# @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 FUSELAGE - MODIFY FASTENERS IN FR40 KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA. MODIFICATION No.: 54459S18477 This page transmits Revision No.01 of Service Bulletin No.A330-57-3090 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to update the installation of the bolts and washers. CHANGES SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Minor editorial or document structure change N GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-FSAAA Minor editorial or document structure change N Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 1 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Minor editorial or document structure change N Objective/Action Minor editorial or document structure change N Advantages Minor editorial or document structure change N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Minor editorial or document structure change N Classification Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N LIST OF COMPONENTS Minor editorial or document structure change N Kit 573090A01R02 Minor editorial or document structure change N Supplementary Kit 573090A01S01 Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N Consumable CMLA01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 2 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Tooling - Price and Availability Minor editorial or document structure change N Tools Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 573090- 831-801-001- MODIFICATION Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Subtask 573090-910-001-001 Minor editorial or document structure change N Subtask 573090-839-001-001 Minor editorial or document structure change N Subtask 573090-941-002-001 Minor editorial or document structure change N Subtask 573090-020-001-001 Minor editorial or document structure change N Subtask 573090-831-005-001 Minor editorial or document structure change N Subtask 573090-831-006-001 Minor editorial or document structure change N Subtask 573090-831-007-001 Minor editorial or document structure change N Subtask 573090-420-001-001 Minor editorial or document structure change N Subtask 573090-941-001-001 Minor editorial or document structure change N Subtask 573090-700-001-001 Minor editorial or document structure change N Subtask 573090-942-001-001 Minor editorial or document structure change N Fig. A-FHAAA Minor editorial or document structure change N Fig. A-FHAAA Sheet 01 Minor editorial or document structure change N Fig. A-FHBAA Minor editorial or document structure change N Fig. A-FHBAA Sheet 01 Minor editorial or document structure change N Fig. A-FBAAA Minor editorial or document structure change N Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N Fig. A-FBAAA Sheet 02 Minor editorial or document structure change N Fig. A-FBAAA Sheet 03 Minor editorial or document structure change N Fig. A-FBAAA Sheet 04 Minor editorial or document structure change N Fig. A-FBAAA Sheet 05 Minor editorial or document structure change N Fig. A-FBAAA Sheet 06 Minor editorial or document structure change N Fig. A-FBBAA Minor editorial or document structure change N Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N Fig. A-FBBAA Sheet 02 Minor editorial or document structure change N Fig. A-FBBAA Sheet 03 Minor editorial or document structure change N Fig. A-FBEAA Minor editorial or document structure change N Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N Fig. A-FBEAA Sheet 02 Minor editorial or document structure change N Fig. A-FBEAA Sheet 03 Minor editorial or document structure change N Fig. A-FBHAA Minor editorial or document structure change N Fig. A-FBHAA Sheet 01 Minor editorial or document structure change N Fig. A-FBHAA Sheet 02 Minor editorial or document structure change N Fig. A-FBHAA Sheet 03 Minor editorial or document structure change N
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 3 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-FGAAA Minor editorial or document structure change N Fig. A-FGAAA Sheet 01 Minor editorial or document structure change N Fig. A-FGAAA Sheet 02 Minor editorial or document structure change N Fig. A-FGAAA Sheet 03 Minor editorial or document structure change N FILLING INSTRUCTIONS HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Mar 27/06 REVISION No. : 01 - Jun 15/11

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 4 5

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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 FUSELAGE - MODIFY FASTENERS IN FR40 KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA. **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 54459S18477 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On the A330 and A340 aircraft fatigue test specimen, cracks appeared on the right and left sides between the crossing area of the keel beam fitting and the front spar of the Center Wing Box (CWB). The damage was found at 31,717 simulated Flight Cycles (FC). Modification Service Bulletin No. A330-57-3032 (Mod. No. 43577S12677 (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION)) has been issued to remove possible damage at the crossing area of the keel beam fitting and the front spar of the CWB and to improve the fatigue strength of the area by means of 4 spotfacings on the lower keel fitting and installation of the reinforcement fitting. A cold working of the holes going through the reinforcement fitting, the lower angle and the FR40 is also performed. During accomplishment of the above mentioned modification Service Bulletin No. A330-57-3032 some cracks findings outside Service Bulletin limits have been reported. Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLE AT FRAME 40 (UNREPAIRED AIRCRAFT)) requiring a special detailed inspection on the horizontal flange of the keel beam in the area of first fastener hole aft of FR40. This Service Bulletin consists in disconnecting one more fastener from the keel beam/bottom skin panel junction by reaming a hole into the keel beam and oversizing the fastener.
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 1 5

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# @A330 SERVICE BULLETIN SUMMARY Then, the two adjacent fasteners are removed in order to perform cold working and to install interference fit fasteners. Accomplishment of this Service Bulletin will avoid initiation of cracks at the crossing area of the keel beam fitting and the lower panel of the Center Wing Box (CWB). Accomplishment of this Service Bulletin cancels the inspection requirements of Inspection Service Bulletin No. A330-57-3081. The ALI task 571162 is to be created to inspect the fastener holes of the forward lower panel. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES POTENTIAL AD NO A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational disruptions. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573090A01R02 2 2,860.00 Bushes, bolts, nuts and washers. Supplementary kit

573090A01S01 2 1,130.00 Bolts, nuts and washers. TOTAL 3,990.00 EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

BEL CPA EIN HDA HFY HVN MAS OHY THA TSC VLK XAX NOTE: This modification is applicable by Service Bulletin only. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.005 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 2 5

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# @A330 SERVICE BULLETIN SUMMARY LIFE LIMIT None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 573090-831-801-001: MODIFICATION TOTAL MANHOURS 76.00 ELAPSED TIME (HOURS) 41.50 APPENDICES None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY
**CONF ALL

STGR1 

### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

### C

FR40 DATUM Y−1959

FASTENERS REPLACED G_SB_573090_5_SAAA_01_00 Figure A-FSAAA - Sheet 01

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 4 5

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# @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 FUSELAGE - MODIFY FASTENERS IN FR40 KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA. MODIFICATION No.: 54459S18477 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This modification is applicable by Service Bulletin only. NOTE: This Service Bulletin is only applicable on aircraft on which Mod. No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is not embodied. (1) Models 330-301 330-321 330-322 330-342 (2) Effectivity by MSN 0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073 0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0112 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 1 5

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# @A330 SERVICE BULLETIN
OPERATOR MSN BEL 0030 0037 0045 0082 0095 CPA 0012 0017 0071 0102 EIN 0059 HDA 0083 0099 0106 0109 HFY 0096 HVN 0087 MAS 0067 0069 0073 0077 0100 0107 0110 OHY 0072 0098 THA 0050 0060 0062 0064 0065 0066 0112 TSC 0111 VLK 0055 0070 0086 XAX 0054 (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062 0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082 0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107 0109 0110 0111 0112 001
(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 573090A01R02 2 Supplementary kit 573090A01S01 2 Consumable CMLA01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History On the A330 and A340 aircraft fatigue test specimen, cracks appeared on the right and left sides between the crossing area of the keel beam fitting and the front spar of the Center Wing Box (CWB). The damage was found at 31,717 simulated Flight Cycles (FC).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 2 5

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# @A330 SERVICE BULLETIN Modification Service Bulletin No. A330-57-3032 (Mod. No. 43577S12677 (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION)) has been issued to remove possible damage at the crossing area of the keel beam fitting and the front spar of the CWB and to improve the fatigue strength of the area by means of 4 spotfacings on the lower keel fitting and installation of the reinforcement fitting. A cold working of the holes going through the reinforcement fitting, the lower angle and the FR40 is also performed. During accomplishment of the above mentioned modification Service Bulletin No. A330-57-3032 some cracks findings outside Service Bulletin limits have been reported. Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLE AT FRAME 40 (UNREPAIRED AIRCRAFT)) requiring a special detailed inspection on the horizontal flange of the keel beam in the area of first fastener hole aft of FR40. (2) Objective/Action This Service Bulletin consists in disconnecting one more fastener from the keel beam/bottom skin panel junction by reaming a hole into the keel beam and oversizing the fastener. Then, the two adjacent fasteners are removed in order to perform cold working and to install interference fit fasteners. (3) Advantages Accomplishment of this Service Bulletin will avoid initiation of cracks at the crossing area of the keel beam fitting and the lower panel of the Center Wing Box (CWB). Accomplishment of this Service Bulletin cancels the inspection requirements of Inspection Service Bulletin No. A330-57-3081. The ALI task 571162 is to be created to inspect the fastener holes of the forward lower panel. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 573090-831-801-001: MODIFICATION (1) On the LH and RH sides, Remove Only if Necessary the Ducts between FR39.1 AND FR40 for Access. (2) On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft without bushes). DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 3 5

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# @A330 SERVICE BULLETIN (3) On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft repaired with bushes). (4) On the LH and RH sides of the center tank at FR40, replace the fasteners of the FWD lower panel. (5) On the LH and RH sides, Install (if removed) the Ducts between FR39.1 and Fr40. E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale 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 pre Mod. No. 41652S11819 Recommended NOT before FC or FH whichever occurs later Proposed Compliance 20,050 FC / 61,140 FH F. APPROVAL Approved under EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 573090-831-801-001: MODIFICATION Get Access 9.00 On Aircraft On the LH and RH sides, Remove Only if Necessary the Ducts between FR39.1 AND FR40 for Access. 3.00 On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft without bushes). 16.00

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 4 5

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# @A330 SERVICE BULLETIN
Task 573090-831-801-001: MODIFICATION On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft repaired with bushes). 16.00 On the LH and RH sides of the center tank at FR40, replace the fasteners of the FWD lower panel. 14.00 On the LH and RH sides, Install (if removed) the Ducts between FR39.1 and Fr40. 3.00 Tests 3.00 Close-Up 12.00 TOTAL MANHOURS 76.00 ELAPSED TIME (HOURS) 41.50 NOTE: The total manhours for one aircraft modified is 60.00 hours. H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11 20-28-00 21-20-00 21-53-18 23-53-18 28-11-00 32-12-00 36-12-41 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-18 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Service Bulletin (SB) A330-57-3032 A330-57-3081 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-42-11 51-44-11 51-48-00 51-76-12 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 5 5

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# @A330 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 6 5

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 573090A01R02 Supplementary kit 573090A01S01 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 Material, Logistics and Suppliers Weg beim Jeager 150 D-22335 Hamburg Germany For ordering by internet : http://spares.airbus.com For ordering modification kits by fax : +49 40 50 76 25 90 For ordering of single spares by fax : +49 40 50 76 40 13 (2) Price and Availability NOTE: Operator that has already received Kit 573090A01 at previous revision must complete it as per table below : Kit held by operator Supplementary kit required latest status of kit INST/DISP 573090A01R01 573090A01S01 573090A01R02 573090A01R02 NONE 573090A01R02 Kit 573090A01R02 does not require an Kit 573090A01S01 because Kit 573090A01S01 is included in 573090A01R02. Kit 573090A01R02 Cost 1,430.00 USD Availability 180 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Supplementary kit 573090A01S01 Cost 565.00 USD Availability 180 calendar days from receipt of order

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 7 5

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# @A330 SERVICE BULLETIN The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy. C. LIST OF COMPONENTS Kit 573090A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 EN6115V6Y11 1 Bolt 8 ASNA2528-6 1 Nut 9 NSA5368PD616A 1 Washer 10 EN6115V5Y12 1 Bolt 11 ASNA2528-5 1 Nut 12 NSA5368PD516A 1 Washer 13 F5332433320000 1 Bush 14 F5332433320200 1 Bush 17 F5332433320400 1 Bush 18 EN6115V5X12 1 Bolt 19 EN6115V6X13 1 Bolt 20 NSA5368-616A 1 Washer 21 NSA5368-516A 1 Washer 22 ASNA2531-6 1 Nut 23 ASNA2531-5 1 Nut 39 NSA5368PD616B 1 Washer 40 NSA5368-616B 1 Washer 41 NSA5368-516B 1 Washer 42 NSA5368PD516B 1 Washer 48 EN6115V5X13 1 Bolt 49 EN6115V6X14 1 Bolt NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Supplementary kit 573090A01S01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 EN6115V6Y11 1 Bolt 9 NSA5368PD616A 1 Washer DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 8 5

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 10 EN6115V5Y12 1 Bolt 12 NSA5368PD516A 1 Washer 18 EN6115V5X12 1 Bolt 19 EN6115V6X13 1 Bolt 20 NSA5368-616A 1 Washer 21 NSA5368-516A 1 Washer 22 ASNA2531-6 1 Nut 23 ASNA2531-5 1 Nut 39 NSA5368PD616B 1 Washer 40 NSA5368-616B 1 Washer 41 NSA5368-516B 1 Washer 42 NSA5368PD516B 1 Washer 48 EN6115V5X13 1 Bolt 49 EN6115V6X14 1 Bolt NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Low Density Fuel Tank Sealant 09-002D As required Corrosion Inhibiting Brush Consistency 09-013B As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Polyurethane Primer 16-001C As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 9 5

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# @A330 SERVICE BULLETIN
F. TOOLING (1) Tooling - Price and Availability None (2) Tools (a) To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. - Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6. - Tools necessary to do the check by ROTOTEST : 1. Instrument Rototest B588 and rotor standard. Supplier : ROHMANN GMBH Rudolf Diesel Str.13 D - 67227 FRANKENTHAL Tel. : 49.(0)6233/3789 - 0 Fax. : 49.(0)6233/3789 - 77 GERMANY 2. Probe RS50-7-9 (0.311 in.). Supplier : ROHMANN GMBH Rudolf Diesel Str.13 D - 67227 FRANKENTHAL Tel. : 49.(0)6233/3789 - 0 Fax. : 49.(0)6233/3789 - 77 GERMANY 3. Calibration standard : 99A53003001101. AIRBUS WEG BEIM JAEGER 150 D - 22453 HAMBURG Tel. : 49.(0)40/5076 - 0 Fax. : 49.(0)40/503168 GERMANY - Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6.
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 10 5

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# @A330 SERVICE BULLETIN (b) 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-A330-57-3090-1 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-A330-57-3090-1 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-A330-57-3090-1 NOTE : In this expendable tool, there is the minimum quantiy 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 : 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 (3) Special Tools None

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 11 5

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# @A330 SERVICE BULLETIN

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DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 12 5

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 573090-831-801-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE WHEEL CHOCKS ARE IN POSITION. MOVEMENTS OF THE AIRCRAFT CAN BE DANGEROUS. WARNING: MAKE SURE THAT THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START A REFUEL/DEFUEL PROCEDURE. IN THIS SAFE AREA, DO NOT LET PERSONS : - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR THE TASK. AIRCRAFT FUEL IS FLAMMABLE. WARNING: DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSE FIRES. WARNING: MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT AVAILABLE. WARNING: DO NOT GET AIRCRAFT FUEL : - IN YOUR MOUTH - IN YOUR EYES - ON YOUR SKIN FOR A LONG TIME. WARNING: MAKE SURE THAT GROUND SAFETY - LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 13 5

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# @A330 SERVICE BULLETIN
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. Task Associated Data Manpower TOTAL MANHOURS 76.00 ELAPSED TIME (HOURS) 41.50 A. GENERAL (1) Subtask 573090-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Low Density Fuel Tank Sealant 09-002D Corrosion Inhibiting Brush Consistency 09-013B Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 Polyurethane Primer 16-001C References Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201 Consumable Material List (CML) Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 14 5

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# @A330 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-42-11 51-44-11 51-48-00 51-76-12 (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 11-026 As required

. (c) Use a non-metallic spatula to remove the sealant and clean the areas with Solvent General Purpose 11-026 As required

. (d) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (e) Drill and deburr the holes (Refer to SRM 51-44-11). (f) Remove and install the fasteners (Refer to SRM 51-42-11). (g) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201). (h) Do the cold expansion of the holes (Refer to SRM 51-48-00). (i) Apply the sealant (Refer to SRM 51-76-12). (j) Apply the Corrosion Inhibiting Brush Consistency 09-013B As required

on all the fasteners to be installed (wet assembly). (k) Apply the Low Density Fuel Tank Sealant 09-002D As required

on the fasteners inside center tank at FR40.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 15 5

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# @A330 SERVICE BULLETIN (l) Protect the spotfacing areas with Chemical Conversion Coating Yellow Aluminum 13-002 As required

and Polyurethane Primer 16-001C As required

. (m) Install the bushes with liquid nitrogen (Refer to PMS 01-05-05). (2) Subtask 573090-839-001-001 - Administrative Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. B. PREPARATION (1) Subtask 573090-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24, Page Block 201 21-20-00, Page Block 201 21-53-18, Page Block 401 32-12-00, Page Block 201 36-12-41, Page Block 401 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Put the access platform(s) in position. (c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201).(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (e) Do the preparation procedure as specified in removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401).
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 16 5

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# @A330 SERVICE BULLETIN (g) Remove the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). C. PROCEDURE (1) Subtask 573090-020-001-001 - On the LH and RH sides, Remove Only if Necessary the Ducts between FR39.1 AND FR40 for Access. Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401 Fig. A-FHAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for access. Sheet 01
Fig. A-FHBAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40, for access. Sheet 01

NOTE: On the LH and RH sides, remove only if necessary the ducts between FR39.1 and FR40, for access. (a) On RH side, remove the air conditioning duct. Refer to Fig. A-FHAAA 1 Remove : 1 Duct Item (26) Retain 1 Insulation Item (25) Retain 1 Nut Item (28) Retain 1 Bolt Item (29) Retain 1 Washer Item (30) Retain 2 Screw Item (31) Retain

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 17 5

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# @A330 SERVICE BULLETIN 2 Washer Item (32) Retain 2 Nut Item (33) Retain 1 Clamp Item (34) Retain 1 Clamp Item (27) Retain NOTE (01): Disconnect and move the rod Items (35) and (36) without removal. NOTE (02): Remove the Insulation Item (35) with associated clamp Item (27) from the duct Item (26) only if necessary. NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). (b) On RH side, remove the air ventilation duct. Refer to Fig. A-FHBAA 1 Remove : 1 Duct Item (36) Retain 8 Clamp Item (33) Retain 4 Clamp Item (32) Retain 2 Sleeve Item (34) Retain 1 Sleeve Item (35) Retain (c) On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401). (d) Put the blanking plugs on the disconnected line ends. (2) Subtask 573090-831-005-001 - On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft without bushes). Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 18 5

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# @A330 SERVICE BULLETIN Material necessary to do the job Kit 573090A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 EN6115V6Y11 1 Bolt 8 ASNA2528-6 1 Nut 9 NSA5368PD616A 1 Washer 10 EN6115V5Y12 1 Bolt 11 ASNA2528-5 1 Nut 12 NSA5368PD516A 1 Washer 13 F5332433320000 1 Bush 14 F5332433320200 1 Bush 39 NSA5368PD616B 1 Washer 42 NSA5368PD516B 1 Washer Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Low Density Fuel Tank Sealant 09-002D As required Corrosion Inhibiting Brush Consistency 09-013B As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Polyurethane Primer 16-001C As required References Non Destructive Test Manual (NTM) 51-10-01 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 Fig. A-FBAAA Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 NOTE (01): Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.) shall be used. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 19 5

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# @A330 SERVICE BULLETIN
NOTE (02): The installed fasteners shall be checked in accordance with the requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that an adequate thread protusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two Kit 573090A01R02 are necessary to modify one aircraft. (a) Inspect the hole. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 1 Remove : 1 Screw Item (7) Discard 1 Nut Item (8) Discard 2 Remove the sealant and clean the hole. 3 Do a rotating inspection of the hole (Refer to NTM 51-10-01). a If no crack is detected, do the operations given in paragraph 3.C.(2).(b), b If crack is detected in the keel beam only, do the operations given in paragraph 3.C.(2).(c), c If crack is detected in the CWB lower panel only or in CWB lower panel and the keel beam, do the operations given in paragraph . 3.C.(2).(d). (b) No crack, oversize the hole in the keel beam. Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03 1 Ream the hole at the level of the keel beam only to a diameter comprised between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm (0.827in.). 3 Oversize the hole in the CWB lower panel, shim and gusset to a diameter comprised between 10.177mm (0.4in.) and 10.219 mm (0.402in.). 4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm (0.4in.). 5 Clean the drilled area.

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# @A330 SERVICE BULLETIN
6 Install : 1 Bolt EN6115V6Y11 Item 7 1 Nut ASNA2528-6 Item 8 1 Washer NSA5368PD616A Item 9 or 1 Washer NSA5368PD616B Item 39 NOTE (01): Before installation of the fasteners (wet assembly), apply : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required (c) Crack detected in the keel beam only. Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 04 1 Ream the hole at the level of the keel beam only to a diameter comprised between 19mm(0.748in.) and 19.2mm(0.756in.). Admissible reaming depth in the CWB lower panel is comprised between 0.5mm (0.02in.) and 0.7mm (0.028in.). 2 Do a rotating inspection of the hole in the keel beam (Refer to NTM 51-10-01). a Crack finding, contact AIRBUS. b No crack finding, oversize the hole in the keel beam to a diameter comprised between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). c Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm (0.827in.). DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 21 5

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# @A330 SERVICE BULLETIN
d Oversize the hole in the CWB lower panel, shim and gusset to a diameter comprised between 10.177mm (0.4in.) and 10.219 mm (0.402in.). e Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm (0.4in.). f Install : 1 Bolt EN6115V6Y11 Item 7 1 Nut ASNA2528-6 Item 8 1 Washer NSA5368PD616A Item 9 or 1 Washer NSA5368PD616B Item 39 NOTE (01): Before installation of the fasteners (wet assembly), apply : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required (d) Crack detected in the CWB lower panel only and/or in the CWB lower panel and the keel beam. Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02, Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 06 1 Ream the hole in the keel beam and the CWB lower panel to diameter comprised between 11.1mm (0.437in.) and 11.3mm (0.445in.). Admissible reaming depth in the shim is comprised between 0.5mm (0.02in.) and 0.7mm. (0.028in.).

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# @A330 SERVICE BULLETIN
2 Do a rotating inspection of the hole in the keel beam and the CWB lower panel (Refer to NTM 51-10-01). a If no crack is detected in the CWB lower panel, do the operations given in paragraph 3.C.(2)(d)3, b If crack is detected in the CWB lower panel, do the operations given in paragraph 3.C.(2)(d)4. 3 No crack finding in the CWB lower panel. Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 05 a Ream the hole in the keel beam and the CWB lower panel to diameter comprised between 13.1mm (0.516in.) and 13.12mm (0.517in.). Admissible reaming depth in the shim 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. 13.1mm (0.516in.). c Ream the hole at the level of the keel beam only to a diameter comprised between 19mm(0.748in.) and 19.2mm(0.756in.). Admissible reaming depth in the CWB lower panel is comprised between 0.5mm (0.02in.) and 0.7mm. (0.028in.). d Do a rotating inspection of the hole in the keel beam (Refer to NTM 51-10-01). <1> Crack finding, contact AIRBUS. <2> No crack finding, oversize the hole in the keel beam to a diameter comprised between 21mm (0.827in.) and 21.2mm (0.835in.) 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.). e Oversize the hole in the shim and the gusset to a diameter comprised between 8.692mm (0.342in.) and 8.732mm (0.344in.). f Install a stepped bush in the bottom skin panel : 1 Bush F5332433320000 Item 13 1 Bolt EN6115V5Y12 Item 10 1 Nut ASNA2528-5 Item 11 1 Washer NSA5368PD516A Item 12 or 1 Washer NSA5368PD516B Item 42 DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 23 5

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# @A330 SERVICE BULLETIN
NOTE (01): Before installation of the fasteners (wet assembly), apply : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required NOTE (04): Install the bush Item 13 with liquid nitrogen (Refer to Process and Material Specification (PMS) 01-05-05). 4 Crack finding in the CWB lower panel. Refer to Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 02 and Fig. A-FBAAA Sheet 06 a Ream the hole in the keel beam and the CWB lower panel to diameter comprised between 13.1mm (0.516in.) and 13.3mm (0.524in.). Admissible reaming depth in the shim is comprised between 0.5mm (0.02in.) and 0.7mm. (0.028in.). b Do a rotating inspection of the hole in the CWB lower panel and the keel beam (Refer to NTM 51-10-01). <1> Crack finding, contact AIRBUS. <2> No crack finding, oversize the hole in the keel beam and the CWB lower panel to a diameter comprised between 15mm (0.591 in.) and 15.02mm (0.592in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the shim is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). <3> Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 15mm (0.591 in.). <4> Oversize the hole in the keel beam only to a diameter comprised between 21mm (0.827in.) and 21.2mm (0.835in.) 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.).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 24 5

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# @A330 SERVICE BULLETIN <5> Do a rotating inspection of the hole in the keel beam (Refer to NTM 51-10-01). <6> Crack finding, contact AIRBUS. <7> No crack finding, oversize the hole in the keel beam to a diameter comprised between 23mm (0.906in.) and 23.2mm (0.913in.) 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.). <8> Oversize the hole in the shim and the gusset to a diameter comprised between 8.692mm (0.342in.) and 8.732mm (0.344in.). <9> Install a stepped bush in the bottom skin panel : 1 Bush F5332433320200 Item 14 1 Bolt EN6115V5Y12 Item 10 1 Nut ASNA2528-5 Item 11 1 Washer NSA5368PD516A Item 12 or 1 Washer NSA5368PD516B Item 42 NOTE (01): Before installation of the fasteners (wet assembly), apply : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required NOTE (04): Install the bush Item 14 with liquid nitrogen (Refer to Process and Material Specification (PMS) 01-05-05).

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 25 5

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# @A330 SERVICE BULLETIN (3) Subtask 573090-831-006-001 - On the LH and RH sides of the center tank at FR40, replace the keel beam fasteners (for aircraft repaired with bushes). Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 573090A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 EN6115V6Y11 1 Bolt 8 ASNA2528-6 1 Nut 9 NSA5368PD616A 1 Washer 10 EN6115V5Y12 1 Bolt 11 ASNA2528-5 1 Nut 12 NSA5368PD516A 1 Washer 17 F5332433320400 1 Bush 39 NSA5368PD616B 1 Washer 42 NSA5368PD516B 1 Washer Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Low Density Fuel Tank Sealant 09-002D As required Corrosion Inhibiting Brush Consistency 09-013B As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Polyurethane Primer 16-001C As required References Non Destructive Test Manual (NTM) 51-10-01 Process and Material Specification (PMS) Process and Material Specification (PMS) 01-05-05 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 Fig. A-FBBAA Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH and RH sides. Sheet 01 Sheet 02 Sheet 03

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 26 5

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# @A330 SERVICE BULLETIN
References Fig. A-FBEAA Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or = 21mm (0.827in.)), LH and RH sides. Sheet 01 Sheet 02 Sheet 03 Fig. A-FBHAA Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and RH sides. Sheet 01 Sheet 02 Sheet 03 NOTE (01): Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.) shall be used. NOTE (02): The installed fasteners shall be checked in accordance with the requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that an adequate thread protusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two Kit 573090A01R02 are necessary to modify one aircraft. (a) Inspect the hole. Refer to Fig. A-FBBAA, Fig. A-FBEAAand Fig. A-FBHAA 1 Remove : 1 Screw Item (7) Discard 1 Nut Item (8) Discard 1 Bush Item (15) Discard or 1 Screw Item (10) Discard 1 Nut Item (11) Discard 1 Bush Item (17) Discard
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 27 5

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# @A330 SERVICE BULLETIN
2 Remove the sealant and clean the hole. 3 Do a rotating inspection of the hole (Refer to NTM 51-10-01). a If case of crack finding : contact AIRBUS, b If the bush with a diameter upper than 15mm (0.591in.) is installed in the keel beam and the CWB lower panel, contact AIRBUS, c If the bush with a diameter upper than 21mm (0.827in.) is installed in the keel beam only contact AIRBUS, d If no crack is detected and if the bush with a diameter lower or equal than 19mm (0.748in.) is installed in the keel beam only, do the operations given in paragraph 3.C.(3)(b), e If no crack is detected and if the bush with a diameter upper than 19mm (0.748in.) and lower or egal than 21mm (0.827in.) is installed in the keel beam only, do the operations given in paragraph 3.C.(3)(c), f If no crack is detected and if the bush with a diameter lower than 15mm (0.591in.) is installed in the keel beam and the CWB lower panel, do the operations given in paragraph 3.C.(3)(d). (b) No crack (bush dia. < or = 19mm (0.748in.), oversize the hole in the keel beam. Refer to Fig. A-FBBAA Sheet 01 thru Fig. A-FBBAA Sheet 03 1 Oversize the hole in the keel beam only to a diameter comprised between 21mm (0.827in.) and 21.2mm (0.835in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 21mm (0.827in.). 3 Oversize the hole in the CWB lower panel, the shim and the gusset to a diameter comprised between 10.177mm (0.4in.) and 10.219mm (0.402in.). 4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm (0.4in.). 5 Install : 1 Bolt EN6115V6Y11 Item 7 1 Nut ASNA2528-6 Item 8 1 Washer NSA5368PD616A Item 9 or 1 Washer NSA5368PD616B Item 39
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 28 5

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# @A330 SERVICE BULLETIN
NOTE (01): Before installation of the fasteners (wet assembly), apply : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required (c) No crack (19mm (0.748in.) < bush dia. < or = 21mm (0.827in.)), oversize the hole in the keel beam. Refer to figure Fig. A-FBEAA Sheet 01 thru Fig. A-FBEAA Sheet 03 1 Oversize the hole in the keel beam only to a diameter comprised between 23mm (0.906in.) and 23.2mm (0.913in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 23mm (0.906in.). 3 Oversize the hole in the shim and the gusset to a diameter comprised between 10.177mm (0.4in.) and 10.219mm (0.402in.). 4 Do a chamfer of 0.8mm*0.8mm (0.031in.*0.031in.) on the hole dia. 10.177mm (0.4in.). 5 Install : 1 Bolt EN6115V6Y11 Item 7 1 Nut ASNA2528-6 Item 8 1 Washer NSA5368PD616A Item 9 or 1 Washer NSA5368PD616B Item 39 NOTE (01): Apply, before installation of the fasteners (wet assembly) :

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 29 5

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# @A330 SERVICE BULLETIN Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply the on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required (d) No crack (bush dia. < or = 15mm (0.591in.), oversize the hole in the keel beam. Refer to Fig. A-FBHAA Sheet 01 thru Fig. A-FBHAA Sheet 03 1 Oversize the hole in the keel beam and the CWB lower panel to a diameter comprised between 17mm (0.669in.) and 17.02mm (0.670in.) with a radius of 2mm (0.079in.). Admissible reaming depth in the shim is comprised between 1mm (0.039in.) and 1.2mm (0.047in.). 2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm (0.669in.). 3 Oversize the hole in the keel beam only to a diameter comprised between 26mm (1.024in.) and 26.2mm (1.031in.) 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.). 4 Oversize the hole in the shim and the gusset to a diameter comprised between 8.692mm (0.342in.) and 8.732mm (0.344in.). 5 Install a stepped bush in the bottom skin panel : 1 Bush F5332433320400 Item 17 1 Bolt EN6115V5Y12 Item 10 1 Nut ASNA2528-5 Item 11 1 Washer NSA5368PD516A Item 12 or 1 Washer NSA5368PD516B Item 42 NOTE (01): Apply, before installation of the fasteners (wet assembly) : DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 30 5

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# @A330 SERVICE BULLETIN Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required NOTE (04): Install the bush Item 17 with liquid nitrogen (Refer to PMS 01-05-05). (4) Subtask 573090-831-007-001 - On the LH and RH sides of the center tank at FR40, replace the fasteners of the FWD lower panel. Manpower Resources Manhours 14.00 Minimum number of person 2 Subtask elapsed time 7.00 Skills AIRFRAME Material necessary to do the job Kit 573090A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 EN6115V5X12 1 Bolt 19 EN6115V6X13 1 Bolt 20 NSA5368-616A 1 Washer 21 NSA5368-516A 1 Washer 22 ASNA2531-6 1 Nut 23 ASNA2531-5 1 Nut 40 NSA5368-616B 1 Washer 41 NSA5368-516B 1 Washer 48 EN6115V5X13 1 Bolt 49 EN6115V6X14 1 Bolt

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 31 5

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# @A330 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Low Density Fuel Tank Sealant 09-002D As required Corrosion Inhibiting Brush Consistency 09-013B As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Polyurethane Primer 16-001C As required References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14 51-48-00 Fig. A-FGAAA Replacement of the Fasteners on the FWD lower Panel, LH and RH sides. Sheet 01 Sheet 02 Sheet 03 NOTE (01): Firstly, the stack up assembly must be checked to determine the actual length of the bolt to be used. After measurement, if the shank protusion above the stack up assembly is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm (0.031in.) shall be used. Otherwise if the shank protusion is between 0.8mm (0.031in.) and 1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063 in.) shall be used. NOTE (02): The installed fasteners shall be checked in accordance with the requirement of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure that an adequate thread protusion is maintained after installation.Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations. NOTE: Description below is given for one side of the aircraft, two Kit 573090A01R02 are necessary to modify one aircraft. (a) Remove : Refer to Fig. A-FGAAA Sheet 01 thru Fig. A-FGAAA Sheet 02 1 Screw Item (18) Discard 1 Screw Item (19) Discard 1 Nut Item (8) Discard

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 32 5

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# @A330 SERVICE BULLETIN 1 Nut Item (11) Discard (b) Remove the sealant and clean the holes. (c) Do a rotating inspection, (Refer to NTM 51-10-01). 1 If a crack is detected, contact AIRBUS. 2 If no crack is detected, do the operations given in paragraph 3.C.(4)(d). (d) Do the cold working of the holes. Refer to Fig. A-FGAAA Sheet 01 and Fig. A-FGAAA Sheet 03 1 Ream the holes to the starting hole diameter of the cold working as shown on Fig. A-FGAAA Sheet 03
. Use tool list No. DK-A330-57-3090-1. 2 Clean the drilles area. 3 Do the cold working of the holes (Refer to SRM 51-48-00). Use FTI tool list No. FTI-A330-57-3090-1 and EK-A330-57-3090-1. 4 Ream the holes to the final hole diameter (Refer to Fig. A-FGAAA Sheet 01 and Fig. A-FGAAA Sheet 03). Use FTI tool list No. DK-A330-57-3090-1. 5 Clean the drilled area. 6 Install : 1 Bolt EN6115V5X12 Item 18 or 1 Bolt EN6115V5X13 Item 48 1 Bolt EN6115V6X13 Item 19 or 1 Bolt EN6115V6X14 Item 49 1 Nut ASNA2531-5 Item 23 1 Nut ASNA2531-6 Item 22 1 Washer NSA5368-516A Item 21 or 1 Washer NSA5368-516B Item 41 DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 33 5

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# @A330 SERVICE BULLETIN
1 Washer NSA5368-616A Item 20 or 1 Washer NSA5368-616B Item 40 NOTE (01): Apply before installation of the fasteners (wet assembly) : Corrosion Inhibiting Brush Consistency 09-013B As required NOTE (02): Apply on the parts : Polyurethane Primer 16-001C As required and Chemical Conversion Coating Yellow Aluminum 13-002 As required
NOTE (03): Apply the on the fasteners inside center tank : Low Density Fuel Tank Sealant 09-002D As required (5) Subtask 573090-420-001-001 - On the LH and RH sides, Install (if removed) the Ducts between FR39.1 and Fr40. Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401 36-12-41, Page Block 401 Fig. A-FHBAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40, for access. Sheet 01
Fig. A-FHAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for access. Sheet 01

(a) Remove the blanking plugs on the disconnected line ends. (b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40 (Refer to AMM 36-12-41 Page Block 401).
DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 34 5

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# @A330 SERVICE BULLETIN (c) On RH side, install (if removed) the air ventilation duct. Refer to Fig. A-FHBAA 1 Install : 1 Duct Item (36) 8 Clamp Item (33) 4 Clamp Item (32) 2 Sleeve Item (34) 1 Sleeve Item (35) NOTE: items (32) thru (36) were retained at removal. (d) On RH side, install (if removed) the air conditioning duct. Refer to Fig. A-FHAAA 1 Install : 1 Duct Item (26) 1 Insulation Item (25) 1 Nut Item (28) 1 Bolt Item (29) 1 Washer Item (30) 2 Screw Item (31) 2 Washer Item (32) 2 Nut Item (33) 1 Clamp Item (34) 1 Clamp Item (27) NOTE (01): Reconnect the rod Items (35) and (36). NOTE (02): For the installation of the sensor 542HH (Refer to AMM 21-53-18 Page Block 401). NOTE (03): Items (25) thru (34) were retained at removal. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 35 5

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# @A330 SERVICE BULLETIN
D. TEST (1) Subtask 573090-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 57-17-11, Page Block 401 (a) Close the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (2) Subtask 573090-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501 21-20-00, Page Block 201 23-53-18, Page Block 401 28-11-00, Page Block 501 36-12-41, Page Block 401 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Do the test after removal/installation of the air conditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201) if removed. (b) Do the test after removal/installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 23-53-18 Page Block 401) if removed. (c) Do a leak check of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page Block 401) if removed. (e) Do the test after removal/installation of the belly fairing access panels (Refer to AMM 53-35-13 Page Block 401). (f) Do the test after removal/installation of the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Do a check of electrical bonding (Refer to AMM 20-28-00 Page Block 501). NOTE: Refer to Table of the Maximum Permitted Resistance Values AMM 20-28-00 Page Block 501.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 36 5

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# @A330 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 573090-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53 21-20-00, Page Block 201 21-53-18, Page Block 401 32-12-00, Page Block 201 36-12-41, Page Block 401 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).(d) Do the close-up procedure as specified in the removal / installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201). (e) Do the close-up procedure as specified in the removal / installation of the pack discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401). (f) Do the close-up procedure as specified in the removal/installation of the APU bleed-air ducts (Refer to AMM 36-12-41 Page Block 401). (g) Remove the access platform(s). (h) Do the close-up procedure as specified in the removal/installation of the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (i) Restore the systems and the aircraft to normal operating condition.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 37 5

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# @A330 SERVICE BULLETIN

**CONF ALL

FR39.2



### B FR40.2

Z192 

### A

**(25)**

**(27) (33)** 
**(31) (32)**  **(36) (34)**  **(35)**

**(33)**
**(31) (32)**  542HH



### (28) **(29) (30)** 

**(26)** 

### A

**B**

G_SB_573090_5_HAAA_01_01 Figure A-FHAAA - Sheet 01 Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for access. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 38 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### B **C D**  Z191−Z192 FR40 FR47



### A **B A** 

**(33) (32) (32)**  **(35) (34) (33)** 



### D **C D** 

**(36)**

G_SB_573090_5_HBAA_01_01 Figure A-FHBAA - Sheet 01 Removal/Installation of the Ventilation Ducts between FR39.1 and FR40, for access. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 39 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

G_SB_573090_5_BAAA_01_00 Figure A-FBAAA - Sheet 01 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 40 5

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# @A330 SERVICE BULLETIN

**CONF ALL

FR40 DATUM Y−1959 

### C VIEW INSIDE CENTER TANK AT FR40

F 

### D **D (7) 7**  **(8) 8 9**  STGR1

SECTION 

### D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK GUSSET

SHIM CWB LOWER PANEL KEEL BEAM 

### (8)

**(7)** FASTENER NOT AFFECTED F HEAD ON HIDDEN SIDE



### BEFORE OR 

### 10 **11 12**  **13** OR 

### 10 **11 12**  **14**

G_SB_573090_5_BAAA_02_00 OR

### 39 OR

### 42 OR

### 42

Figure A-FBAAA - Sheet 02 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 41 5

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# @A330 SERVICE BULLETIN

**CONF ALL

SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

**7 8**  **9**

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm (0.02in x 0.02in.) 1mm THRU 1.2mm MAX. (0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D 1

RADIUS 2mm (0.079in.) DIA 10.177mm THRU 10.219mm (0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm (0.031in x 0.031in.) DIA 21mm THRU 21.2mm (0.827in. THRU 0.835in.) OR

### 39

G_SB_573090_5_BAAA_03_00 Figure A-FBAAA - Sheet 03 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 42 5

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# @A330 SERVICE BULLETIN

**CONF ALL
SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

**7 8**  **9**

1 APPLY MAT. No 09−002D 1

RADIUS 2mm (0.079in.) STEP 1

SHIM CWB LOWER PANEL

KEEL BEAM1mm THRU 1.2mm (0.039in. THRU 0.047in.)
0.5mm THRU 0.7mm (0.02in. THRU 0.028in.) DIA 10.177mm THRU 10.219mm (0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm (0.031in x 0.031in.)

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

DIA 19mm THRU 19.2mm (0.748in. THRU 0.756in.) STEP 2 DIA 21mm THRU 21.2mm (0.827in. THRU 0.835in.)

G_SB_573090_5_BAAA_04_00 OR

### 39

Figure A-FBAAA - Sheet 04 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 43 5

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# @A330 SERVICE BULLETIN

**CONF ALL
SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

1 APPLY MAT. No 09−002D 1

1mm THRU 1.2mm (0.039in. THRU 0.047in.) 0.5mm THRU 0.7mm (0.02in. THRU 0.028in.) 

### 11 **12**

**10** DIA 8.692mm THRU 8.732mm (0.342in. THRU 0.344in.)



### 13

RADIUS 2mm (0.079in.) 1mm THRU 1.2mm (0.039in. THRU 0.047in.) 0.5mm THRU 0.7mm (0.02in. THRU 0.028in.) CHAMFER 0.5mm x 0.5mm (0.02in x 0.02in.)

DIA 11.1mm THRU 11.3mm (0.437in. THRU 0.445in.) DIA 13.1mm THRU 13.12mm

(0.516in. THRU 0.517in.) DIA 19mm THRU 19.2mm (0.748in. THRU 0.756in.) DIA 21mm THRU 21.2mm (0.827in. THRU 0.835in.) STEP 2 STEP 1

STEP 3 STEP 4 OR

### 42

G_SB_573090_5_BAAA_05_01 Figure A-FBAAA - Sheet 05 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 44 5

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# @A330 SERVICE BULLETIN

**CONF ALL

SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

1 APPLY MAT. No 09−002D 1

1mm THRU 1.2mm (0.039in. THRU 0.047in.) 0.5mm THRU 0.7mm (0.02in. THRU 0.028in.) 

### 11 **12**

**10**

1mm THRU 1.2mm (0.039in. THRU 0.047in.) 0.5mm THRU 0.7mm (0.02in. THRU 0.028in.) 

### 14

RADIUS 2mm (0.079in.) DIA 8.692mm THRU 8.732mm (0.342in. THRU 0.344in.)

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

DIA 11.1mm THRU 11.3mm (0.437in. THRU 0.445in.) DIA 13.1mm THRU 13.3mm

(0.516in. THRU 0.524in.) DIA 21mm THRU 21.2mm (0.827in. THRU 0.835in.) DIA 15mm THRU 15.02mm (0.591in. THRU 0.592in.) DIA 23mm THRU 23.2mm (0.906in. THRU 0.913in.) STEP 2 STEP 1
STEP 3 STEP 4 STEP 5 OR

### 42

G_SB_573090_5_BAAA_06_01 Figure A-FBAAA - Sheet 06 Replacement of the Fasteners of the Keel Beam (holes without bushes), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 45 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

G_SB_573090_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 46 5

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# @A330 SERVICE BULLETIN

**CONF ALL

FR40 DATUM Y−1959 

### C VIEW INSIDE CENTER TANK AT FR40

F 

### D **D** STGR1

SECTION 

### D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK GUSSET

SHIM CWB LOWER PANEL KEEL BEAM 

### (8) FASTENER NOT AFFECTED F HEAD ON HIDDEN SIDE



### BEFORE **(7) 7 (8) 8**  **9 (15)** 

**(15) (7)**  DIA 19mm

(0.748in.) G_SB_573090_5_BBAA_02_00 OR

### 39

Figure A-FBBAA - Sheet 02 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 47 5

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# @A330 SERVICE BULLETIN

**CONF ALL SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

**7 8**  **9**

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm (0.02in x 0.02in.) 1mm THRU 1.2mm MAX. (0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D 1

RADIUS 2mm (0.079in.) DIA 10.177mm THRU 10.219mm (0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm (0.031in x 0.031in.) DIA 21mm THRU 21.2mm (0.827in. THRU 0.835in.)

G_SB_573090_5_BBAA_03_00 OR

### 39

Figure A-FBBAA - Sheet 03 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. < or = 19mm (0.748in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 48 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

G_SB_573090_5_BEAA_01_01 Figure A-FBEAA - Sheet 01 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or = 21mm (0.827in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 49 5

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# @A330 SERVICE BULLETIN

**CONF ALL

FR40 DATUM Y−1959 

### C VIEW INSIDE CENTER TANK AT FR40

F 

### D **D** STGR1

SECTION 

### D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK GUSSET

SHIM CWB LOWER PANEL KEEL BEAM 

### (8) FASTENER NOT AFFECTED F HEAD ON HIDDEN SIDE



### BEFORE **(7) 7 (8) 8**  **9 (15)** 

**(15) (7)**  DIA 19mm (0.748in.) 21mm (0.827in.)

G_SB_573090_5_BEAA_02_00 OR

### 39

Figure A-FBEAA - Sheet 02 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or = 21mm (0.827in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 50 5

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# @A330 SERVICE BULLETIN

**CONF ALL
SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

**7 8**  **9**

CWB LOWER PANEL

KEEL BEAM

CHAMFER 0.5mm x 0.5mm (0.02in x 0.02in.) 1mm THRU 1.2mm MAX. (0.039in. THRU 0.047in.) MAX.

1 APPLY MAT. No 09−002D 1

RADIUS 2mm (0.079in.) DIA 10.177mm THRU 10.219mm (0.4in. THRU 0.402in.)

CHAMFER 0.8mm x 0.8mm (0.031in x 0.031in.) DIA 23mm THRU 23.2mm (0.906in. THRU 0.913in.)

G_SB_573090_5_BEAA_03_00 OR

### 39

Figure A-FBEAA - Sheet 03 Replacement of the Fasteners of the Keel Beam (holes with bushes dia. > 19mm (0.748 in.) and < or = 21mm (0.827in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 51 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

G_SB_573090_5_BHAA_01_01 Figure A-FBHAA - Sheet 01 Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 52 5

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# @A330 SERVICE BULLETIN

**CONF ALL

FR40 DATUM Y−1959 

### C VIEW INSIDE CENTER TANK AT FR40

F 

### D **D** STGR1

SECTION 

### D−D

INSIDE CENTER TANK

OUTSIDE CENTER TANK GUSSET

SHIM CWB LOWER PANEL KEEL BEAM FASTENER NOT AFFECTED F HEAD ON HIDDEN SIDE



### BEFORE **(11)**

**(17) (10)** DIA 15mm

(0.591in.) 

### (10) **(11) (17)**  **10 11**  **12 17** 

G_SB_573090_5_BHAA_02_00 OR

### 42

Figure A-FBHAA - Sheet 02 Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 53 5

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# @A330 SERVICE BULLETIN

**CONF ALL SECTION 

### D−D

SHIM CWB LOWER PANEL KEEL BEAM GUSSET 

### AFTER

1 APPLY MAT. No 09−002D 1

1mm THRU 1.2mm (0.039in. THRU 0.047in.) 

### 11 **12**

**10**

1mm THRU 1.2mm (0.039in. THRU 0.047in.) RADIUS 2mm (0.079in.) 

### 17 DIA 8.692mm THRU 8.732mm (0.342in. THRU 0.344in.)

DIA 26mm THRU 26.2mm (1.024in. THRU 1.031in.) DIA 17mm THRU 17.02mm (0.669in. THRU 0.670in.)

G_SB_573090_5_BHAA_03_00 OR

### 42

Figure A-FBHAA - Sheet 03 Replacement of the Fasteners of the Keel Beam (holes with bushes < or = 15mm (0.591in.)), LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 54 5

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# @A330 SERVICE BULLETIN

**CONF ALL



### A Z141−142 

### A FR40 FR47



### B

**B**

FR40 DATUM

STGR1 Y−1959



### C **B**

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

G_SB_573090_5_GAAA_01_01 Figure A-FGAAA - Sheet 01 Replacement of the Fasteners on the FWD lower Panel, LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 55 5

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# @A330 SERVICE BULLETIN

**CONF ALL

Y−1959 

### BEFORE 

### C

HOLE OLD ITEM STGR1 FR40 KEEL BEAM DAT.

FASTENER NOT AFFECTED 

### (19) **(18) (8)**  **(11)**

G_SB_573090_5_GAAA_02_00 Figure A-FGAAA - Sheet 02 Replacement of the Fasteners on the FWD lower Panel, LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 56 5

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# @A330 SERVICE BULLETIN

**CONF ALL 

### C **AFTER**

1 Y−1959

STGR1 FR40 KEEL BEAM DAT.

2
TABLE OF THE EXPANDED HOLES FOR THE NEW FASTENERS. EXISTING HOLE

DIAMETER STDN HOLE

N° 9.12mm 9.19mm 12−0−N 9.823mm (0.386in.) 9.782mm (0.385in.) (0.361in.) (0.359in.) 7.55mm 7.62mm 8.245mm (0.324in.) 8.211mm (0.323in.) (0.3in.) (0.297in.) 10−0−N

NEW ITEM NEW ITEM NUT FASTENER

1
2 HOLE

N° FINAL HOLE DIAMETER STARTING HOLE DIAMETER

= EXPANSION SLEEVE INSTALLATION ORIENTATION SCHEMATIC DIAGRAM FASTENER NOT AFFECTED MAT. No. 09−002 1 1 MIN. MAX. MIN. MAX. MIN. MAX. 7.815mm (0.307in.) 7.849mm (0.309in.) 6.227mm (0.245in.) 6.262mm (0.246in.)

EN6115V6X13 ASNA2531−6 NEW ITEM 

### 22 NSA5368−616A WASHER 

### 19 **20** 1
2

OR EN6115V6X14 OR 

### 49 OR NSA5368−616B OR 

### 40 1 1 EN6115V5X12 ASNA2531−5 

### 23 NSA5368−516A 

### 18 **21** OR EN6115V5X13 OR 

### 48 OR NSA5368−516B OR 

### 41 1

G_SB_573090_5_GAAA_03_01 Figure A-FGAAA - Sheet 03 Replacement of the Fasteners on the FWD lower Panel, LH and RH sides. DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 57 5

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER FUSELAGE - MODIFY FASTENERS IN FR40 KEELBEAM/BOTTOM SKIN PANEL JUNCTION AREA. MODIFICATION No.: 54459S18477 Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments: From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 1 5

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# @A330 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Mar 27/06 SERVICE BULLETIN No.: A330-57-3090 REVISION No.: 01 - Jun 15/11 Page: 1 5

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