configurations applicable to these MSNs are given at the end of this list 0113 0116 0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 573098A01R02 2 01 The Kits and configurations applicable to these MSNs are given at the end of this list 0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 0253-0256 0258-0259 0261-0262 0265-0267 0269 0271-0272 0275-0277 0279 0281 0283-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0317 0320 0322-0324 0326 0328 0330 0333-0334 0337-0340 0342-0346 0348-0351 0353 0356-0358 0361-0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386 0388-0389 0392-0393 0396-0398 0400-0401 0403-0405 0407-0409 0412 0418-0423 0425 0427-0428 0432 0437 0439 0441 0443-0444 0448 0451-0452 0454-0456 0458 0461-0463 0465-0466 0469 0472-0473 0476-0477 0479-0481 0484 0486-0487 0489-0491 0493-0494 0496-0498 0500-0510 0512 0522 KIT No. QTY PER A/C CONFIGURATION 573098A03R03 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 **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 A330-57-3032 for retrofit. The structural analysis has led to the issue of the Inspection Service Bulletin A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)). DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 4 Printed in France © AIRBUS 2008 All rights reserved

# A330 SERVICE BULLETIN

The Inspection Service Bulletin requires a detailed inspection on A330 aircraft pre Mod. No. 55306S18660 (FUSELAGE-CENTER FUSELAGE-REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) 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 A330-57-3081 for aircraft on which 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. (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.

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

(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. Aircraft A330-300 Post Mod. No. 41652S11819 and pre Mod. No. 44360S13013 Recommended NOT before FC or FH Proposed Compliance 20,550 FC / 62,640 FH (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 A330-300 Post Mod. No. 44360S13013 and pre Mod. No. 49202S16307 A330-200 Post Mod. No. 44360S13013 and pre Mod. No. 49202S16307 Recommended NOT before FC or FH Proposed Compliance 20,550 FC / 62,640 FH 22,640 FC / 48,160 FH

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

**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 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 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

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 **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 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

Service Bulletin No. A330-57-3032 Service Bulletin No. A330-57-3081 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

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

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# A330 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 573098A01R02 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 573098A01S01 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. : A330-57-3098

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# A330 SERVICE BULLETIN

Kit Held by the Operator Supplementary Kits Required Latest Status of Kit INST/DISP 573098A01R01 573098A01S01 573098A01R02 573098A01R02 NONE 573098A01R02 NOTE : Kit 573098A01R02 does not require an Kit 573098A01S01 because Kit 573098A01S01 is included in Kit 573098A01R02. Kit 573098A03R03 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 573098A01R02 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 573098A01S01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 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 573098A03R03 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 Bolt 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 Inhibitingfillet 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. : A330-57-3098

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# A330 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-A330-57-3098-1 This tool reference include all capital, durable and expendable tooling kits regardless of effectivity but capital tooling is normally already and previously bought by the operator as a long term investment or loaned from FTI. - Durable tooling : ref. DK-A330-00057-3098-1 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-A330-57-3098-1 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 14 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

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# A330 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 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. : A330-57-3098

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# A330 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 A330-57-3081, 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. : A330-57-3098

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# A330 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 573098A01R02 Refer to Figure 3 NOTE : Description below is given for one side of the aircraft, two Kit 573098A01R02 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. : A330-57-3098

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# A330 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. : A330-57-3098

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# A330 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-A330-57-3098-1. b Clean the drilled area.
c Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 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-A330-57-3098-1.
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. : A330-57-3098

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# A330 SERVICE BULLETIN

NOTE(01) Description below is given for one side of the aircraft, two Kit 573098A01R02 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. : A330-57-3098

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# A330 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-A330-57-3098-1. Clean the drilled area. b Do the cold working of the hole 6 (Refer to SRM 51-48-00). Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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. : A330-57-3098

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# A330 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. : A330-57-3098

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# A330 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. : A330-57-3098

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# A330 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 573098A03R03 Refer to Figures 5 and 6 NOTE(01) Description below is given for one side of the aircraft, two Kit 573098A03R03 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 27 Printed in France © AIRBUS 2008 All rights reserved

# A330 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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
e Clean the drilled area. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 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. : A330-57-3098

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# A330 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-A330-57-3098-1.
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-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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) and Internal Top Coat (Mat. No. 16-002C) after assembly in the hole.
DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

NOTE(05) Do a seal bead with Corrosion Inhibitingfillet 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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
e Clean the drilled area. f Install : 1 Bolt EN6115-6Y-16 Item 28 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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

# A330 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. : A330-57-3098

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# A330 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-A330-57-3098-1.
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-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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 Aluminum (Mat. No. 13-002). 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 Consistency (Mat. No. 09-016B) in the hole on the edge of the plug Item 38. 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). DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
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. : A330-57-3098

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# A330 SERVICE BULLETIN

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.). Use tool list No. DK-A330-57-3098-1. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

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-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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 Inhibitingfillet 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. Refer to Figure 6, Sheets 1 and 2 DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 SERVICE BULLETIN

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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
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. : A330-57-3098

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# A330 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-A330-57-3098-1.
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-A330-57-3098-1 and EK-A330-57-3098-1. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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# A330 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-A330-57-3098-1. 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 Inhibitingfillet 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. : A330-57-3098

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# A330 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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
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. : A330-57-3098

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# A330 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 573098A03R03 Refer to Figure 7 NOTE(01) Description below is given for one side of the aircraft, two Kit 573098A03R03 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. : A330-57-3098

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# A330 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-A330-57-3098-1.
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-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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 Inhibitingfillet 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. : A330-57-3098

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

# A330 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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
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. : A330-57-3098

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

# A330 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 573098A03R03 Refer to Figure 8 NOTE(01) Description below is given for one side of the aircraft, two Kit 573098A03R03 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. : A330-57-3098

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

# A330 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-A330-57-3098-1.
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-A330-57-3098-1 and EK-A330-57-3098-1.
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-A330-57-3098-1. 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. : A330-57-3098

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

# A330 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 withCorrosion Inhibitingfillet 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-A330-57-3098-1. 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-A330-57-3098-1 and EK-A330-57-3098-1. 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-A330-57-3098-1.
e Clean the drilled area. DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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

# A330 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. : A330-57-3098

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

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 48 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 49 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 50 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 51 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 52 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 53 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 54 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 55 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 56 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 57 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 58 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 59 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 60 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 61 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 62 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 63 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 64 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 65 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 66 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 67 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 68 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 69 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 70 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 71 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 72 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 73 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 74 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 75 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 76 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 77 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 78 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 1 Printed in France © AIRBUS 2008 All rights reserved

# A330 SERVICE BULLETIN APPENDIX 1

Figure 1, Sheet 1 Inspection Report DATE : Aug 30/07 SERVICE BULLETIN No. : A330-57-3098

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

# A330 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 t at 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved

# A330 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. : A330-57-3098

REVISION No. : 01 - Jul 31/09 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved