# @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



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH MODIFICATION No.: 53222D44560 This page transmits Revision No.03 of Service Bulletin No.A330-53-3160 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 03 issued to update the Flight Cycles (FC) and Flight Hours (FH). 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 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 Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 1 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
APPENDICES Minor editorial or document structure change N Fig. A-GSAAA Minor editorial or document structure change N Fig. A-GSAAA 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 CONF 002 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N 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 Threshold are revised. N Accomplishment Timescale Threshold are revised. 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 Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N 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 Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 2 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
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 533160D01R04 Minor editorial or document structure change N Kit 533160D02R05 Minor editorial or document structure change N Kit 533160D03R01 Minor editorial or document structure change N Kit 533160D04R01 Minor editorial or document structure change N Kit 533160D05R01 Minor editorial or document structure change N Kit 533160D06R01 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 CMLD01 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 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 533160- 831-848-001- MODIFICATION Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Subtask 533160-910-203-001 Minor editorial or document structure change N Subtask 533160-839-201-001 Minor editorial or document structure change N Subtask 533160-910-203-001 Minor editorial or document structure change N Subtask 533160-839-201-001 Minor editorial or document structure change N Subtask 533160-941-201-001 Minor editorial or document structure change N Subtask 533160-941-201-001 Minor editorial or document structure change N Subtask 533160-831-204-001 Minor editorial or document structure change N Subtask 533160-831-205-001 Minor editorial or document structure change N Subtask 533160-831-206-001 Minor editorial or document structure change N Subtask 533160-831-207-001 Minor editorial or document structure change N Subtask 533160-831-208-001 Minor editorial or document structure change N Subtask 533160-831-209-001 Minor editorial or document structure change N Subtask 533160-831-210-001 Minor editorial or document structure change N
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 3 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 533160-831-211-001 Minor editorial or document structure change N Subtask 533160-831-212-001 Minor editorial or document structure change N Subtask 533160-400-201-001 Minor editorial or document structure change N Subtask 533160-400-202-001 Minor editorial or document structure change N Subtask 533160-831-204-002 Minor editorial or document structure change N Subtask 533160-831-205-002 Minor editorial or document structure change N Subtask 533160-831-206-002 Minor editorial or document structure change N Subtask 533160-831-207-002 Minor editorial or document structure change N Subtask 533160-831-208-002 Minor editorial or document structure change N Subtask 533160-831-209-002 Minor editorial or document structure change N Subtask 533160-831-210-002 Minor editorial or document structure change N Subtask 533160-831-211-002 Minor editorial or document structure change N Subtask 533160-831-212-002 Minor editorial or document structure change N Subtask 533160-400-201-002 Minor editorial or document structure change N Subtask 533160-400-202-002 Minor editorial or document structure change N Subtask 533160-831-223-001 Minor editorial or document structure change N Subtask 533160-831-223-001 Minor editorial or document structure change N Fig. A-GBAAA Minor editorial or document structure change N Fig. A-GBAAA Sheet 01 Minor editorial or document structure change N Fig. A-GBAAA Sheet 02 Minor editorial or document structure change N Fig. A-GBAAA Sheet 03 Minor editorial or document structure change N Fig. A-GBAAA Sheet 04 Minor editorial or document structure change N Fig. A-GBAAB Minor editorial or document structure change N Fig. A-GBAAB Sheet 01 Minor editorial or document structure change N Fig. A-GBAAB Sheet 02 Minor editorial or document structure change N Fig. A-GBAAB Sheet 03 Minor editorial or document structure change N Fig. A-GBAAB Sheet 04 Minor editorial or document structure change N Fig. A-GBBAA Minor editorial or document structure change N Fig. A-GBBAA Sheet 01 Minor editorial or document structure change N Fig. A-GBBAA Sheet 02 Minor editorial or document structure change N Fig. A-GBBAA Sheet 03 Minor editorial or document structure change N Fig. A-GBBAA Sheet 04 Minor editorial or document structure change N Fig. A-GBBAA Sheet 05 Minor editorial or document structure change N Fig. A-GBBAA Sheet 06 Minor editorial or document structure change N Fig. A-GBBAA Sheet 07 Minor editorial or document structure change N Fig. A-GBBAA Sheet 08 Minor editorial or document structure change N Fig. A-GBBAA Sheet 09 Minor editorial or document structure change N Fig. A-GBBAA Sheet 10 Minor editorial or document structure change N Fig. A-GBBAA Sheet 11 Minor editorial or document structure change N Fig. A-GBBAA Sheet 12 Minor editorial or document structure change N Fig. A-GBBAA Sheet 13 Minor editorial or document structure change N DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 4 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-GBBAA Sheet 14 Minor editorial or document structure change N Fig. A-GBBAA Sheet 15 Minor editorial or document structure change N Fig. A-GBBAB Minor editorial or document structure change N Fig. A-GBBAB Sheet 01 Minor editorial or document structure change N Fig. A-GBBAB Sheet 02 Minor editorial or document structure change N Fig. A-GBBAB Sheet 03 Minor editorial or document structure change N Fig. A-GBBAB Sheet 04 Minor editorial or document structure change N Fig. A-GBBAB Sheet 05 Minor editorial or document structure change N Fig. A-GBBAB Sheet 06 Minor editorial or document structure change N Fig. A-GBBAB Sheet 07 Minor editorial or document structure change N Fig. A-GBBAB Sheet 08 Minor editorial or document structure change N Fig. A-GBBAB Sheet 09 Minor editorial or document structure change N Fig. A-GBBAB Sheet 10 Minor editorial or document structure change N Fig. A-GBBAB Sheet 11 Minor editorial or document structure change N Fig. A-GBBAB Sheet 12 Minor editorial or document structure change N Fig. A-GBBAB Sheet 13 Minor editorial or document structure change N Fig. A-GBBAB Sheet 14 Minor editorial or document structure change N Fig. A-GBBAB Sheet 15 Minor editorial or document structure change N Fig. A-GBCAA Minor editorial or document structure change N Fig. A-GBCAA Sheet 01 Minor editorial or document structure change N Fig. A-GBCAA Sheet 02 Minor editorial or document structure change N Fig. A-GBCAA Sheet 03 Minor editorial or document structure change N Fig. A-GBCAA Sheet 04 Minor editorial or document structure change N Fig. A-GBCAA Sheet 05 Minor editorial or document structure change N Fig. A-GBCAA Sheet 06 Minor editorial or document structure change N Fig. A-GBCAA Sheet 07 Minor editorial or document structure change N Fig. A-GBCAA Sheet 08 Minor editorial or document structure change N Fig. A-GBCAA Sheet 09 Minor editorial or document structure change N Fig. A-GBCAA Sheet 10 Minor editorial or document structure change N Fig. A-GBDAA Minor editorial or document structure change N Fig. A-GBDAA Sheet 01 Minor editorial or document structure change N Fig. A-GBDAA Sheet 02 Minor editorial or document structure change N Fig. A-GBDAA Sheet 03 Minor editorial or document structure change N Fig. A-GBDAA Sheet 04 Minor editorial or document structure change N Fig. A-GBDAA Sheet 05 Minor editorial or document structure change N Fig. A-GBEAA Minor editorial or document structure change N Fig. A-GBEAA Sheet 01 Minor editorial or document structure change N Fig. A-GBEAA Sheet 02 Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 5 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS This Service Bulletin was updated with rev. 01 to include all new information from the validation on the A330 MSN 229. Revision No. 02 This Service Bulletin has been updated to correct the quantity of the fastener, item 19 and item 20 for configuration 02. REVISION SEQUENCE ORIGINAL: Jul 09/07 REVISION No.: 02 - Mar 29/10 REVISION No. : 03 - Jan 06/12

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 6 6

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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. 

# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 53222D44560 NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During long life structure tests on the A340-600, damage was found in the upper shell structure between FR84 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no action is required. Nevertheless, due to the higher DSG of 33000 FC / 40000 FC and different design (e.g. skin thickness) for A330-200 aircraft, this damage is considered relevant for these models. Structure improvements have to be embodied. This Service Bulletin has been validated on A330 aircraft MSN 0229. A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS World, Maintenance and Engineering, Service Bulletin Information. This Service Bulletin has been issued to inform the operator to improve the upper shell structure between FR84 and FR87 as follows :
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 1 6

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# @A330 SERVICE BULLETIN SUMMARY - removal/installation of the vertical stabilizer for access reason. - do a rototest inspection of fastener holes and a eddy current high frequency inspection between the fastener rows in the upper shell area of FR80, FR84 and FR86. - install new reinforcement T-doublers on the upper shell fuselage skin in the area of FR84 and FR86 between STGR5A LH and STGR5A RH, - do a cold working with interference fit at FR80, FR84, FR85 and FR86, - replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4 LH/RH, - install a system angle between FR85 and FR86 and between STGR2 and STGR3 LH/RH. - replace a system angle between FR83 and FR84, at STGR3 LH/RH. The accomplishment of this Service Bulletin will ensure the structural integrity of the upper shell structure between FR84 to FR87 up the DSG of 40000 FC for A330-200 aircraft. This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft delivery configuration and modified by the reported incorporation of Airbus SBs). Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. Airbus disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by Airbus, the operator should contact Airbus Customer Services Repair Engineering Support (SER1). Repair review will be done by Airbus at conditions of the Customer Services Catalogue. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 533160D01R04 1 14,240.00 Attachment Parts, Reinforcement Part
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 2 6

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# @A330 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 533160D02R05 1 9,270.00 Attachment Parts Kit 533160D03R01 1 4,030.00 Attachment Parts TOTAL 27,540.00 **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 533160D04R01 1 14,990.00 Attachment Parts, Reinforcement Part Kit 533160D05R01 1 9,310.00 Attachment Parts Kit 533160D06R01 1 4,060.00 Attachment Parts TOTAL 28,360.00 EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

ACI AEA AFR ALK AZA BER BMA BTV CRL CSN CYP DAH DAL DGA EDW EIN ETD EVA FWI GFA GRL HVN I2L IAC ISS IYE JST KAL KKK MAS MON MSR QAF QTR STZ SWR TAM TAP TCX THY TSC UAE VKG VOZ XLF CONCURRENT REQUIREMENTS Due to the access requirements, AIRBUS recommends the simultaneous accomplishment of: Service Bulletin No. A330-53-3152 Mod. No. 53222D44902 A330-53-3157 54622D46095 NOTE: Service Bulletin A330-53-3152 is applicable for MSN 0205 thru 0667. NOTE: Service Bulletin A330-53-3157 is applicable for MSN 0181 and 0195. REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT Yes OTHERS OIT SE999.0124/06

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 3 6

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# @A330 SERVICE BULLETIN SUMMARY NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 533160-831-848-001: MODIFICATION TOTAL MANHOURS 190.50 ELAPSED TIME (HOURS) 97.50 **CONF 002 Task 533160-831-848-001: MODIFICATION TOTAL MANHOURS 192.50 ELAPSED TIME (HOURS) 99.50 APPENDICES **CONF ALL None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 4 6

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# @A330 SERVICE BULLETIN SUMMARY
**CONF ALL Z310



## A AD REPAIR AREA Z270 

### A

G_SB_533160_6_SAAA_01_00 STGR8

STGR8 FR91

FR87

FR79

Figure A-GSAAA - Sheet 01

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 5 6

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# @A330 SERVICE BULLETIN SUMMARY

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DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 6 6

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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



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH MODIFICATION No.: 53222D44560 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This Service Bulletin is applicable for A330-200 aircraft on which MOD 44205D40465 has already been embodied, and MOD 52974D44611 and MOD 53223D44586 have NOT been embodied in production. (1) Models 330-202 330-203 330-223 330-243 (2) Effectivity by MSN 0181 0195 0205 0211 0222-0223 0226 0229-0230 0232 0238 0240 0247-0251 0253-0255 0258-0259 0261-0262 0265-0266 0269 0271-0272 0275-0276 0281 0283 0285-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0314 0316-0317 0320 0322 0324 0326 0328 0330 0334 0339-0340 0343 0345 0348 0353 0358 0361-0362 0364-0366 0369 0372 0382 0384 0392 0396-0398 0401 0403-0404 0409 0422 0427 0432 0437 0441 0443-0444 0448 0451-0452 0454-0456 0458 0461-0463 0465-0466 0469 0472-0473 0476-0477 0480-0481 0486-0487 0489 0491 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 1 6

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# @A330 SERVICE BULLETIN
0493-0494 0498 0500-0511 0513 0516 0518-0519 0521-0522 0525-0527 0529-0530 0532 0535-0536 0551 0555 0567 0571 0573 0584 0587 0597 0600 0605 0609-0610 0612 0614 0616 0618 0620-0621 0625 0627 0631-0635 0638 0644 0647 0649-0650 0652-0653 0655-0658 0661 0664-0667 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN ACI 0507 0510 AEA 0461 0597 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519 0567 0584 0657 ALK 0303 0306 0311 0313 0404 AZA 0272 0339 BER 0403 0432 0444 0454 0469 0476 0493 BMA 0398 0401 BTV 0205 0330 CRL 0285 0320 CSN 0649 0652 0656 0664 CYP 0505 0526 DAH 0644 0647 0650 0653 0667 DAL 0609 0614 0618 0620 0621 0631 0633 DGA 0240 EDW 0291 EIN 0269 0397 ETD 0658 EVA 0530 0535 0555 0573 0587 0634 0655 0661 FWI 0253 GFA 0276 0281 0286 0287 0334 0340 0527 0529 0532 GRL 0230 HVN 0255 0262 0275 0294 0299 0366 I2L 0211 0551 IAC 0353 0362 ISS 0665 IYE 0625 0627 0632 JST 0506 0508 0513 0522 KAL 0222 0226 0258 KKK 0343 0358 0364 MAS 0290 0296 0300 MON 0261 0265 MSR 0600 0610 0666 QAF 0487 0605 QTR 0441 0473 0489 0511 0521 0571 0612 0616 0638
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 2 6

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# @A330 SERVICE BULLETIN
OPERATOR MSN STZ 0324 SWR 0229 0249 0288 0322 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 TAP 0181 0195 0223 0305 0308 0312 0317 TCX 0254 0266 0301 0427 0456 THY 0463 0504 TSC 0250 0271 0369 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0382 0384 0392 0396 0409 0437 0451 0452 0455 0462 0491 0494 0509 0518 0525 0536 VKG 0309 VOZ 0365 0372 XLF 0501 0635 (4) Configuration by MSN MSN CONFIGURATION 0181 0195 0205 0211 0222 0223 0226 0229 0230 0232 0238 0240 0247 0248 0249 0250 0251 0253 0254 0255 0258 0259 0261 0262 0265 0266 0269 0271 0272 0275 0276 0281 0283 0285 0286 0287 0288 0290 0291 0293 0294 0295 0296 0299 0300 0301 0303 0305 0306 0308 0309 0311 0312 0313 0314 0316 0317 0320 0322 0324 0326 0328 0330 0334 0339 0340 0343 0345 0348 0353 0358 0361 0362 0364 0365 0366 0369 0372 0382 0384 0392 0396 0397 0398 0401 0403 0404 0409 0422 0427 0432 0437 0441 0443 0444 0448 0451 0452 0454 0455 0456 0458 0461 0462 0463 0465 0466 0469 0472 0473 0476 0477 0480 0481 0486 0487 0489 0491 0493 0494 0498 0500 0501 0502 0503 0504 0505 0506 0507 0508 0509 0510 0511 0513 0516 0518 0519 0521 0522 0525 0526 0527 0529 0530 0532 0535 0536 0551 0567 0584 0597 0627 0635 0657 001

0555 0571 0573 0587 0600 0605 0609 0610 0612 0614 0616 0618 0620 0621 0625 0631 0632 0633 0634 0638 0644 0647 0649 0650 0652 0653 0655 0656 0658 0661 0664 0665 0666 0667 002

(5) Configuration definition **CONF 001 Config. 001 is applicable to aircraft that have weight variant (WV) 20 thru WV 29. **CONF 002 Config. 002 is applicable to aircraft which have weight variant (WV) 50 thru VW 55. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 533160D01R04 1 (1) DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 3 6

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# @A330 SERVICE BULLETIN
MATERIAL QTY PER A/C SEE NOTES Kit 533160D02R05 1 (2) Kit 533160D03R01 1 (3) Consumable CMLD01 1 NOTE (1) : Kit 533160D01 should be used for the standard fastener installation. NOTE (2) : Kit 533160D02 should be used for the installation of the first oversize fasteners, if the fasteners of kit 533160D01 do not fit. NOTE (3) : Kit 533160D03 should be used for the installation of smaller fastener, if the fastener edge clearance of the standard fastener installation of kit 533160D01 does not match the minimum distance. **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 533160D04R01 1 (1) Kit 533160D05R01 1 (2) Kit 533160D06R01 1 (3) Consumable CMLD01 1 NOTE (1) : Kit 533160D04 should be used for the standard fastener installation. NOTE (2) : Kit 533160D05 should be used for the installation of the first oversize fasteners, if the fasteners of kit 533160D04 do not fit. NOTE (3) : Kit 533160D06 should be used for the installation of smaller fastener, if the fastener edge clearance of the standard fastener installation of kit 533160D04 does not match the minimum distance. **CONF ALL B. CONCURRENT REQUIREMENTS Due to the access requirements, AIRBUS recommends the simultaneous accomplishment of: Service Bulletin No. A330-53-3152 Mod. No. 53222D44902 A330-53-3157 54622D46095 NOTE: Service Bulletin A330-53-3152 is applicable for MSN 0205 thru 0667. NOTE: Service Bulletin A330-53-3157 is applicable for MSN 0181 and 0195. C. REASON (1) History During long life structure tests on the A340-600, damage was found in the upper shell structure between FR84 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no action is required. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 4 6

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# @A330 SERVICE BULLETIN Nevertheless, due to the higher DSG of 33000 FC / 40000 FC and different design (e.g. skin thickness) for A330-200 aircraft, this damage is considered relevant for these models. Structure improvements have to be embodied. This Service Bulletin has been validated on A330 aircraft MSN 0229. A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS World, Maintenance and Engineering, Service Bulletin Information. (2) Objective/Action This Service Bulletin has been issued to inform the operator to improve the upper shell structure between FR84 and FR87 as follows : - removal/installation of the vertical stabilizer for access reason. - do a rototest inspection of fastener holes and a eddy current high frequency inspection between the fastener rows in the upper shell area of FR80, FR84 and FR86. - install new reinforcement T-doublers on the upper shell fuselage skin in the area of FR84 and FR86 between STGR5A LH and STGR5A RH, - do a cold working with interference fit at FR80, FR84, FR85 and FR86, - replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4 LH/RH, - install a system angle between FR85 and FR86 and between STGR2 and STGR3 LH/RH. - replace a system angle between FR83 and FR84, at STGR3 LH/RH. (3) Advantages The accomplishment of this Service Bulletin will ensure the structural integrity of the upper shell structure between FR84 to FR87 up the DSG of 40000 FC for A330-200 aircraft.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 5 6

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# @A330 SERVICE BULLETIN (4) Operational/Maintenance Consequences This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft delivery configuration and modified by the reported incorporation of Airbus SBs). Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. Airbus disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by Airbus, the operator should contact Airbus Customer Services Repair Engineering Support (SER1). Repair review will be done by Airbus at conditions of the Customer Services Catalogue. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 533160-831-848-001: MODIFICATION (1) Remove the fasteners in the upper fuselage shell between FR80 and FR87. (2) Do the Eddy Current Rotating Probe Testing FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. (3) Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. (4) Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. (5) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. (6) Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. (7) Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. (8) Install fasteners with cold working in the upper fuselage skin at FR85 (9) Apply surface protection to the modification area. (10) Installation of undersize fasteners of kit 533160D03R01 (11) Oversize fasteners of kit 533160D02R01
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 6 6

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# @A330 SERVICE BULLETIN
**CONF 002 Task 533160-831-848-001: MODIFICATION (1) Remove the fasteners in the upper fuselage shell between FR80 and FR87. (2) Do the Eddy Current Rotating Probe Testing of FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. (3) Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. (4) Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. (5) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. (6) Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. (7) Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. (8) Install fasteners with cold working in the upper fuselage skin at FR85 (9) Apply surface protection to the modification area. (10) Installation of undersize fasteners of kit 533160D06R01 (11) Oversize fasteners of kit 533160D05R01 **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 7 6

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# @A330 SERVICE BULLETIN (2) Accomplishment Timescale **CONF 001 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to trade of between FC/FH to better suit fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used any type of utilization, for 1st inspection and repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold/interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary as a consequence, the selection of SR or LR threshold and subsequent intervals can be change whenever. Threshold and Interval are whichever occurs first between FC and FH for selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). NOTE: The Service Bulletin must be performed at whichever limit (FC or FH) occurs first. Type Threshold SR Threshold LR Threshold 12900 FC or 45300 FH 9600 FC or 62600 FH NOTE: A grace period of 20 months from Service Bulletin revision 03 issuance is allowed but without exceeding 13500 FC. **CONF 002 Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to trade of between FC/FH to better suit fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used any type of utilization, for 1st inspection and repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold/interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary as a consequence, the selection of SR or LR threshold and subsequent intervals can be change whenever. Threshold and Interval are whichever occurs first between FC and FH for selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). NOTE: The Service Bulletin must be performed at whichever limit (FC or FH) occurs first. Type Threshold SR Threshold LR Threshold 9800 FC or 34500 FH 7300 FC or 47600 FH NOTE: A grace period of 20 months from Service Bulletin revision 03 issuance is allowed but without exceeding 10700 FC or 59300 FH, whichever DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 8 6

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# @A330 SERVICE BULLETIN
occurs first. **CONF ALL F. APPROVAL The technical content of this Service Bulletin is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 533160-831-848-001: MODIFICATION Get Access 48.00 On Aircraft Remove the fasteners in the upper fuselage shell between FR80 and FR87. 2.25 Do the Eddy Current Rotating Probe Testing FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. 3.00 Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. 2.50 Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. 1.50 Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. 2.00
Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. 35.00 Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. 33.50 Install fasteners with cold working in the upper fuselage skin at FR85 2.25 Apply surface protection to the modification area. 1.50 Installation of undersize fasteners of kit 533160D03R01 0.00 Oversize fasteners of kit 533160D02R01 0.00 Tests 9.00 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 9 6

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# @A330 SERVICE BULLETIN
Task 533160-831-848-001: MODIFICATION Close-Up 50.00 TOTAL MANHOURS 190.50 ELAPSED TIME (HOURS) 97.50 **CONF 002 Task 533160-831-848-001: MODIFICATION Get Access 48.00 On Aircraft Remove the fasteners in the upper fuselage shell between FR80 and FR87. 2.25 Do the Eddy Current Rotating Probe Testing of FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. 3.00 Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. 2.50 Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. 1.50 Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. 1.50
Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. 38.00 Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. 33.00 Install fasteners with cold working in the upper fuselage skin at FR85 2.25 Apply surface protection to the modification area. 1.50 Installation of undersize fasteners of kit 533160D06R01 0.00 Oversize fasteners of kit 533160D05R01 0.00 Tests 9.00 Close-Up 50.00 TOTAL MANHOURS 192.50 ELAPSED TIME (HOURS) 99.50 **CONF ALL H. WEIGHT AND BALANCE **CONF 001 Manufacturers Empty Weight +5.81 KG (+12.8087 LB) Effect on Balance +330.54 KGM (+2390.795 LB.FT )

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 10 6

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# @A330 SERVICE BULLETIN
**CONF 002 Manufacturers Empty Weight +6.56 KG (+14.46 LB) Effect on Balance +373.58 KGM (+2702.10 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29 12-34-24 20-28-00 25-33-48 25-33-52 25-33-53 25-33-54 27-51-18 29-00-00 29-14-00 36-12-14 36-12-41 36-22-17 51-31-11 52-10-00 55-31-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11 51-43-00 51-44-11 51-46-11 51-46-12 51-47-00 51-48-00 **CONF 002 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29 12-34-24 20-28-00 25-33-48 25-33-52 25-33-53 25-33-54 27-51-18 29-00-00 29-14-00 36-12-14 36-12-41 36-22-17 51-31-11 52-10-00 55-31-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11 51-43-00 51-44-11 51-46-11 51-46-12 51-47-00 51-48-00 **CONF ALL K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 53-51-11
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 11 6

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# @A330 SERVICE BULLETIN
L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 12 6

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 533160D01R04 Kit 533160D02R05 Kit 533160D03R01 Kit 533160D04R01 Kit 533160D05R01 Kit 533160D06R01 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, Logistic and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http//spares.airbus.com For ordering by fax: +49 40 50 76 25 90 For ordering by E-mail: airbus.kit@airbus.com Operators interested in obtaining the FTI tool kits should contact: Fatigue Technology Inc. 401 ANDOVER PARK EAST SEATTLE, WA 98188-7605 USA E-Mail: www.fatiguetech.com Phone: +(1) 206 2462010 Fax: +(1) 206 2449886 (2) Price and Availability

Kit 533160D01R04 Cost 14,240.00 USD Availability 90 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 533160D02R05 Cost 9,270.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 13 6

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# @A330 SERVICE BULLETIN The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 533160D03R01 Cost 4,030.00 USD Availability 90 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 533160D04R01 Cost 14,990.00 USD Availability 90 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 533160D05R01 Cost 9,310.00 USD Availability 90 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 533160D06R01 Cost 4,060.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 14 6

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# @A330 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 533160D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 F5357716920000 1 DOUBLER 2 F5357716920100 1 DOUBLER 3 F5357716920200 1 DOUBLER 4 F5357716920300 1 DOUBLER 5 F5357798920000 1 SHIM 6 F5357798920100 1 SHIM 7 F5357798920200 1 SHIM 8 F5357798920300 1 SHIM 9 A5398525620600 1 ANGLE 10 F5357716921800 1 DOUBLER 11 F5357716921900 1 DOUBLER 12 F5357716922100 1 DOUBLER 13 F5357716922000 1 DOUBLER 14 F5357798921200 1 SHIM 15 F5357798921400 1 SHIM 16 F5357798921700 1 SHIM 17 F5357798921600 1 SHIM 18 DAN5-5-4 2 PIN 19 DAN5-6-3 14 PIN 20 DAN5-6-4 2 PIN 21 DAN5-6-5 10 PIN 22 DAN5-6-6 20 PIN 23 DAN5-6-7 8 PIN 24 DAN5-6-8 16 PIN 25 DAN5-6-10 8 PIN 26 DAN7-8-9 4 PIN 27 DAN7-8-10 4 PIN 28 DAN7-8-11 12 PIN 29 DAN7-10-11 8 PIN 30 DAN7-10-12 6 PIN 31 DAN7-10-17 4 PIN 32 DAN5-6-7X 4 PIN 33 DAN5-6-10X 4 PIN 34 DAN7-6-11Y 2 PIN 35 DAN7-8-13Y 6 PIN 36 DAN7-8-15Y 6 PIN 37 DAN7-8-16Y 6 PIN 38 EN6115K4Y7 20 BOLT 39 EN6115K4Y8 6 BOLT 40 EN6115K4Y10 8 BOLT 41 EN6115K4Y11 8 BOLT 42 EN6115K4Y12 14 BOLT
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 15 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 43 EN6115K4Y15 2 BOLT 44 EN6115K4Y16 2 BOLT 45 NSA5075-5 2 COLLAR 46 NSA5075-6 78 COLLAR 47 DAN12-6Y 2 COLLAR 48 DAN12-8 20 COLLAR 49 DAN12-10 18 COLLAR 50 ASNA2528-3 60 NUT 51 ASNA2528-4 54 NUT 52 ASNA2528-5 40 NUT 53 NSA5330-6 6 COLLAR 54 DAN12-8Y 72 COLLAR 55 DAN12-8X 2 COLLAR 56 DAN11-6X 8 COLLAR 57 DAN5-6-7Y 2 PIN 58 DAN5-6-8Y 4 PIN 59 DAN7-8-12X 2 PIN 60 DAN7-8-10Y 20 PIN 61 DAN7-8-11Y 20 PIN 62 DAN7-8-12Y 14 PIN 63 EN6115K3-3 10 BOLT 64 EN6115K3-4 10 BOLT 65 EN6115K3-5 22 BOLT 66 EN6115K3-7 10 BOLT 67 EN6115K3-8 8 BOLT 68 EN6115K5-10 8 BOLT 69 EN6115K5-11 8 BOLT 70 EN6115K5-12 8 BOLT 71 EN6115K5-17 8 BOLT 72 EN6115K5-19 8 BOLT 73 LN9198-4012CF 1 RIVET 74 LN9198-4014CF 1 RIVET 75 EN6080D5-06 1 RIVET 76 LN9198-4812CF 2 RIVET 77 LN9198-4814CF 8 RIVET 124 EN6115K3A7 2 BOLT 125 EN6115K3A8 2 BOLT 126 ASNA2528-3A 4 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 16 6

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# @A330 SERVICE BULLETIN
Kit 533160D02R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 20 DAN5-6-4 2 PIN 28 DAN7-8-11 PIN 29 DAN7-10-11 5 PIN 30 DAN7-10-12 5 PIN 32 DAN5-6-7X 5 PIN 33 DAN5-6-10X 5 PIN 46 NSA5075-6 2 COLLAR 48 DAN12-8 2 COLLAR 49 DAN12-10 5 COLLAR 50 ASNA2528-3 5 NUT 51 ASNA2528-4 4 NUT 52 ASNA2528-5 6 NUT 53 NSA5330-6 5 COLLAR 54 DAN12-8Y 2 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 57 DAN5-6-7Y 4 PIN 62 DAN7-8-12Y 2 PIN 68 EN6115K5-10 5 BOLT 69 EN6115K5-11 5 BOLT 70 EN6115K5-12 5 BOLT 78 DAN5-6-3X 5 PIN 79 DAN5-6-4X 2 PIN 80 DAN5-6-5X 5 PIN 81 DAN5-6-6X 5 PIN 82 DAN5-6-8X 5 PIN 83 DAN7-8-9X 4 PIN 84 DAN7-8-10X 4 PIN 85 DAN7-8-11X 5 PIN 86 DAN7-10-11X 5 PIN 87 DAN7-10-12X 5 PIN 88 DAN7-10-17X 4 PIN 89 DAN5-6-10Y 4 PIN 90 DAN7-10-13 5 PIN 91 DAN7-10-15 5 PIN 92 DAN7-10-16 5 PIN 93 EN6115K5-7 5 BOLT 94 EN6115K5-8 6 BOLT 95 EN6115K5-15 2 BOLT 96 EN6115K5-16 2 BOLT 97 DAN12-10X 5 COLLAR 98 NSA5075-8 5 COLLAR 99 DAN5-8-7 2 PIN 100 DAN5-8-8 4 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 17 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 101 DAN7-10-10 5 PIN 102 EN6115K3X3 5 BOLT 103 EN6115K3X4 5 BOLT 104 EN6115K3X5 5 BOLT 105 EN6115K4-7 2 BOLT 106 EN6115K3X7 5 BOLT 107 EN6115K3X8 5 BOLT 108 EN6115K4-8 2 BOLT 109 EN6115K5X10 5 BOLT 110 EN6115K5X11 5 BOLT 111 EN6115K5X12 5 BOLT 112 EN6115K5X17 5 BOLT 113 EN6115K5X19 5 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. Kit 533160D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 32 DAN5-6-7X 2 PIN 34 DAN7-6-11Y 5 PIN 40 EN6115K4Y10 5 BOLT 41 EN6115K4Y11 5 BOLT 42 EN6115K4Y12 5 BOLT 47 DAN12-6Y 5 COLLAR 51 ASNA2528-4 5 NUT 54 DAN12-8Y 5 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 59 DAN7-8-12X 5 PIN 61 DAN7-8-11Y 5 PIN 62 DAN7-8-12Y 5 PIN 82 DAN5-6-8X 4 PIN 84 DAN7-8-10X 5 PIN 85 DAN7-8-11X 5 PIN 114 DAN7-6-9Y 4 PIN 115 DAN7-6-10Y 2 PIN 116 DAN7-8-17Y 4 PIN 117 DAN7-6-11X 2 PIN 118 DAN7-8-13X 5 PIN 119 DAN7-8-15X 5 PIN 120 DAN7-8-16X 5 PIN 121 DAN12-6X 2 COLLAR DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 18 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 122 EN6115K4Y17 5 BOLT 123 EN6115K4Y19 5 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. Kit 533160D04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 F5357716920000 1 DOUBLER 2 F5357716920100 1 DOUBLER 3 F5357716920400 1 DOUBLER 4 F5357716920500 1 DOUBLER 5 F5357798920400 1 SHIM 6 F5357798920500 1 SHIM 7 F5357798920600 1 SHIM 8 F5357798920700 1 SHIM 9 A5398525620600 1 ANGLE 10 F5357716921800 1 DOUBLER 11 F5357716921900 1 DOUBLER 12 F5357716922100 1 DOUBLER 13 F5357716922000 1 DOUBLER 14 F5357798921200 1 SHIM 15 F5357798921400 1 SHIM 16 F5357798921700 1 SHIM 17 F5357798921600 1 SHIM 18 DAN5-5-4 2 PIN 19 DAN5-6-3 12 PIN 20 DAN5-6-4 6 PIN 21 DAN5-6-5 12 PIN 22 DAN5-6-6 22 PIN 23 DAN5-6-7 8 PIN 24 DAN5-6-8 16 PIN 25 DAN5-6-10 8 PIN 26 DAN7-8-9 8 PIN 27 DAN7-8-10 4 PIN 28 DAN7-8-11 14 PIN 29 DAN7-10-11 8 PIN 30 DAN7-10-12 6 PIN 31 DAN7-10-17 4 PIN 32 DAN5-6-7X 4 PIN 33 DAN5-6-10X 4 PIN 34 DAN7-6-11Y 2 PIN 35 DAN7-8-13Y 6 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 19 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 36 DAN7-8-15Y 6 PIN 37 DAN7-8-16Y 6 PIN 38 EN6115K4Y7 20 BOLT 39 EN6115K4Y8 6 BOLT 40 EN6115K4Y10 8 BOLT 41 EN6115K4Y11 8 BOLT 42 EN6115K4Y12 14 BOLT 43 EN6115K4Y15 2 BOLT 44 EN6115K4Y16 2 BOLT 45 NSA5075-5 2 COLLAR 46 NSA5075-6 84 COLLAR 47 DAN12-6Y 2 COLLAR 48 DAN12-8 24 COLLAR 49 DAN12-10 18 COLLAR 50 ASNA2528-3 66 NUT 51 ASNA2528-4 60 NUT 52 ASNA2528-5 40 NUT 53 NSA5330-6 6 COLLAR 54 DAN12-8Y 72 COLLAR 55 DAN12-8X 2 COLLAR 56 DAN11-6X 8 COLLAR 57 DAN5-6-7Y 2 PIN 58 DAN5-6-8Y 4 PIN 59 DAN7-8-12X 2 PIN 60 DAN7-8-10Y 20 PIN 61 DAN7-8-11Y 20 PIN 62 DAN7-8-12Y 14 PIN 63 EN6115K3-3 12 BOLT 64 EN6115K3-4 14 BOLT 65 EN6115K3-5 22 BOLT 66 EN6115K3-7 10 BOLT 67 EN6115K3-8 8 BOLT 68 EN6115K5-10 8 BOLT 69 EN6115K5-11 8 BOLT 70 EN6115K5-12 8 BOLT 71 EN6115K5-17 8 BOLT 72 EN6115K5-19 8 BOLT 73 LN9198-4012CF 1 RIVET 74 LN9198-4014CF 1 RIVET 75 EN6080D5-06 1 RIVET 76 LN9198-4812CF 2 RIVET 77 EN6081D6-08 6 RIVET 124 EN6115K3A7 2 BOLT 125 EN6115K3A8 2 BOLT 126 ASNA2528-3A 4 NUT
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 20 6

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# @A330 SERVICE BULLETIN
NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 533160D05R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 20 DAN5-6-4 2 PIN 28 DAN7-8-11 2 PIN 29 DAN7-10-11 5 PIN 30 DAN7-10-12 5 PIN 32 DAN5-6-7X 5 PIN 33 DAN5-6-10X 5 PIN 46 NSA5075-6 2 COLLAR 48 DAN12-8 2 COLLAR 49 DAN12-10 5 COLLAR 50 ASNA2528-3 5 NUT 51 ASNA2528-4 4 NUT 52 ASNA2528-5 10 NUT 53 NSA5330-6 5 COLLAR 54 DAN12-8Y 2 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 57 DAN5-6-7Y 4 PIN 62 DAN7-8-12Y 2 PIN 68 EN6115K5-10 5 BOLT 69 EN6115K5-11 5 BOLT 70 EN6115K5-12 5 BOLT 78 DAN5-6-3X 5 PIN 79 DAN5-6-4X 4 PIN 80 DAN5-6-5X 5 PIN 81 DAN5-6-6X 5 PIN 82 DAN5-6-8X 5 PIN 83 DAN7-8-9X 5 PIN 84 DAN7-8-10X 4 PIN 85 DAN7-8-11X 5 PIN 86 DAN7-10-11X 5 PIN 87 DAN7-10-12X 5 PIN 88 DAN7-10-17X 4 PIN 89 DAN5-6-10Y 4 PIN 90 DAN7-10-13 5 PIN 91 DAN7-10-15 5 PIN 92 DAN7-10-16 5 PIN 93 EN6115K5-7 5 BOLT 94 EN6115K5-8 6 BOLT 95 EN6115K5-15 2 BOLT 96 EN6115K5-16 2 BOLT DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 21 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 97 DAN12-10X 5 COLLAR 98 NSA5075-8 5 COLLAR 99 DAN5-8-7 2 PIN 100 DAN5-8-8 4 PIN 101 DAN7-10-10 5 PIN 102 EN6115K3X3 5 BOLT 103 EN6115K3X4 5 BOLT 104 EN6115K3X5 5 BOLT 105 EN6115K4-7 2 BOLT 106 EN6115K3X7 5 BOLT 107 EN6115K3X8 5 BOLT 108 EN6115K4-8 2 BOLT 109 EN6115K5X10 5 BOLT 110 EN6115K5X11 5 BOLT 111 EN6115K5X12 5 BOLT 112 EN6115K5X17 5 BOLT 113 EN6115K5X19 5 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. Kit 533160D06R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 32 DAN5-6-7X 2 PIN 34 DAN7-6-11Y 5 PIN 40 EN6115K4Y10 5 BOLT 41 EN6115K4Y11 5 BOLT 42 EN6115K4Y12 5 BOLT 47 DAN12-6Y 5 COLLAR 51 ASNA2528-4 5 NUT 54 DAN12-8Y 5 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 4 COLLAR 59 DAN7-8-12X 5 PIN 61 DAN7-8-11Y 5 PIN 62 DAN7-8-12Y 5 PIN 82 DAN5-6-8X 4 PIN 84 DAN7-8-10X 5 PIN 85 DAN7-8-11X 5 PIN 114 DAN7-6-9Y 5 PIN 115 DAN7-6-10Y 2 PIN 116 DAN7-8-17Y 4 PIN 117 DAN7-6-11X 2 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 22 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 118 DAN7-8-13X 5 PIN 119 DAN7-8-15X 5 PIN 120 DAN7-8-16X 5 PIN 121 DAN12-6X 2 COLLAR 122 EN6115K4Y17 5 BOLT 123 EN6115K4Y19 5 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 CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required sealant 09-013 As required sealant 09-016 As required cleaning agent 11-026 As required corrosion preventive 15-005 As required polyurethane primer 16-001 As required polyurethane top coat 16-018 As required wash primer 16-020 As required lint-free cloth 19-003 As required (2) Components To accomplish this Service Bulletin, it is necessary to use parts and tools listed in AMM 51-31-11. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 23 6

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# @A330 SERVICE BULLETIN (2) Tools Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for cold working: NOTE: For the definition of capital, durable and expendable tools, refer to SIL 51-012. - Capital tool kit FTI-A330-53-3160-1No.: The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long term investment or can be loaned from FTI. - Durable tool kit No.: DK-A330-53-3160-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by SIL 51-012. - Expendable tool kit No.: EK-A330-53-3160-1 The expendable tool kit contains the quantity of expendable tools necessary to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. (3) Special Tools None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 24 6

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 533160-831-848-001 - MODIFICATION WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Manpower TOTAL MANHOURS 190.50 ELAPSED TIME (HOURS) 97.50 **CONF 002 Manpower TOTAL MANHOURS 192.50 ELAPSED TIME (HOURS) 99.50

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 25 6

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# @A330 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 533160-910-203-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required sealant 09-013 As required sealant 09-016 As required polyurethane primer 16-001 As required polyurethane top coat 16-018 As required wash primer 16-020 As required References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11 51-43-00 51-44-11 51-46-11, Page Block 001 51-46-12 (a) Refer to the Standards Manual (SM) if you find part numbers for the hardware components in the related kit(s) which you can not identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (b) For the specification of the consumable materials (Refer to Consumable Material List (CML)). (c) For the identification of access panels (Refer to AMM 06-41-53, Page Block 001). (d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (e) Remove old sealant with non-metallic scraper and a stiff brush.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 26 6

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# @A330 SERVICE BULLETIN (f) For fastener removal/installation (Rlefer to SRM 51-42-11). (g) For fastener hole and drill data (Refer to SRM 51-44-11). (h) To transfer drill holes, use a pilot drill and a drill bush. (i) Make sure you have the correct edge clearance before you drill the holes. (j) For alternative and substitute fasteners (Refer to SRM 51-43-00). (k) For spot facing of fastener holes (Refer to SRM 51-46-12). (l) For countersinking of fastener holes (Refer to SRM 51-46-11, Page Block 001). (m) 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. (n) Before the installation of structural items, apply sealant 09-005 As required

on the mating surfaces. (o) Wet install rivets, pins and collars with sealant 09-005 As required (p) After installation of structural items, apply fillet seal around the edges with sealant 09-013 As required

or sealant 09-016 As required (q) For the procedure to use sealant (Refer to SRM 51-24-00). (r) After rework, apply wash primer 16-020 As required polyurethane primer 16-001 As required

and polyurethane top coat 16-018 As required

to the rivet heads and tails (Refer to SRM 51-23-00).

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 27 6

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# @A330 SERVICE BULLETIN (2) Subtask 533160-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 533160-910-203-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required sealant 09-013 As required sealant 09-016 As required polyurethane primer 16-001 As required polyurethane top coat 16-018 As required wash primer 16-020 As required References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11 51-43-00 51-44-11 51-46-11, Page Block 001 51-46-12 (a) Refer to the Standards Manual (SM) if you find part numbers for the hardware components in the related kit(s) which you can not identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. (b) For the specification of the consumable materials (Refer to Consumable Material List (CML)). (c) For the identification of access panels (Refer to AMM 06-41-53, Page Block 001).

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 28 6

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# @A330 SERVICE BULLETIN (d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (e) Remove old sealant with non-metallic scraper and a stiff brush. (f) For fastener removal/installation (Rlefer to SRM 51-42-11). (g) For fastener hole and drill data (Refer to SRM 51-44-11). (h) To transfer drill holes, use a pilot drill and a drill bush. (i) Make sure you have the correct edge clearance before you drill the holes. (j) For alternative and substitute fasteners (Refer to SRM 51-43-00). (k) For spot facing of fastener holes (Refer to SRM 51-46-12). (l) For countersinking of fastener holes (Refer to SRM 51-46-11, Page Block 001). (m) 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. (n) Before the installation of structural items, apply sealant 09-005 As required

on the mating surfaces. (o) Wet install rivets, pins and collars with sealant 09-005 As required (p) After installation of structural items, apply fillet seal around the edges with sealant 09-013 As required

or sealant 09-016 As required (q) For the procedure to use sealant (Refer to SRM 51-24-00). (r) After rework, apply wash primer 16-020 As required polyurethane primer 16-001 As required

and polyurethane top coat 16-018 As required
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 29 6

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# @A330 SERVICE BULLETIN to the rivet heads and tails (Refer to SRM 51-23-00). (2) Subtask 533160-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 533160-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 25-33-48, Page Block 401 25-33-52, Page Block 401 25-33-53, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 36-12-41, Page Block 401 36-22-17, Page Block 401 52-10-00, Page Block 201 55-31-11, Page Block 401 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page Block 201). (b) Put the access platform(s) in position in the rear fuselage area and at the FWD passenger/crew doors. (c) Open the access door 312AR in the rear fuselage area. (d) Open the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block 201). (e) Depressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM 29-00-00, Page Block 201). (f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM 29-14-00, Page Block 201).

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 30 6

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# @A330 SERVICE BULLETIN (g) Put warning notices in position to tell persons not to pressurize the hydraulic systems 1 in the cockpit on the hydraulic section 40VU of the overhead panel, 2 on the ground service panel of each hydraulic system. (h) Open, safety and tag the circuit breaker(s) which are listed in 1 AMM 27-51-18, Page Block 401. (i) Remove the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401). (j) Remove the Bleed Air pipe sense line between FR85 and FR87, (Refer to AMM 36-22-17, Page Block 401). (k) Remove the Bleed Air pipe between FR85 and FR87, (Refer to AMM 36-12-41, Page Block 401). (l) Remove the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401). (m) Remove the AFT galley (Refer to AMM 25-33-52, Page Block 401 and AMM 25-33-53, Page Block 401). **CONF 002 (1) Subtask 533160-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 25-33-48, Page Block 401 25-33-52, Page Block 401 25-33-53, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 36-12-41, Page Block 401 36-22-17, Page Block 401 52-10-00, Page Block 201 55-31-11, Page Block 401 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page Block 201). (b) Put the access platform(s) in position in the rear fuselage area and at the FWD passenger/crew doors. (c) Open the access door 312AR in the rear fuselage area. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 31 6

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# @A330 SERVICE BULLETIN (d) Open the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block 201). (e) Depressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM 29-00-00, Page Block 201). (f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM 29-14-00, Page Block 201). (g) Put warning notices in position to tell persons not to pressurize the hydraulic systems 1 in the cockpit on the hydraulic section 40VU of the overhead panel, 2 on the ground service panel of each hydraulic system. (h) Open, safety and tag the circuit breaker(s) which are listed in 1 AMM 27-51-18, Page Block 401. (i) Remove the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401). (j) Remove the Bleed Air pipe sense line between FR85 and FR87, (Refer to AMM 36-22-17, Page Block 401). (k) Remove the Bleed Air pipe between FR85 and FR87, (Refer to AMM 36-12-41, Page Block 401). (l) Remove the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401). (m) Remove the AFT galley (Refer to AMM 25-33-52, Page Block 401 and AMM 25-33-53, Page Block 401). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 533160-831-204-001 - Remove the fasteners in the upper fuselage shell between FR80 and FR87. Manpower Resources Manhours 2.25 Minimum number of person 2 Subtask elapsed time 1.75 Skills AIRFRAME

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 32 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBAAA Removal of Fastener from the upper fuselage shell between FR80 and FR86 Sheet 01 Sheet 02 Sheet 03 Sheet 04 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) At FR80 between STGR2 LH/RH and STGR5 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 03, View C: 6 pin DAN5-8-8 Item (39) Discard 6 collar NAS5075-8 Item (51) Discard (b) At FR84 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B: 12 pin DAN5-6-5 Item (36) Discard 8 pin DAN5-8-10 Item (40) Discard 2 pin DAN5-6-7 Item (37) Discard 8 pin DAN5-8-11 Item (41) Discard 52 pin DAN5-8-7 Item (38) Discard 4 rivet LN9198-4800CF Item (44) Discard 2 rivet LN9198-4000CF Item (43) Discard 14 collar NSA5075-6 Item (54) Discard 68 collar NSA5075-8 Item (51) Discard 1 angle A53985256206 Item (130) Retain 2 angle F53577990000 Item (131) Retain (c) At FR85 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B: 4 pin DAN5-8-10 Item (40) Discard 4 pin DAN5-8-11 Item (41) Discard
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 33 6

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# @A330 SERVICE BULLETIN 4 pin DAN5-8-7 Item (38) Discard 12 collar NSA5075-8 Item (51) Discard (d) At FR86 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B: 16 pin DAN5-6-5 Item (36) Discard 12 pin DAN5-8-11 Item (41) Discard 8 pin DAN5-8-14 Item (42) Discard 82 pin DAN5-8-7 Item (38) Discard 4 pin DAN5-8-10 Item (40) Discard 4 rivet LN9198-4800CF Item (44) Discard 2 rivet LN9198-4000CF Item (43) Discard 16 collar NSA5075-6 Item (54) Discard 106 collar NSA5075-8 Item (51) Discard 2 angle F53577990000 Item (131) Retain 1 angle A53985256206 Item (132) Discard

(2) Subtask 533160-831-205-001 - Do the Eddy Current Rotating Probe Testing FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. Manpower Resources Manhours 3.00 Minimum number of person 3 Subtask elapsed time 1.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 , Procedure A Fig. A-GBDAA Inspection Areas of Fastener Hole Rototest and for HFEC Inspection Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 34 6

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# @A330 SERVICE BULLETIN
CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Do the Eddy Current Rotating Probe Testing , as shown on Fig. A-GBDAA Sheet 01 , Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05 (Refer to NTM 51-10-01, Page Block 601, Procedure A). NOTE: Check only the fastener holes for the fasteners which have been removed to accomplish this modification. 1 In case of no crack finding, continue with the accomplishment of the modification. 2 In case of crack finding, contact AIRBUS for repair. (3) Subtask 533160-831-206-001 - Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GBDAA Inspection Areas of Fastener Hole Rototest and for HFEC Inspection Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Do a eddy current high frequency inspection from the fuselage outside, as shown on Fig. A-GBDAA Sheet 01 , Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 andFig. A-GBDAA Sheet 05 (Refer to NTM 51-10-08, Page Block 601). 1 In case of no crack finding, continue with the accomplishment of the modification. 2 In case of crack finding, contact AIRBUS for repair.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 35 6

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# @A330 SERVICE BULLETIN (4) Subtask 533160-831-207-001 - Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 0.75 Skills AIRFRAME References Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001 Fig. A-GBAAA Removal of Fastener from the upper fuselage shell between FR80 and FR86 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Fig. A-GBEAA Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking Sheet 01 Sheet 02

CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Check the edge clearance of all fastener holes from the outside and from the inside of the fuselage shell as shown on Fig. A-GBAAA Sheet 01 , Fig. A-GBAAA Sheet 02 and Fig. A-GBAAA Sheet 04. If the edge clearance is very close for the current fasteners, try to rework the fastener holes to keep the minimum distance to the structure edge after re-drilling to the final fastener hole diameter as shown on Fig. A-GBEAA Sheet 01 and Fig. A-GBEAA Sheet 02. For the correct edge clearance, refer to SRM 51-47-00. Only in the case that the fastener hole can not be moved to keep the correct edge clearance, an undersize fastener of Kit 533160D03R01 should be installed, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE: In accordance with SRM 51-47-00, Edge Distance for Milling Steps, the additional distance of 1.0 mm (0.039 in) to the edge margin for higher milling steps than 1.0 mm is not applicable for these fastener DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 36 6

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# @A330 SERVICE BULLETIN
holes. NOTE: The installation of undersize fastener is limited by five fastener per reinforcement bracket with a maximum of two fastener adjacent to each other. NOTE: For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . (5) Subtask 533160-831-208-001 - Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Kit 533160D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 39 EN6115K4Y8 6 BOLT 51 ASNA2528-4 6 NUT Kit 533160D02R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 ASNA2528-5 6 NUT 94 EN6115K5-8 6 BOLT References Structural Repair Manual (SRM) 51-48-00 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 37 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBBAA Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00, Page Block 001 and Fig. AGBCAA Sheet 06

. (b) Drill the fastener holes with the correct start drill, as Fig. A-GBCAA Sheet 07

. (c) Ream the fastener holes with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07

. (d) Expand the fastener holes (Refer to SRM 51-48-00, Page Block 001. (e) Ream the fastener holes with the correct gage finish reamer, as shown on Fig. AGBCAA Sheet 07

. NOTE: For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01 . NOTE: If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 38 6

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# @A330 SERVICE BULLETIN (f) At the FR80 in the upper fuselage install as given in Figure Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02, View C and Fig. A-GBCAA Sheet 07: 6 Bolt EN6115K4Y8 Item 39 6 Nut ASNA2528-4 Item 51 or next oversize (part of Kit 533160D02R05) 6 Bolt EN6115K5-8 Item 94 6 Nut ASNA2528-5 Item 52

(6) Subtask 533160-831-209-001 - Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. Manpower Resources Manhours 35.00 Minimum number of person 3 Subtask elapsed time 11.50 Skills AIRFRAME Material necessary to do the job Kit 533160D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 F5357716920000 1 DOUBLER 2 F5357716920100 1 DOUBLER 3 F5357716920200 1 DOUBLER 4 F5357716920300 1 DOUBLER 5 F5357798920000 1 SHIM 6 F5357798920100 1 SHIM 7 F5357798920200 1 SHIM 8 F5357798920300 1 SHIM 9 A5398525620600 1 ANGLE 18 DAN5-5-4 2 PIN 19 DAN5-6-3 14 PIN 20 DAN5-6-4 2 PIN 21 DAN5-6-5 10 PIN 22 DAN5-6-6 20 PIN 24 DAN5-6-8 10 PIN 26 DAN7-8-9 4 PIN 27 DAN7-8-10 4 PIN 28 DAN7-8-11 6 PIN 29 DAN7-10-11 8 PIN 30 DAN7-10-12 6 PIN 31 DAN7-10-17 4 PIN 38 EN6115K4Y7 16 BOLT DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 39 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 40 EN6115K4Y10 4 BOLT 41 EN6115K4Y11 4 BOLT 42 EN6115K4Y12 14 BOLT 45 NSA5075-5 2 COLLAR 46 NSA5075-6 56 COLLAR 48 DAN12-8 14 COLLAR 49 DAN12-10 18 COLLAR 50 ASNA2528-3 26 NUT 51 ASNA2528-4 38 NUT 52 ASNA2528-5 40 NUT 53 NSA5330-6 6 COLLAR 54 DAN12-8Y 10 COLLAR 57 DAN5-6-7Y 2 PIN 58 DAN5-6-8Y 4 PIN 60 DAN7-8-10Y 4 PIN 61 DAN7-8-11Y 4 PIN 62 DAN7-8-12Y 2 PIN 63 EN6115K3-3 10 BOLT 64 EN6115K3-4 6 BOLT 65 EN6115K3-5 10 BOLT 68 EN6115K5-10 8 BOLT 69 EN6115K5-11 8 BOLT 70 EN6115K5-12 8 BOLT 71 EN6115K5-17 8 BOLT 72 EN6115K5-19 8 BOLT 75 EN6080D5-06 1 RIVET 76 LN9198-4812CF 2 RIVET 77 LN9198-4814CF 4 RIVET 124 EN6115K3A7 2 BOLT 126 ASNA2528-3A 2 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required References Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801 Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 40 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBBAA Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B L/H. 1 Clean the working area with cleaning agent 11-026 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 5 and the doubler, item 1 to the fuselage structure. 2 Countersink (100 DEG) the rivet hole, previously used to fit the angle, item (132), as shown on Fig. A-GBBAA Sheet 03

. 3 Close one rivet hole, previously used to fit the angle, item (132), as shown on Fig. A-GBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet 06 with 1 Rivet EN6080D5-06 Item 75 NOTE: Install the rivet, item 75, with 09-005 sealant.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 41 6

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# @A330 SERVICE BULLETIN
4 Put the shim, item 5 and the doubler, item 1 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 03

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 5 Transfer drill the pilot holes from the shim, item 5 and from the doubler, item 1 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 6 Transfer drill the existing fastener holes from the fuselage structure to the doubler, item 1, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 7 Mark the fastener holes with a soft felt pen which have to be expand by cold working, as shown on Fig. A-GBBAA Sheet 04

. 8 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 9 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 10 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 11 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 13 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Put the angle, item 9, in position, as shown on Fig. A-GBBAA Sheet 03

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 42 6

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# @A330 SERVICE BULLETIN
15 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 16 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 05

. 17 Remove the angle, item 9, from the fuselage skin. 18 Remove the doubler, item 1 and the shim, item 5 from the fuselage structure. 19 Deburr the fastener holes. 20 Clean the shim, item 5, the doubler, item 1 and the fuselage structure with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required 21 Install with screw pins, as shown on Fig. A-GBCAA Sheet 03: 1 Doubler F5357716920000 Item 1 1 Shim F5357798920000 Item 5 with: sealant 09-005 As required

22 Put in position, with sealant 09-005 As required and secure with screw pins, as shown on Fig. A-GBCAA Sheet 03: 1 Angle A5398525620600 Item 9

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 43 6

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# @A330 SERVICE BULLETIN
23 To the fuselage skin, the doubler, item 1 and the shim, item 5, install with sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. a For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 2 Pin DAN5-5-4 Item 18 3 Pin DAN5-6-3 Item 19 2 Pin DAN5-6-5 Item 21 4 Pin DAN5-6-6 Item 22 2 Pin DAN5-6-8 Item 24 b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 2 Pin DAN7-8-11 Item 28 4 Pin DAN7-10-11 Item 29 c For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 3 Pin DAN7-10-12 Item 30 2 Pin DAN7-10-17 Item 31 d For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN5-6-7Y Item 57 2 Pin DAN5-6-8Y Item 58 2 Pin DAN7-8-10Y Item 60
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 44 6

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# @A330 SERVICE BULLETIN
2 Pin DAN7-8-11Y Item 61 e For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 f For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 3 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Bolt EN6115K4Y12 Item 42 g For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 2 Bolt EN6115K3-3 Item 63 2 Bolt EN6115K3-4 Item 64 2 Bolt EN6115K3-5 Item 65 1 Bolt EN6115K3A7 Item 124 h For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-17 Item 71 with 4 Nut ASNA2528-5 Item 52 13 Nut ASNA2528-4 Item 51 6 Nut ASNA2528-3 Item 50 5 Collar DAN12-8Y Item 54 11 Collar NSA5075-6 Item 46 3 Collar NSA5330-6 Item 53 2 Collar NSA5075-5 Item 45 4 Collar DAN12-8 Item 48 9 Collar DAN12-10 Item 49 1 nut ASNA2528-3A Item 126

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 45 6

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# @A330 SERVICE BULLETIN
24 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 6 and the doubler, item 2 to the fuselage structure. 2 Put the shim, item 6 and the doubler, item 2 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 05

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 6 and from the doubler, item 2 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 2, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 5 Mark the fastener holes with a soft felt pen which have to be expand by cold working, as shown on Fig. A-GBCAA Sheet 06

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 46 6

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# @A330 SERVICE BULLETIN
7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 14 Remove the doubler, item 2 and the shim, item 6 from the fuselage structure. 15 Deburr the fastener holes. 16 Clean the shim, item 6, the doubler, item 2 and the fuselage structure with cleaning agent 11-026 As required
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 47 6

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# @A330 SERVICE BULLETIN
and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 05: 1 Doubler F5357716920100 Item 2 1 Shim F5357798920100 Item 6 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 2 and the shim, item 6, install with: sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. a For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 5 Pin DAN5-6-3 Item 19 2 Pin DAN5-6-5 Item 21 4 Pin DAN5-6-6 Item 22 2 Pin DAN5-6-8 Item 24 b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 2 Pin DAN7-8-11 Item 28 c For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 4 Pin DAN7-10-11 Item 29

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 48 6

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# @A330 SERVICE BULLETIN
3 Pin DAN7-10-12 Item 30 2 Pin DAN7-10-17 Item 31 d For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN5-6-7Y Item 57 2 Pin DAN5-6-8Y Item 58 2 Pin DAN7-8-10Y Item 60 2 Pin DAN7-8-11Y Item 61 e For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 f For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 3 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Bolt EN6115K4Y12 Item 42 g For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 2 Bolt EN6115K3-3 Item 63 2 Bolt EN6115K3-4 Item 64 2 Bolt EN6115K3-5 Item 65 1 Bolt EN6115K3A7 Item 124 h For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-17 Item 71 with: 4 Nut ASNA2528-5 Item 52 13 Nut ASNA2528-4 Item 51 6 Nut ASNA2528-3 Item 50 5 Collar DAN12-8Y Item 54 13 Collar NSA5075-6 Item 46 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 49 6

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# @A330 SERVICE BULLETIN
3 Collar NSA5330-6 Item 53 4 Collar DAN12-8 Item 48 9 Collar DAN12-10 Item 49 1 nut ASNA2528-3A Item 126 19 Clean the repair area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required (c) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A L/H. 1 Clean the working area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 7 and the doubler, item 3 to the fuselage structure. 2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAA Sheet 07, View J. 3 Drill with a 4.8 mm (0.19 in.) DIA drill the new hole with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole. 5 Remove the surface protection around the rivet holes of angle, item (131), for electrical bonding. 6 Install, as shown on Fig. A-GBBAA Sheet 07, Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 06: 1 angle F53577990000 Item (131) 1 Rivet LN9198-4812CF Item 76 2 Rivet LN9198-4814CF Item 77 with: sealant 09-005 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 50 6

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# @A330 SERVICE BULLETIN
NOTE: Install the angle, item (131), as electrical bonding point, refer to ESPM 20-51-20 and refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 7 and the doubler, item 3 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 07

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Transfer drill the pilot holes from the shim, item 7 and from the doubler, item 3 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 3, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 08

. 11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 51 6

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# @A330 SERVICE BULLETIN
16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to maximum of 16 mm (0.63 in) on the doubler, item 3 located at FR86, as shown on Fig. A-GBBAA Sheet 08

. 20 Remove the doubler, item 3 and the shim, item 7 from the fuselage structure. 21 Deburr the fastener holes. 22 Clean the shim, item 7, the doubler, item 3 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 07: 1 Doubler F5357716920200 Item 3 1 Shim F5357798920200 Item 7 with: sealant 09-005 As required

24 To the fuselage skin, the doubler, item 3 and the shim, item 7, install with sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 52 6

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# @A330 SERVICE BULLETIN
NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. a For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 3 Pin DAN5-6-3 Item 19 1 Pin DAN5-6-4 Item 20 3 Pin DAN5-6-5 Item 21 6 Pin DAN5-6-6 Item 22 3 Pin DAN5-6-8 Item 24 b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 1 Pin DAN7-8-11 Item 28 c For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 5 Bolt EN6115K4Y7 Item 38 1 Bolt EN6115K4Y12 Item 42 d For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 3 Bolt EN6115K3-3 Item 63 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 e For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-10 Item 68 4 Bolt EN6115K5-11 Item 69 4 Bolt EN6115K5-12 Item 70

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 53 6

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# @A330 SERVICE BULLETIN
f For the following fasteners, as shown on Fig. A-GBCAA Sheet 10

. 4 Bolt EN6115K5-19 Item 72 with 3 Collar DAN12-8 Item 48 6 Nut ASNA2528-4 Item 51 7 Nut ASNA2528-3 Item 50 16 Nut ASNA2528-5 Item 52 16 Collar NSA5075-6 Item 46 25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (d) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 8 and the doubler, item 4 to the fuselage structure. 2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAA Sheet 07, View J. 3 Drill with a 4.8 (0.19 in.) mm DIA drill the new hole with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole. 5 Remove the surface protection around the rivet holes of the angle, item (131) for electrical bonding. 6 Install, as shown on Fig. A-GBBAA Sheet 07, Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 06: 1 Angle F53577990000 Item (131)

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 54 6

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# @A330 SERVICE BULLETIN
1 Rivet LN9198-4812CF Item 76 2 Rivet LN9198-4814CF Item 77 with: sealant 09-005 As required

NOTE: Install the angle, item (131) as electrical bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 8 and the doubler, item 4 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 07

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Transfer drill the pilot holes from the shim, item 8 and from the doubler, item 4 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 4, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 08

. 11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 55 6

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# @A330 SERVICE BULLETIN
14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to maximum of 16 mm (0.63 in) on the doubler, item 4 located at FR86, as shown on Fig. A-GBBAA Sheet 08

. 20 Remove the doubler, item 4 and the shim, item 8 from the fuselage structure. 21 Deburr the fastener holes. 22 Clean the shim, item 8, the doubler, item 4 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 07: 1 Doubler F5357716920300 Item 4 1 Shim F5357798920300 Item 8 with: sealant 09-005 As required
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 56 6

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# @A330 SERVICE BULLETIN
24 To the fuselage skin, the doubler, item 4 and the shim, item 8, install with sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. a For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 3 Pin DAN5-6-3 Item 19 1 Pin DAN5-6-4 Item 20 3 Pin DAN5-6-5 Item 21 6 Pin DAN5-6-6 Item 22 3 Pin DAN5-6-8 Item 24 b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 1 Pin DAN7-8-11 Item 28 c For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 5 Bolt EN6115K4Y7 Item 38 1 Bolt EN6115K4Y12 Item 42 d For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 3 Bolt EN6115K3-3 Item 63 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 57 6

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# @A330 SERVICE BULLETIN

e For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-10 Item 68 4 Bolt EN6115K5-11 Item 69 4 Bolt EN6115K5-12 Item 70 f For the following fasteners, as shown on Fig. A-GBCAA Sheet 10

. 4 Bolt EN6115K5-19 Item 72 with 6 Nut ASNA2528-4 Item 51 3 Collar DAN12-8 Item 48 16 Nut ASNA2528-5 Item 52 7 Nut ASNA2528-3 Item 50 16 Collar NSA5075-6 Item 46 25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (7) Subtask 533160-831-210-001 - Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. Manpower Resources Manhours 33.50 Minimum number of person 3 Subtask elapsed time 10.50 Skills AIRFRAME Material necessary to do the job Kit 533160D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 10 F5357716921800 1 DOUBLER 11 F5357716921900 1 DOUBLER 12 F5357716922100 1 DOUBLER 13 F5357716922000 1 DOUBLER 14 F5357798921200 1 SHIM
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 58 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 15 F5357798921400 1 SHIM 16 F5357798921700 1 SHIM 17 F5357798921600 1 SHIM 23 DAN5-6-7 8 PIN 24 DAN5-6-8 6 PIN 25 DAN5-6-10 8 PIN 28 DAN7-8-11 6 PIN 32 DAN5-6-7X 4 PIN 33 DAN5-6-10X 4 PIN 34 DAN7-6-11Y 2 PIN 35 DAN7-8-13Y 6 PIN 36 DAN7-8-15Y 6 PIN 37 DAN7-8-16Y 6 PIN 43 EN6115K4Y15 2 BOLT 44 EN6115K4Y16 2 BOLT 46 NSA5075-6 22 COLLAR 47 DAN12-6Y 2 COLLAR 48 DAN12-8 6 COLLAR 50 ASNA2528-3 34 NUT 51 ASNA2528-4 4 NUT 54 DAN12-8Y 62 COLLAR 55 DAN12-8X 2 COLLAR 56 DAN11-6X 8 COLLAR 59 DAN7-8-12X 2 PIN 60 DAN7-8-10Y 16 PIN 61 DAN7-8-11Y 16 PIN 62 DAN7-8-12Y 12 PIN 64 EN6115K3-4 4 BOLT 65 EN6115K3-5 12 BOLT 66 EN6115K3-7 10 BOLT 67 EN6115K3-8 8 BOLT 73 LN9198-4012CF 1 RIVET 74 LN9198-4014CF 1 RIVET 77 LN9198-4814CF 4 RIVET 125 EN6115K3A8 2 BOLT 126 ASNA2528-3A 2 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 59 6

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# @A330 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801 Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001 Fig. A-GBBAA Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A L/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 10 and the doubler, item 14 to the fuselage structure. 2 Mark the new holes for the angles, item (130) and (131), as shown on Fig. AGBBAA Sheet 09, View N. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 60 6

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# @A330 SERVICE BULLETIN
3 Drill with a 4.1 mm (0.16 in.) DIA drill the new holes with the angle, item (130). 4 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131). 5 Remove the angles, item (130) and (131) from the fuselage skin and deburr the rivet holes. 6 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 7 Install, as shown on Fig. A-GBBAA Sheet 09, Fig. A-GBBAA Sheet 10 and Fig. A-GBCAA Sheet 06: 1 angle A5398525620600 Item (130) 1 angle F5357799000000 Item (131) 1 Rivet LN9198-4012CF Item 73 1 Rivet LN9198-4014CF Item 74 2 Rivet LN9198-4814CF Item 77 with: sealant 09-005 As required NOTE : Install the angle, item (131) as electrical bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 8 Put the shim, item 14 and the doubler, item 10 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 09

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the pilot holes from the shim, item 14 and from the doubler, item 10 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 10 Transfer drill the fastener holes from the fuselage structure to the doubler, item 10 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 11 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 10

.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 61 6

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# @A330 SERVICE BULLETIN
12 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 13 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 14 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 16 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 17 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 18 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 19 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 20 Remove the doubler, item 10 and the shim, item 14 from the fuselage structure. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 62 6

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# @A330 SERVICE BULLETIN
21 Deburr the fastener holes. 22 Clean the shim, item 14, the doubler, item 10 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 09 : 1 Doubler F5357716921800 Item 10 1 Shim F5357798921200 Item 14 with: sealant 09-005 As required

24 To the fuselage skin, the doubler, item 10 and the shim, item 14, install with sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-7 Item 23 2 Pin DAN5-6-8 Item 24 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 1 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 63 6

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# @A330 SERVICE BULLETIN
2 Pin DAN5-6-7X Item 32 1 Pin DAN5-6-10X Item 33 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 1 Pin DAN7-6-11Y Item 34 3 Pin DAN7-8-15Y Item 36 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 5 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y15 Item 43 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 3 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 with 5 Collar NSA5075-6 Item 46 1 Collar DAN12-6Y Item 47 1 Collar DAN12-8 Item 48 9 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 16 Collar DAN12-8Y Item 54 3 Collar DAN11-6X Item 56 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 64 6

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# @A330 SERVICE BULLETIN
25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 11 and the doubler, item 15 to the fuselage structure. 2 Mark the new holes for the angle, item (131), as shown on Fig. A-GBBAA Sheet 11 , View R. 3 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet holes. 5 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 6 Install, as shown on Fig. A-GBBAA Sheet 11 , Fig. A-GBBAA Sheet 12 and Fig. A-GBCAA Sheet 06: 1 angle F5357799000000 Item (131) 2 Rivet LN9198-4814CF Item 77 with: sealant 09-005 As required NOTE : Install the angle, item (131) , as bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 15 and the doubler, item 11 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 11

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 65 6

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# @A330 SERVICE BULLETIN
8 Transfer drill the pilot holes from the shim, item 15 and from the doubler, item 11 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 11 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 12

. 11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04Kit 533160D03R01, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 66 6

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# @A330 SERVICE BULLETIN
533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Remove the doubler, item 11 and the shim, item 15 from the fuselage structure. 20 Deburr the fastener holes. 21 Clean the shim, item 15, the doubler, item 11 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 22 Install with screw pins, as shown on Fig. A-GBBAA Sheet 11 : 1 Doubler F5357716921900 Item 11 1 Shim F5357798921400 Item 15 with: sealant 09-005 As required

23 To the fuselage skin, the doubler, item 11 and the shim, item 15, install with sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 67 6

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# @A330 SERVICE BULLETIN
1 Pin DAN5-6-7 Item 23 2 Pin DAN5-6-8 Item 24 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 1 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 1 Pin DAN5-6-10X Item 33 2 Pin DAN5-6-7X Item 32 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 1 Pin DAN7-6-11Y Item 34 3 Pin DAN7-8-15Y Item 36 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 5 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y15 Item 43 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 3 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 with
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 68 6

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# @A330 SERVICE BULLETIN
5 Collar NSA5075-6 Item 46 1 Collar DAN12-6Y Item 47 1 Collar DAN12-8 Item 48 9 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 16 Collar DAN12-8Y Item 54 3 Collar DAN11-6X Item 56 24 Clean the repair area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required (c) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A L/H. 1 Clean the working area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 13 and the doubler, item 17 to the fuselage structure. 2 Put the shim, item 17 and the doubler, item 13 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 13

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 17 and from the doubler, item 13 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 13 with a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 69 6

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# @A330 SERVICE BULLETIN
5 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 14

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 70 6

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# @A330 SERVICE BULLETIN
14 Remove the doubler, item 13 and the shim, item 17 from the fuselage structure. 15 Deburr the fastener holes. 16 Clean the shim, item 17, the doubler, item 13 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 13 : 1 Doubler F5357716922000 Item 13 1 Shim F5357798921600 Item 17 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 13 and the shim, item 17, install with: sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-8 Item 24 3 Pin DAN5-6-7 Item 23 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 2 Pin DAN7-8-11 Item 28
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 71 6

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# @A330 SERVICE BULLETIN
NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 1 Pin DAN5-6-10X Item 33 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 3 Pin DAN7-8-13Y Item 35 3 Pin DAN7-8-16Y Item 37 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN7-8-12X Item 59 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y16 Item 44 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 2 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 1 Bolt EN6115K3A8 Item 125 with 6 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48 8 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 15 Collar DAN12-8Y Item 54 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 72 6

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# @A330 SERVICE BULLETIN
1 Collar DAN12-8X Item 55 1 Collar DAN11-6X Item 56 1 nut ASNA2528-3A Item 126 19 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (d) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 12 and the doubler, item 16 to the fuselage structure. 2 Put the shim, item 16 and the doubler, item 12 in the final position on the fuselage structure, as shown on Fig. A-GBBAA Sheet 13

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 16 and from the doubler, item 12 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 12 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 5 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAA Sheet 14

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and, as shown on Fig. A-GBCAA Sheet 01 Fig. A-GBCAA Sheet 10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 73 6

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# @A330 SERVICE BULLETIN
7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-001, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 001 Installation of undersize fasteners of kit 533160D03R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 14 Remove the doubler, item 12 and the shim, item 16 from the fuselage structure. 15 Deburr the fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 74 6

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# @A330 SERVICE BULLETIN
16 Clean the shim, item 16, the doubler, item 12 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 13 : 1 Doubler F5357716922100 Item 12 1 Shim F5357798921700 Item 16 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 12 and the shim, item 16, install with: sealant 09-005 As required as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-8 Item 24 3 Pin DAN5-6-7 Item 23 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 2 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 1 Pin DAN5-6-10X Item 33

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 75 6

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# @A330 SERVICE BULLETIN
NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 3 Pin DAN7-8-13Y Item 35 3 Pin DAN7-8-16Y Item 37 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN7-8-12X Item 59 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y16 Item 44 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 2 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 1 Bolt EN6115K3A8 Item 125 with 6 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48 8 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 15 Collar DAN12-8Y Item 54 1 Collar DAN12-8X Item 55 1 Collar DAN11-6X Item 56 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 76 6

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# @A330 SERVICE BULLETIN
1 nut ASNA2528-3A Item 126 19 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (8) Subtask 533160-831-211-001 - Install fasteners with cold working in the upper fuselage skin at FR85 Manpower Resources Manhours 2.25 Minimum number of person 2 Subtask elapsed time 1.25 Skills AIRFRAME Material necessary to do the job Kit 533160D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 38 EN6115K4Y7 4 BOLT 40 EN6115K4Y10 4 BOLT 41 EN6115K4Y11 4 BOLT 51 ASNA2528-4 12 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required References Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 77 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Fig. A-GBBAA Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the fasteners with cold working at FR85 between STGR2B L/H and STGR5A L/H. 1 Clean the working area with cleaning agent 11-026 As required

2 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Drill the marked fastener holes for cold working with the correct start drill, as shown onFig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 4 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 78 6

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# @A330 SERVICE BULLETIN
5 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 6 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 7 Deburr the fastener holes. 8 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

9 Install the fastener with sealant 09-005 As required , as shown on Fig. A-GBBAA Sheet 15 and Fig. A-GBCAA Sheet 07: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. 2 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Nut ASNA2528-4 Item 51 10 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the fasteners with cold working at FR85 between STGR2B R/H and STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 79 6

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# @A330 SERVICE BULLETIN
and lint-free cloth 19-003 As required 2 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 4 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 5 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 6 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 7 Deburr the fastener holes. 8 Clean the repair area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required

9 Install the fastener with: sealant 09-005 As required , as shown on Fig. A-GBBAA Sheet 15 and Fig. A-GBCAA Sheet 07: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D02R05. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 001 Oversize fasteners of kit 533160D02R01

. 2 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 80 6

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# @A330 SERVICE BULLETIN
2 Bolt EN6115K4Y11 Item 41 6 Nut ASNA2528-4 Item 51 10 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required lint-free cloth 19-003 As required (9) Subtask 533160-831-212-001 - Apply surface protection to the modification area. Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-013 As required sealant 09-016 As required corrosion preventive 15-005 As required polyurethane primer 16-001 As required polyurethane top coat 16-018 As required wash primer 16-020 As required CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. Apply surface protection to the modification area. (a) Apply sealant 09-013 As required

or sealant 09-016 As required

to form a bead around the new doubler and reinstalled angles.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 81 6

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# @A330 SERVICE BULLETIN (b) Apply wash primer 16-020 As required

to all reworked edges and heads of fasteners. (c) Apply polyurethane primer 16-001 As required

to all reworked edges and heads of fasteners. (d) Apply polyurethane top coat 16-018 As required

to all reworked edges and heads of fasteners. (e) Apply corrosion preventive 15-005 As required

to the modification area inside the fuselage. (10) Subtask 533160-400-201-001 - Installation of undersize fasteners of kit 533160D03R01 Manpower Resources Manhours 0.00 Minimum number of person 0 Subtask elapsed time 0.00 Skills NON SPECIFIC Material necessary to do the job Kit 533160D03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 32 DAN5-6-7X 2 PIN 34 DAN7-6-11Y 5 PIN 40 EN6115K4Y10 5 BOLT 41 EN6115K4Y11 5 BOLT 42 EN6115K4Y12 5 BOLT 47 DAN12-6Y 5 COLLAR 51 ASNA2528-4 5 NUT 54 DAN12-8Y 5 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 59 DAN7-8-12X 5 PIN 61 DAN7-8-11Y 5 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 82 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 62 DAN7-8-12Y 5 PIN 82 DAN5-6-8X 4 PIN 84 DAN7-8-10X 5 PIN 85 DAN7-8-11X 5 PIN 114 DAN7-6-9Y 4 PIN 115 DAN7-6-10Y 2 PIN 116 DAN7-8-17Y 4 PIN 117 DAN7-6-11X 2 PIN 118 DAN7-8-13X 5 PIN 119 DAN7-8-15X 5 PIN 120 DAN7-8-16X 5 PIN 121 DAN12-6X 2 COLLAR 122 EN6115K4Y17 5 BOLT 123 EN6115K4Y19 5 BOLT References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) The subsequent undersize fasteners are parts of Kit 533160D03R01. NOTE: Depending of the edge margin measurement requested with subtask 533160-831-207-001 undersize fasteners can be installed. Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 NOTE: The installation of undersize fasteners is limited by five fasteners per reinforcement bracket with a maximum of two fasteners adjacent to each other. If it is not the case, contact AIRBUS. 2 Pin DAN5-6-7X Item 32 5 Pin DAN7-6-11Y Item 34 5 Bolt EN6115K4Y10 Item 40 5 Bolt EN6115K4Y11 Item 41 5 Bolt EN6115K4Y12 Item 42
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 83 6

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# @A330 SERVICE BULLETIN
5 Collar DAN12-6Y Item 47 5 Nut ASNA2528-4 Item 51 5 Collar DAN12-8Y Item 54 5 Collar DAN12-8X Item 55 5 Collar DAN11-6X Item 56 5 Pin DAN7-8-12X Item 59 5 Pin DAN7-8-11Y Item 61 5 Pin DAN7-8-12Y Item 62 4 Pin DAN5-6-8X Item 82 5 Pin DAN7-8-10X Item 84 5 Pin DAN7-8-11X Item 85 4 Pin DAN7-6-9Y Item 114 2 Pin DAN7-6-10Y Item 115 4 Pin DAN7-8-17Y Item 116 2 Pin DAN7-6-11X Item 117 5 Pin DAN7-8-13X Item 118 5 Pin DAN7-8-15X Item 119 5 Pin DAN7-8-16X Item 120 2 Collar DAN12-6X Item 121 5 Bolt EN6115K4Y17 Item 122 5 Bolt EN6115K4Y19 Item 123

(11) Subtask 533160-400-202-001 - Oversize fasteners of kit 533160D02R01 Manpower Resources Manhours 0.00 Minimum number of person 0 Subtask elapsed time 0.00 Skills NON SPECIFIC

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 84 6

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# @A330 SERVICE BULLETIN Material necessary to do the job Kit 533160D02R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 20 DAN5-6-4 2 PIN 28 DAN7-8-11 PIN 29 DAN7-10-11 5 PIN 30 DAN7-10-12 5 PIN 32 DAN5-6-7X 5 PIN 33 DAN5-6-10X 5 PIN 46 NSA5075-6 2 COLLAR 48 DAN12-8 2 COLLAR 49 DAN12-10 5 COLLAR 50 ASNA2528-3 5 NUT 51 ASNA2528-4 4 NUT 52 ASNA2528-5 NUT 53 NSA5330-6 5 COLLAR 54 DAN12-8Y 2 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 57 DAN5-6-7Y 4 PIN 62 DAN7-8-12Y 2 PIN 68 EN6115K5-10 5 BOLT 69 EN6115K5-11 5 BOLT 70 EN6115K5-12 5 BOLT 78 DAN5-6-3X 5 PIN 79 DAN5-6-4X 2 PIN 80 DAN5-6-5X 5 PIN 81 DAN5-6-6X 5 PIN 82 DAN5-6-8X 5 PIN 83 DAN7-8-9X 4 PIN 84 DAN7-8-10X 4 PIN 85 DAN7-8-11X 5 PIN 86 DAN7-10-11X 5 PIN 87 DAN7-10-12X 5 PIN 88 DAN7-10-17X 4 PIN 89 DAN5-6-10Y 4 PIN 90 DAN7-10-13 5 PIN 91 DAN7-10-15 5 PIN 92 DAN7-10-16 5 PIN 93 EN6115K5-7 5 BOLT 94 EN6115K5-8 BOLT 95 EN6115K5-15 2 BOLT 96 EN6115K5-16 2 BOLT 97 DAN12-10X 5 COLLAR 98 NSA5075-8 5 COLLAR
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 85 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 99 DAN5-8-7 2 PIN 100 DAN5-8-8 4 PIN 101 DAN7-10-10 5 PIN 102 EN6115K3X3 5 BOLT 103 EN6115K3X4 5 BOLT 104 EN6115K3X5 5 BOLT 105 EN6115K4-7 2 BOLT 106 EN6115K3X7 5 BOLT 107 EN6115K3X8 5 BOLT 108 EN6115K4-8 2 BOLT 109 EN6115K5X10 5 BOLT 110 EN6115K5X11 5 BOLT 111 EN6115K5X12 5 BOLT 112 EN6115K5X17 5 BOLT 113 EN6115K5X19 5 BOLT References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) If fasteners of Kit 533160D01R04 do not fit because oversize fasteners are necessary, then refer to the fastener tables, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of kit Kit 533160D02R05 and listed below: 2 Pin DAN5-6-4 Item 20 2 Pin DAN7-8-11 Item 28 5 Pin DAN7-10-11 Item 29 5 Pin DAN7-10-12 Item 30 5 Pin DAN5-6-7X Item 32 5 Pin DAN5-6-10X Item 33 2 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 86 6

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# @A330 SERVICE BULLETIN
5 Collar DAN12-10 Item 49 5 Nut ASNA2528-3 Item 50 4 Nut ASNA2528-4 Item 51 10 Nut ASNA2528-5 Item 52 5 Collar NSA5330-6 Item 53 2 Collar DAN12-8Y Item 54 5 Collar DAN12-8X Item 55 5 Collar DAN11-6X Item 56 4 Pin DAN5-6-7Y Item 57 2 Pin DAN7-8-12Y Item 62 5 Bolt EN6115K5-10 Item 68 5 Bolt EN6115K5-11 Item 69 5 Bolt EN6115K5-12 Item 70 5 Pin DAN5-6-3X Item 78 2 Pin DAN5-6-4X Item 79 5 Pin DAN5-6-5X Item 80 5 Pin DAN5-6-6X Item 81 5 Pin DAN5-6-8X Item 82 4 Pin DAN7-8-9X Item 83 4 Pin DAN7-8-10X Item 84 5 Pin DAN7-8-11X Item 85 5 Pin DAN7-10-11X Item 86 5 Pin DAN7-10-12X Item 87 4 Pin DAN7-10-17X Item 88 4 Pin DAN5-6-10Y Item 89 5 Pin DAN5-6-10Y Item 89 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 87 6

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# @A330 SERVICE BULLETIN
5 Pin DAN7-10-13 Item 90 5 Pin DAN7-10-15 Item 91 5 Pin DAN7-10-16 Item 92 5 Bolt EN6115K5-7 Item 93 5 Bolt EN6115K5-8 Item 94 2 Bolt EN6115K5-15 Item 95 2 Bolt EN6115K5-16 Item 96 5 Collar DAN12-10X Item 97 5 Collar NSA5075-8 Item 98 2 Pin DAN5-8-7 Item 99 4 Pin DAN5-8-8 Item 100 5 Pin DAN7-10-10 Item 101 5 Bolt EN6115K3X3 Item 102 5 Bolt EN6115K3X4 Item 103 5 Bolt EN6115K3X5 Item 104 2 Bolt EN6115K4-7 Item 105 5 Bolt EN6115K3X7 Item 106 5 Bolt EN6115K3X8 Item 107 2 Bolt EN6115K4-8 Item 108 5 Bolt EN6115K5X10 Item 109 5 Bolt EN6115K5X11 Item 110 5 Bolt EN6115K5X12 Item 111 5 Bolt EN6115K5X17 Item 112 5 Bolt EN6115K5X19 Item 113

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 88 6

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# @A330 SERVICE BULLETIN
**CONF 002 (1) Subtask 533160-831-204-002 - Remove the fasteners in the upper fuselage shell between FR80 and FR87. Manpower Resources Manhours 2.25 Minimum number of person 2 Subtask elapsed time 1.75 Skills AIRFRAME References Fig. A-GBAAB Removal of Fastener from the upper fuselage shell between FR80 and FR86 Sheet 01 Sheet 02 Sheet 03 Sheet 04 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) At FR80 between STGR2 LH/RH and STGR5 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View C: 6 pin DAN5-8-8 Item (39) Discard 6 collar NAS5075-8 Item (51) Discard (b) At FR84 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View B : 12 pin DAN5-6-5 Item (36) Discard 8 pin DAN5-8-10 Item (40) Discard 2 pin DAN5-6-7 Item (37) Discard 8 pin DAN5-8-11 Item (41) Discard 52 pin DAN5-8-7 Item (38) Discard 4 rivet LN9198-4800CF Item (44) Discard 2 rivet LN9198-4000CF Item (43) Discard 14 collar NSA5075-6 Item (54) Discard 68 collar NSA5075-8 Item (51) Discard
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 89 6

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# @A330 SERVICE BULLETIN 1 angle A53985256206 Item (130) Retain 2 angle F53577990000 Item (131) Retain (c) At FR85 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View B : 4 pin DAN5-8-10 Item (40) Discard 4 pin DAN5-8-11 Item (41) Discard 4 pin DAN5-8-7 Item (38) Discard 12 collar NSA5075-8 Item (51) Discard (d) At FR86 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown Fig. A-GBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View B : 18 pin DAN5-6-5 Item (36) Discard 12 pin DAN5-8-11 Item (41) Discard 8 pin DAN5-8-14 Item (42) Discard 82 pin DAN5-8-7 Item (38) Discard 4 pin DAN5-8-10 Item (40) Discard 4 rivet LN9198-4800CF Item (44) Discard 2 rivet LN9198-4000CF Item (43) Discard 18 collar NSA5075-6 Item (54) Discard 106 collar NSA5075-8 Item (51) Discard 2 angle F53577990000 Item (131) Retain 1 angle A53985256206 Item (132) Discard

(2) Subtask 533160-831-205-002 - Do the Eddy Current Rotating Probe Testing of FR80, FR84 and FR86 to find cracks around the holes of the previous removed fasteners. Manpower Resources Manhours 3.00 Minimum number of person 3 Subtask elapsed time 1.00 Skills AIRFRAME DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 90 6

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# @A330 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 , Procedure A Fig. A-GBDAA Inspection Areas of Fastener Hole Rototest and for HFEC Inspection Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Do the Eddy Current Rotating Probe Testing as shown on Fig. A-GBDAA Sheet 01 , Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05.(Refer to NTM 51-10-01, Page Block 601 , Procedure A). NOTE: Check only the fastener holes for the fasteners which have been removed to accomplish this modification 1 In case of no crack finding, continue with the accomplishment of the modification. 2 In case of crack finding, contact AIRBUS for repair. (3) Subtask 533160-831-206-002 - Do the eddy current high frequency inspection of FR84 and FR86 to find cracks between the fastener rows. Manpower Resources Manhours 2.50 Minimum number of person 2 Subtask elapsed time 1.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GBDAA Inspection Areas of Fastener Hole Rototest and for HFEC Inspection Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 91 6

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# @A330 SERVICE BULLETIN (a) Do a eddy current high frequency inspection from the fuselage outside, as shown on Fig. A-GBDAA Sheet 01 , Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05 (Refer to NTM 51-10-08, Page Block 601). 1 In case of no crack finding, continue with the accomplishment of the modification. 2 In case of crack finding, contact AIRBUS for repair. (4) Subtask 533160-831-207-002 - Do a check of the fastener position to make sure that the edge clearance of all existing fastener holes is correct. Manpower Resources Manhours 1.50 Minimum number of person 2 Subtask elapsed time 0.75 Skills AIRFRAME References Structural Repair Manual (SRM) 51-47-00 Fig. A-GBAAB Removal of Fastener from the upper fuselage shell between FR80 and FR86 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Fig. A-GBEAA Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking Sheet 01 Sheet 02

CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 92 6

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# @A330 SERVICE BULLETIN (a) Check the edge clearance of all existing fastener holes from the outside and from the inside of the fuselage shell, as shown on Fig. A-GBAAB Sheet 01 , Fig. AGBAAB Sheet 02 and Fig. A-GBAAB Sheet 04. If the edge clearance is very close for the current fasteners, try to rework the fastener holes to keep the minimum distance to the structure edge after re-drilling to the final fastener hole diameter as shown on Fig. A-GBEAA Sheet 01 and Fig. A-GBEAA Sheet 02. For the correct edge clearance, refer to SRM 51-47-00. Only in the case that the fastener hole can not be moved to keep the correct edge clearance, an undersize fastener of Kit 533160D06R01 should be installed, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE: In accordance with SRM 51-47-00, Edge Distance for Milling Steps, the additional distance of 1.0 mm (0.039 in) to the edge margin for higher milling steps than 1.0 mm is not applicable for these fastener holes. NOTE: The installation of undersize fastener is limited by five fastener per reinforcement bracket with a maximum of two fastener adjacent to each other. NOTE: For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . (5) Subtask 533160-831-208-002 - Install 6 fasteners with cold working in the upper fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH. Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills AIRFRAME Material necessary to do the job Kit 533160D04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 39 EN6115K4Y8 6 BOLT 51 ASNA2528-4 6 NUT Kit 533160D05R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 ASNA2528-5 6 NUT 94 EN6115K5-8 6 BOLT References Structural Repair Manual (SRM) 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 93 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBBAB Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00, Page Block 001 and Fig. AGBCAA Sheet 06

. (b) Drill the fastener holes with the correct start drill, as shown on Fig. A-GBCAA Sheet 07

. (c) Ream the fastener holes with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07

. (d) Expand the fastener holes, refer to SRM 51-48-00, Page Block 001). (e) Ream the fastener holes with the correct gage finish reamer, as shown on Fig. AGBCAA Sheet 07

. NOTE: If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables in Figure Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE: For information of oversize fasteners refer to SUBTASK DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 94 6

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# @A330 SERVICE BULLETIN
533160-400-202 002 Oversize fasteners of kit 533160D05R01 . (f) At the FR80 in the upper fuselage install as shown on Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02, View C and Fig. A-GBCAA Sheet 07: 6 Bolt EN6115K4Y8 Item 39 6 Nut ASNA2528-4 Item 51 or next oversize (part of Kit 533160D05R01) 6 Bolt EN6115K5-8 Item 94 6 Nut ASNA2528-5 Item 52

(6) Subtask 533160-831-209-002 - Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR86. Manpower Resources Manhours 38.00 Minimum number of person 3 Subtask elapsed time 12.50 Skills AIRFRAME Material necessary to do the job Kit 533160D04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 F5357716920000 1 DOUBLER 2 F5357716920100 1 DOUBLER 3 F5357716920400 1 DOUBLER 4 F5357716920500 1 DOUBLER 5 F5357798920400 1 SHIM 6 F5357798920500 1 SHIM 7 F5357798920600 1 SHIM 8 F5357798920700 1 SHIM 9 A5398525620600 1 ANGLE 18 DAN5-5-4 2 PIN 19 DAN5-6-3 12 PIN 20 DAN5-6-4 6 PIN 21 DAN5-6-5 12 PIN 22 DAN5-6-6 22 PIN 24 DAN5-6-8 10 PIN 26 DAN7-8-9 8 PIN 27 DAN7-8-10 4 PIN 28 DAN7-8-11 8 PIN 29 DAN7-10-11 8 PIN 30 DAN7-10-12 6 PIN
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 95 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 31 DAN7-10-17 4 PIN 38 EN6115K4Y7 16 BOLT 40 EN6115K4Y10 4 BOLT 41 EN6115K4Y11 4 BOLT 42 EN6115K4Y12 14 BOLT 45 NSA5075-5 2 COLLAR 46 NSA5075-6 62 COLLAR 48 DAN12-8 18 COLLAR 49 DAN12-10 18 COLLAR 50 ASNA2528-3 32 NUT 51 ASNA2528-4 38 NUT 52 ASNA2528-5 40 NUT 53 NSA5330-6 6 COLLAR 54 DAN12-8Y 10 COLLAR 57 DAN5-6-7Y 2 PIN 58 DAN5-6-8Y 4 PIN 60 DAN7-8-10Y 4 PIN 61 DAN7-8-11Y 4 PIN 62 DAN7-8-12Y 2 PIN 63 EN6115K3-3 12 BOLT 64 EN6115K3-4 10 BOLT 65 EN6115K3-5 10 BOLT 68 EN6115K5-10 8 BOLT 69 EN6115K5-11 8 BOLT 70 EN6115K5-12 8 BOLT 71 EN6115K5-17 8 BOLT 72 EN6115K5-19 8 BOLT 75 EN6080D5-06 1 RIVET 76 LN9198-4812CF 2 RIVET 77 EN6081D6-08 2 RIVET 124 EN6115K3A7 2 BOLT 126 ASNA2528-3A 2 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required References Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801 Elec. Std. Practices Manual (ESPM) 20-51-20

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 96 6

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# @A330 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-47-00 51-48-00 51-48-00, Page Block 001 Fig. A-GBBAB Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B L/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 5 and the doubler, item 1 to the fuselage structure. 2 Countersink (100 DEG) the rivet hole, previously used to fit the angle, item (132), as shown on Fig. A-GBBAB Sheet 03

.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 97 6

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# @A330 SERVICE BULLETIN
3 Close one rivet hole, previously used to fit the angle, item (132), as shown on Fig. A-GBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet 06 with 1 Rivet EN6080D5-06 Item 75 NOTE: Install the rivet, item 75, with 09-005 sealant. 4 Put the shim, item 5 and the doubler, item 1 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 03

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 5 Transfer drill the pilot holes from the shim, item 5 and from the doubler, item 1 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 6 Transfer drill the fastener holes from the fuselage structure to the doubler, item 1 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 7 Mark the fastener holes with a soft felt pen which have to be expand by cold working, as shown on Fig. A-GBBAB Sheet 04

. 8 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 9 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 10 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 11 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 98 6

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# @A330 SERVICE BULLETIN
12 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 13 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thruFig. A-GBCAA Sheet 10

. 14 Put the angle, item 9, in position, as shown on Fig. A-GBBAB Sheet 03

. 15 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thruFig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 16 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 17 Remove the angle, item 9, from the fuselage skin. 18 Remove the doubler, item 1 and the shim, item 5 from the fuselage structure. 19 Deburr the fastener holes. 20 Clean the shim, item 5, the doubler, item 1 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 21 sealant 09-005 As required 1 Doubler F5357716920000 Item 1 1 Shim F5357798920400 Item 5 with: sealant 09-005 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 99 6

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# @A330 SERVICE BULLETIN
22 Put in position, with sealant 09-005 As required and secure with screw pins, as shown on Fig. A-GBBAB Sheet 03 : 1 Angle A5398525620600 Item 9 23 To the fuselage skin, the doubler, item 1 and the shim, item 5, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 2 Pin DAN5-5-4 Item 18 1 Pin DAN5-6-3 Item 19 2 Pin DAN5-6-4 Item 20 2 Pin DAN5-6-5 Item 21 4 Pin DAN5-6-6 Item 22 2 Pin DAN5-6-8 Item 24 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 2 Pin DAN7-8-11 Item 28 2 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 100 6

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# @A330 SERVICE BULLETIN
4 Pin DAN7-10-11 Item 29 3 Pin DAN7-10-12 Item 30 2 Pin DAN7-10-17 Item 31 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN5-6-7Y Item 57 2 Pin DAN5-6-8Y Item 58 2 Pin DAN7-8-10Y Item 60 2 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 3 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Bolt EN6115K4Y12 Item 42 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 2 Bolt EN6115K3-3 Item 63 2 Bolt EN6115K3-4 Item 64 2 Bolt EN6115K3-5 Item 65 1 Bolt EN6115K3A7 Item 124 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-17 Item 71 with 4 Nut ASNA2528-5 Item 52 13 Nut ASNA2528-4 Item 51 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 101 6

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# @A330 SERVICE BULLETIN
6 Nut ASNA2528-3 Item 50 5 Collar DAN12-8Y Item 54 11 Collar NSA5075-6 Item 46 3 Collar NSA5330-6 Item 53 2 Collar NSA5075-5 Item 45 4 Collar DAN12-8 Item 48 9 Collar DAN12-10 Item 49 1 nut ASNA2528-3A Item 126 24 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 6 and the doubler, item 2 to the fuselage structure. 2 Put the shim, item 6 and the doubler, item 2 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 05

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 6 and from the doubler, item 2 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 102 6

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# @A330 SERVICE BULLETIN
4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 2 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 5 Mark the fastener holes with a soft felt pen which have to be expand by cold working, as shown on Fig. A-GBBAB Sheet 06

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 103 6

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# @A330 SERVICE BULLETIN
13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. 14 Remove the doubler, item 2 and the shim, item 6 from the fuselage structure. 15 Deburr the fastener holes. 16 Clean the shim, item 6, the doubler, item 2 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 05: 1 Doubler F5357716920100 Item 2 1 Shim F5357798920500 Item 6 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 2 and the shim, item 6, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 3 Pin DAN5-6-3 Item 19 2 Pin DAN5-6-4 Item 20 2 Pin DAN5-6-5 Item 21 4 Pin DAN5-6-6 Item 22
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 104 6

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# @A330 SERVICE BULLETIN
2 Pin DAN5-6-8 Item 24 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 1 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 2 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 4 Pin DAN7-10-11 Item 29 3 Pin DAN7-10-12 Item 30 2 Pin DAN7-10-17 Item 31 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN5-6-7Y Item 57 2 Pin DAN5-6-8Y Item 58 2 Pin DAN7-8-10Y Item 60 2 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 3 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Bolt EN6115K4Y12 Item 42 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 2 Bolt EN6115K3-3 Item 63 2 Bolt EN6115K3-4 Item 64
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 105 6

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# @A330 SERVICE BULLETIN
2 Bolt EN6115K3-5 Item 65 1 Bolt EN6115K3A7 Item 124 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-17 Item 71 with 4 Nut ASNA2528-5 Item 52 13 Nut ASNA2528-4 Item 51 6 Nut ASNA2528-3 Item 50 5 Collar DAN12-8Y Item 54 13 Collar NSA5075-6 Item 46 3 Collar NSA5330-6 Item 53 4 Collar DAN12-8 Item 48 9 Collar DAN12-10 Item 49 1 nut ASNA2528-3A Item 126 19 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (c) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A L/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 7 and the doubler, item 3 to the fuselage structure. 2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAB Sheet 07, View J.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 106 6

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# @A330 SERVICE BULLETIN
3 Drill with a 4.8 mm (0.19 in.) DIA drill the new hole with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole. 5 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 6 Install to the mating surfaces install, as shown on Fig. A-GBBAB Sheet 07, Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 06: 1 angle F53577990000 Item (131) 1 Rivet LN9198-4812CF Item 76 1 Rivet EN6081D6-08 Item 77 with: sealant 09-005 As required

NOTE: Install the angle, item (131), as electrical bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 7 and the doubler, item 3 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 07

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Transfer drill the pilot holes from the shim, item 7 and from the doubler, item 3 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 3 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 08

. 11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 107 6

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# @A330 SERVICE BULLETIN
12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002 to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to maximum of 16 mm (0.63 in) on the doubler, item 3 located at FR86, as shown on Fig. A-GBBAB Sheet 08

. 20 Remove the doubler, item 3 and the shim, item 7 from the fuselage structure. 21 Deburr the fastener holes. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 108 6

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# @A330 SERVICE BULLETIN
22 Clean the shim, item 7, the doubler, item 3 and the fuselage structure with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins, as shown on Fig. A-GBBAB Sheet 07: 1 Doubler F5357716920400 Item 3 1 Shim F5357798920600 Item 7 with: sealant 09-005 As required

24 To the fuselage skin, the doubler, item 3 and the shim, item 7, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 4 Pin DAN5-6-3 Item 19 1 Pin DAN5-6-4 Item 20 4 Pin DAN5-6-5 Item 21 7 Pin DAN5-6-6 Item 22 3 Pin DAN5-6-8 Item 24 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 3 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 109 6

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# @A330 SERVICE BULLETIN
1 Pin DAN7-8-11 Item 28 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 5 Bolt EN6115K4Y7 Item 38 1 Bolt EN6115K4Y12 Item 42 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 4 Bolt EN6115K3-3 Item 63 3 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-10 Item 68 4 Bolt EN6115K5-11 Item 69 4 Bolt EN6115K5-12 Item 70 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 10

. 4 Bolt EN6115K5-19 Item 72 with 19 Collar NSA5075-6 Item 46 5 Collar DAN12-8 Item 48 10 Nut ASNA2528-3 Item 50 6 Nut ASNA2528-4 Item 51 16 Nut ASNA2528-5 Item 52 25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 110 6

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# @A330 SERVICE BULLETIN (d) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 8 and the doubler, item 4 to the fuselage structure. 2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAB Sheet 07, View J. 3 Drill with a 4.8 (0.19 in.) mm DIA drill the new hole with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole. 5 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 6 Install to the mating surfaces, as shown on Fig. A-GBBAB Sheet 07, Fig. AGBBAB Sheet 08 and Fig. A-GBCAA Sheet 06: 1 angle F53577990000 Item (131) 1 Rivet LN9198-4812CF Item 76 1 Rivet EN6081D6-08 Item 77 with: sealant 09-005 As required

NOTE: Install the angle, item (131) as electrical bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 8 and the doubler, item 4 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 07

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Transfer drill the pilot holes from the shim, item 8 and from the doubler, item 4 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 111 6

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# @A330 SERVICE BULLETIN
9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 4 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 08

. 11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002 to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 112 6

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# @A330 SERVICE BULLETIN
18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to maximum of 16 mm (0.63 in) on the doubler, item 4 located at FR86, as shown on Fig. A-GBBAB Sheet 08

. 20 Remove the shim, item 8 and the doubler, item 4 from the fuselage structure. 21 Deburr the fastener holes. 22 Clean the shim, item 8, the doubler, item 4 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins , as shown on Fig. A-GBBAB Sheet 07: 1 Doubler F5357716920500 Item 4 1 Shim F5357798920700 Item 8 with: sealant 09-005 As required

24 To the fuselage skin, the doubler, item 4 and the shim, item 8, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 4 Pin DAN5-6-3 Item 19 1 Pin DAN5-6-4 Item 20
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 113 6

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# @A330 SERVICE BULLETIN
4 Pin DAN5-6-5 Item 21 7 Pin DAN5-6-6 Item 22 3 Pin DAN5-6-8 Item 24 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 3 Pin DAN7-8-9 Item 26 1 Pin DAN7-8-10 Item 27 1 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 5 Bolt EN6115K4Y7 Item 38 1 Bolt EN6115K4Y12 Item 42 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 4 Bolt EN6115K3-3 Item 63 3 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 09

. 4 Bolt EN6115K5-10 Item 68 4 Bolt EN6115K5-11 Item 69 4 Bolt EN6115K5-12 Item 70 NOTE: For the following fasteners, as shown onFig. A-GBCAA Sheet 10

. 4 Bolt EN6115K5-19 Item 72 with 19 Collar NSA5075-6 Item 46 5 Collar DAN12-8 Item 48 10 Nut ASNA2528-3 Item 50 6 Nut ASNA2528-4 Item 51 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 114 6

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# @A330 SERVICE BULLETIN
16 Nut ASNA2528-5 Item 52 25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (7) Subtask 533160-831-210-002 - Install reinforcement doublers and shims with cold working on the upper fuselage shell at FR84. Manpower Resources Manhours 33.00 Minimum number of person 3 Subtask elapsed time 10.50 Skills AIRFRAME Material necessary to do the job Kit 533160D04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 10 F5357716921800 1 DOUBLER 11 F5357716921900 1 DOUBLER 12 F5357716922100 1 DOUBLER 13 F5357716922000 1 DOUBLER 14 F5357798921200 1 SHIM 15 F5357798921400 1 SHIM 16 F5357798921700 1 SHIM 17 F5357798921600 1 SHIM 23 DAN5-6-7 8 PIN 24 DAN5-6-8 6 PIN 25 DAN5-6-10 8 PIN 28 DAN7-8-11 6 PIN 32 DAN5-6-7X 4 PIN 33 DAN5-6-10X 4 PIN 34 DAN7-6-11Y 2 PIN 35 DAN7-8-13Y 6 PIN 36 DAN7-8-15Y 6 PIN 37 DAN7-8-16Y 6 PIN 43 EN6115K4Y15 2 BOLT 44 EN6115K4Y16 2 BOLT 46 NSA5075-6 22 COLLAR 47 DAN12-6Y 2 COLLAR 48 DAN12-8 6 COLLAR 50 ASNA2528-3 34 NUT 51 ASNA2528-4 4 NUT DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 115 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 54 DAN12-8Y 62 COLLAR 55 DAN12-8X 2 COLLAR 56 DAN11-6X 8 COLLAR 59 DAN7-8-12X 2 PIN 60 DAN7-8-10Y 16 PIN 61 DAN7-8-11Y 16 PIN 62 DAN7-8-12Y 12 PIN 64 EN6115K3-4 4 BOLT 65 EN6115K3-5 12 BOLT 66 EN6115K3-7 10 BOLT 67 EN6115K3-8 8 BOLT 73 LN9198-4012CF 1 RIVET 74 LN9198-4014CF 1 RIVET 77 EN6081D6-08 4 RIVET 125 EN6115K3A8 2 BOLT 126 ASNA2528-3A 2 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required References Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801 Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001 Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 116 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBBAB Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A L/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 10 and the doubler, item 14 to the fuselage structure. 2 Mark the new holes for the angles, item (130) and (131), as shown on Fig. AGBBAB Sheet 09, View N. 3 Drill with a 4.1 mm (0.16 in.) DIA drill the new holes with the angle, item (130). 4 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131). 5 Remove the angles, item (130) and (131) from the fuselage skin and deburr the rivet holes. 6 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 7 Install to the mating surfaces install, as shown on Fig. A-GBBAB Sheet 09, Fig. A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 06: 1 angle A5398525620600 Item (130) DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 117 6

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# @A330 SERVICE BULLETIN 1 angle F5357799000000 Item (131) 1 Rivet LN9198-4012CF Item 73 1 Rivet LN9198-4014CF Item 74 2 Rivet EN6081D6-08 Item 77 with: sealant 09-005 As required

NOTE: Install the angle, item (131) , as bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 8 Put the shim, item 14 and the doubler, item 10 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 09

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the pilot holes from the shim, item 14 and from the doubler, item 10 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 10 Transfer drill the fastener holes from the fuselage structure to the doubler, 10 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 11 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 10

. 12 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 13 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 .

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 118 6

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# @A330 SERVICE BULLETIN
CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 14 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 16 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 17 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 18 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 19 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 20 Remove the doubler, item 10 and the shim, item 14 from the fuselage structure. 21 Deburr the fastener holes. 22 Clean the shim, item 14, the doubler, item 10 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 23 Install with screw pins, as shown on Fig. A-GBBAB Sheet 09 : 1 Doubler F5357716921800 Item 10 1 Shim F5357798921200 Item 14
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 119 6

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# @A330 SERVICE BULLETIN
with: sealant 09-005 As required

24 To the fuselage skin, the doubler, item 10 and the shim, item 14, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-7 Item 23 2 Pin DAN5-6-8 Item 24 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 1 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 2 Pin DAN5-6-7X Item 32 1 Pin DAN5-6-10X Item 33 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 1 Pin DAN7-6-11Y Item 34 3 Pin DAN7-8-15Y Item 36 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 4 Pin DAN7-8-10Y Item 60

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 120 6

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# @A330 SERVICE BULLETIN
4 Pin DAN7-8-11Y Item 61 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 5 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y15 Item 43 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 3 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 with 5 Collar NSA5075-6 Item 46 1 Collar DAN12-6Y Item 47 1 Collar DAN12-8 Item 48 9 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 16 Collar DAN12-8Y Item 54 3 Collar DAN11-6X Item 56 25 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A R/H. 1 Clean the working area with cleaning agent 11-026 As required
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 121 6

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# @A330 SERVICE BULLETIN
and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 11 and the doubler, item 15 to the fuselage structure. 2 Mark the new holes for the angle, item (131), as shown on Fig. A-GBBAB Sheet 11 , View R. 3 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131). 4 Remove the angle, item (131) from the fuselage skin and deburr the rivet holes. 5 Remove the surface protection around the rivet holes of the angle, item (131), for electrical bonding. 6 Install to the mating surfaces, as shown on Fig. A-GBBAB Sheet 11 , Fig. AGBBAB Sheet 12 and Fig. A-GBCAA Sheet 06: 1 angle F5357799000000 Item (131) 2 Rivet EN6081D6-08 Item 77 with: sealant 09-005 As required NOTE : Install the angle, item (131), as electrical bonding point, refer to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801. 7 Put the shim, item 15 and the doubler, item 11 in the final position on the fuselage structure as shown on Fig. A-GBBAB Sheet 11

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Transfer drill the pilot holes from the shim, item 15 and from the doubler, item 11 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 9 Transfer drill the fastener holes from the fuselage structure to the doubler, item 11 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 10 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 12

.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 122 6

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# @A330 SERVICE BULLETIN
11 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. 12 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 14 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 15 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 16 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 17 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 19 Remove the doubler, item 11 and the shim, item 15 from the fuselage structure. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 123 6

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# @A330 SERVICE BULLETIN
20 Deburr the fastener holes. 21 Clean the shim, item 15, the doubler, item 11 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required 22 Install with screw pins, as shown on Fig. A-GBBAB Sheet 11 : 1 Doubler F5357716921900 Item 11 1 Shim F5357798921400 Item 15 with: sealant 09-005 As required

23 To the fuselage skin, the doubler, item 11 and the shim, item 15, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-7 Item 23 2 Pin DAN5-6-8 Item 24 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 1 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 124 6

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# @A330 SERVICE BULLETIN
2 Pin DAN5-6-7X Item 32 1 Pin DAN5-6-10X Item 33 NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 1 Pin DAN7-6-11Y Item 34 3 Pin DAN7-8-15Y Item 36 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 5 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y15 Item 43 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 3 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 with 5 Collar NSA5075-6 Item 46 1 Collar DAN12-6Y Item 47 1 Collar DAN12-8 Item 48 9 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 16 Collar DAN12-8Y Item 54 3 Collar DAN11-6X Item 56 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 125 6

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# @A330 SERVICE BULLETIN
24 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (c) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A L/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 17 and the doubler, item 13 to the fuselage structure. 2 Put the shim, item 17 and the doubler, item 13 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 13

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 17 and from the doubler, item 13 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 13 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 5 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 14

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 126 6

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# @A330 SERVICE BULLETIN
7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 06

. 14 Remove the doubler, item 13 and the shim, item 17 from the fuselage structure. 15 Deburr the fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 127 6

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# @A330 SERVICE BULLETIN
16 Clean the shim, item 17, the doubler, item 13 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 13 : 1 Doubler F5357716922000 Item 13 1 Shim F5357798921600 Item 17 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 13 and the shim, item 17, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-8 Item 24 3 Pin DAN5-6-7 Item 23 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 2 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 1 Pin DAN5-6-10X Item 33

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 128 6

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# @A330 SERVICE BULLETIN
NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 3 Pin DAN7-8-16Y Item 37 3 Pin DAN7-8-13Y Item 35 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN7-8-12X Item 59 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y16 Item 44 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 2 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 1 Bolt EN6115K3A8 Item 125 with 6 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48 8 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 15 Collar DAN12-8Y Item 54 1 Collar DAN12-8X Item 55 1 Collar DAN11-6X Item 56 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 129 6

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# @A330 SERVICE BULLETIN
1 nut ASNA2528-3A Item 126 19 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (d) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required and remove parts of sealant from the structure corners to get a perfect fit of the shim, item 12 and the doubler, item 16 to the fuselage structure. 2 Put the shim, item 12 and the doubler, item 16 in the final position on the fuselage structure, as shown on Fig. A-GBBAB Sheet 13

. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Transfer drill the pilot holes from the shim, item 16 and from the doubler, item 12 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 4 Transfer drill the fastener holes from the fuselage structure to the doubler, item 12 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush. 5 Mark the fastener holes which have to be expand by cold working with a soft felt pen, as shown on Fig. A-GBBAB Sheet 14

. 6 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 130 6

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# @A330 SERVICE BULLETIN
7 Check the edge clearance of the fastener holes as described in Subtask 533160-831-207-002, to define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 8 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 9 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 10 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 11 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 12 Check the edge clearance of the unmarked fastener holes and define the correct fastener dimension, refer to SRM 51-47-00. If the minimum edge clearance is not given to the standard fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

. NOTE : For information of undersize fasteners, refer to SUBTASK 533160-400-201 002 Installation of undersize fasteners of kit 533160D06R01 . CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 05

. 14 Remove the doubler, item 12 and the shim, item 16 from the fuselage structure. 15 Deburr the fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 131 6

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# @A330 SERVICE BULLETIN
16 Clean the shim, item 16, the doubler, item 12 and the fuselage structure with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 13 : 1 Doubler F5357716922100 Item 12 1 Shim F5357798921700 Item 16 with: sealant 09-005 As required

18 To the fuselage skin, the doubler, item 12 and the shim, item 16, install with sealant 09-005 As required as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of Kit 533160D05R01. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 01

. 1 Pin DAN5-6-8 Item 24 3 Pin DAN5-6-7 Item 23 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 02

. 2 Pin DAN5-6-10 Item 25 2 Pin DAN7-8-11 Item 28 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 03

. 1 Pin DAN5-6-10X Item 33

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 132 6

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# @A330 SERVICE BULLETIN
NOTE : For the following fasteners, as shown on Fig. A-GBCAA Sheet 04

. 3 Pin DAN7-8-16Y Item 37 3 Pin DAN7-8-13Y Item 35 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 05

. 1 Pin DAN7-8-12X Item 59 4 Pin DAN7-8-10Y Item 60 4 Pin DAN7-8-11Y Item 61 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 06

. 1 Pin DAN7-8-12Y Item 62 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 07

. 1 Bolt EN6115K4Y16 Item 44 NOTE: For the following fasteners, as shown on Fig. A-GBCAA Sheet 08

. 1 Bolt EN6115K3-4 Item 64 3 Bolt EN6115K3-5 Item 65 2 Bolt EN6115K3-7 Item 66 2 Bolt EN6115K3-8 Item 67 1 Bolt EN6115K3A8 Item 125 with 6 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48 8 Nut ASNA2528-3 Item 50 1 Nut ASNA2528-4 Item 51 15 Collar DAN12-8Y Item 54 1 Collar DAN12-8X Item 55 1 Collar DAN11-6X Item 56 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 133 6

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# @A330 SERVICE BULLETIN
1 nut ASNA2528-3A Item 126 19 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (8) Subtask 533160-831-211-002 - Install fasteners with cold working in the upper fuselage skin at FR85 Manpower Resources Manhours 2.25 Minimum number of person 2 Subtask elapsed time 1.25 Skills AIRFRAME Material necessary to do the job Kit 533160D04R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 38 EN6115K4Y7 4 BOLT 40 EN6115K4Y10 4 BOLT 41 EN6115K4Y11 4 BOLT 51 ASNA2528-4 12 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-005 As required cleaning agent 11-026 As required lint-free cloth 19-003 As required References Elec. Std. Practices Manual (ESPM) 20-51-20 Structural Repair Manual (SRM) 51-47-00 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 134 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Fig. A-GBBAB Installation of Reinforcement Brackets and new Fastener with Cold Working Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 Sheet 15 CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. (a) Install the fasteners with cold working at FR85 between STGR2B L/H and STGR5A L/H. 1 Clean the working area with: cleaning agent 11-026 As required

2 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 4 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 135 6

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# @A330 SERVICE BULLETIN
5 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 6 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 7 Deburr the fastener holes. 8 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required

9 Install the fastener with sealant 09-005 As required , as shown on Fig. A-GBBAB Sheet 15 and Fig. A-GBCAA Sheet 07: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. 2 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Nut ASNA2528-4 Item 51 10 Clean the repair area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required (b) Install the fasteners with cold working at FR85 between STGR2B R/H and STGR5A R/H. 1 Clean the working area with cleaning agent 11-026 As required
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 136 6

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# @A330 SERVICE BULLETIN
2 Measure the size of the fastener holes and define the next stage of drill hole diameter in accordance with the SRM 51-48-00 Page Block 001 for cold working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all fastener holes. CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL HOLE. 3 Drill the marked fastener holes for cold working with the correct start drill, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 4 Ream the marked fastener holes for cold working with the correct start reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 5 Expand the marked fastener holes in accordance with the SRM 51-48-00 Page Block 001. 6 Ream the marked fastener holes with the correct gage finish reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10

. 7 Deburr the fastener holes. 8 Clean the repair area with: cleaning agent 11-026 As required and lint-free cloth 19-003 As required

9 Install the fastener with sealant 09-005 As required , as shown on Fig. A-GBBAB Sheet 15 and Fig. A-GBCAA Sheet 07: NOTE : If the following fasteners do not fit and oversize fasteners are necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar. NOTE : For information of oversize fasteners refer to SUBTASK 533160-400-202 002 Oversize fasteners of kit 533160D05R01

. 2 Bolt EN6115K4Y7 Item 38 2 Bolt EN6115K4Y10 Item 40 2 Bolt EN6115K4Y11 Item 41 6 Nut ASNA2528-4 Item 51
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 137 6

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# @A330 SERVICE BULLETIN
10 Clean the repair area with cleaning agent 11-026 As required and lint-free cloth 19-003 As required (9) Subtask 533160-831-212-002 - Apply surface protection to the modification area. Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES sealant 09-013 As required sealant 09-016 As required corrosion preventive 15-005 As required polyurethane primer 16-001 As required polyurethane top coat 16-018 As required wash primer 16-020 As required CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA. Apply surface protection to the modification area. (a) Apply sealant 09-013 As required

or sealant 09-016 As required

to form a bead around the new doubler and reinstalled angles. (b) Apply wash primer 16-020 As required

to all reworked edges and heads of fasteners.
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 138 6

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# @A330 SERVICE BULLETIN (c) Apply polyurethane primer 16-001 As required

to all reworked edges and heads of fasteners. (d) Apply polyurethane top coat 16-018 As required

to all reworked edges and heads of fasteners. (e) Apply corrosion preventive 15-005 As required

to the modification area inside the fuselage. (10) Subtask 533160-400-201-002 - Installation of undersize fasteners of kit 533160D06R01 Manpower Resources Manhours 0.00 Minimum number of person 0 Subtask elapsed time 0.00 Skills NON SPECIFIC Material necessary to do the job Kit 533160D06R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 32 DAN5-6-7X 2 PIN 34 DAN7-6-11Y 5 PIN 40 EN6115K4Y10 5 BOLT 41 EN6115K4Y11 5 BOLT 42 EN6115K4Y12 5 BOLT 47 DAN12-6Y 5 COLLAR 51 ASNA2528-4 5 NUT 54 DAN12-8Y 5 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 4 COLLAR 59 DAN7-8-12X 5 PIN 61 DAN7-8-11Y 5 PIN 62 DAN7-8-12Y 5 PIN 82 DAN5-6-8X 4 PIN 84 DAN7-8-10X 5 PIN 85 DAN7-8-11X 5 PIN 114 DAN7-6-9Y 5 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 139 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 115 DAN7-6-10Y 2 PIN 116 DAN7-8-17Y 4 PIN 117 DAN7-6-11X 2 PIN 118 DAN7-8-13X 5 PIN 119 DAN7-8-15X 5 PIN 120 DAN7-8-16X 5 PIN 121 DAN12-6X 2 COLLAR 122 EN6115K4Y17 5 BOLT 123 EN6115K4Y19 5 BOLT References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) The subsequent undersize fasteners are parts of Kit 533160D06R01. NOTE: Depending of the edge margin measurement requested with subtask 533160-831-207-002 undersize fasteners can be installed. Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 NOTE: The installation of undersize fasteners is limited by five fasteners per reinforcement bracket with a maximum of two fasteners adjacent to each other. If it is not the case, contact AIRBUS. 2 Pin DAN5-6-7X Item 32 5 Pin DAN7-6-11Y Item 34 5 Bolt EN6115K4Y10 Item 40 5 Bolt EN6115K4Y11 Item 41 5 Bolt EN6115K4Y12 Item 42 5 Collar DAN12-6Y Item 47 5 Nut ASNA2528-4 Item 51 5 Collar DAN12-8Y Item 54 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 140 6

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# @A330 SERVICE BULLETIN
5 Collar DAN12-8X Item 55 4 Collar DAN11-6X Item 56 5 Pin DAN7-8-12X Item 59 5 Pin DAN7-8-11Y Item 61 5 Pin DAN7-8-12Y Item 62 4 Pin DAN5-6-8X Item 82 5 Pin DAN7-8-10X Item 84 5 Pin DAN7-8-11X Item 85 5 Pin DAN7-6-9Y Item 114 2 Pin DAN7-6-10Y Item 115 4 Pin DAN7-8-17Y Item 116 2 Pin DAN7-6-11X Item 117 5 Pin DAN7-8-13X Item 118 5 Pin DAN7-8-15X Item 119 5 Pin DAN7-8-16X Item 120 2 Collar DAN12-6X Item 121 5 Bolt EN6115K4Y17 Item 122 5 Bolt EN6115K4Y19 Item 123

(11) Subtask 533160-400-202-002 - Oversize fasteners of kit 533160D05R01 Manpower Resources Manhours 0.00 Minimum number of person 0 Subtask elapsed time 0.00 Skills NON SPECIFIC Material necessary to do the job Kit 533160D05R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 20 DAN5-6-4 2 PIN DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 141 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 28 DAN7-8-11 2 PIN 29 DAN7-10-11 5 PIN 30 DAN7-10-12 5 PIN 32 DAN5-6-7X 5 PIN 33 DAN5-6-10X 5 PIN 46 NSA5075-6 2 COLLAR 48 DAN12-8 2 COLLAR 49 DAN12-10 5 COLLAR 50 ASNA2528-3 5 NUT 51 ASNA2528-4 4 NUT 52 ASNA2528-5 4 NUT 53 NSA5330-6 5 COLLAR 54 DAN12-8Y 2 COLLAR 55 DAN12-8X 5 COLLAR 56 DAN11-6X 5 COLLAR 57 DAN5-6-7Y 4 PIN 62 DAN7-8-12Y 2 PIN 68 EN6115K5-10 5 BOLT 69 EN6115K5-11 5 BOLT 70 EN6115K5-12 5 BOLT 78 DAN5-6-3X 5 PIN 79 DAN5-6-4X 4 PIN 80 DAN5-6-5X 5 PIN 81 DAN5-6-6X 5 PIN 82 DAN5-6-8X 5 PIN 83 DAN7-8-9X 5 PIN 84 DAN7-8-10X 4 PIN 85 DAN7-8-11X 5 PIN 86 DAN7-10-11X 5 PIN 87 DAN7-10-12X 5 PIN 88 DAN7-10-17X 4 PIN 89 DAN5-6-10Y 4 PIN 90 DAN7-10-13 5 PIN 91 DAN7-10-15 5 PIN 92 DAN7-10-16 5 PIN 93 EN6115K5-7 5 BOLT 94 EN6115K5-8 BOLT 95 EN6115K5-15 2 BOLT 96 EN6115K5-16 2 BOLT 97 DAN12-10X 5 COLLAR 98 NSA5075-8 5 COLLAR 99 DAN5-8-7 2 PIN 100 DAN5-8-8 4 PIN 101 DAN7-10-10 5 PIN 102 EN6115K3X3 5 BOLT 103 EN6115K3X4 5 BOLT DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 142 6

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# @A330 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 104 EN6115K3X5 5 BOLT 105 EN6115K4-7 2 BOLT 106 EN6115K3X7 5 BOLT 107 EN6115K3X8 5 BOLT 108 EN6115K4-8 2 BOLT 109 EN6115K5X10 5 BOLT 110 EN6115K5X11 5 BOLT 111 EN6115K5X12 5 BOLT 112 EN6115K5X17 5 BOLT 113 EN6115K5X19 5 BOLT References Fig. A-GBCAA Fastener Table Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 (a) If fasteners of Kit 533160D04R01 do not fit because oversize fasteners are necessary, then refer to the fastener tables, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut or collar which is part of kit Kit 533160D05R01 and listed below: 2 Pin DAN5-6-4 Item 20 2 Pin DAN7-8-11 Item 28 5 Pin DAN7-10-11 Item 29 5 Pin DAN7-10-12 Item 30 5 Pin DAN5-6-7X Item 32 5 Pin DAN5-6-10X Item 33 2 Collar NSA5075-6 Item 46 2 Collar DAN12-8 Item 48 5 Collar DAN12-10 Item 49 5 Nut ASNA2528-3 Item 50 4 Nut ASNA2528-4 Item 51 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 143 6

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# @A330 SERVICE BULLETIN
4 Nut ASNA2528-5 Item 52 5 Collar NSA5330-6 Item 53 2 Collar DAN12-8Y Item 54 5 Collar DAN12-8X Item 55 5 Collar DAN11-6X Item 56 4 Pin DAN5-6-7Y Item 57 2 Pin DAN7-8-12Y Item 62 5 Bolt EN6115K5-10 Item 68 5 Bolt EN6115K5-11 Item 69 5 Bolt EN6115K5-12 Item 70 5 Pin DAN5-6-3X Item 78 4 Pin DAN5-6-4X Item 79 5 Pin DAN5-6-5X Item 80 5 Pin DAN5-6-6X Item 81 5 Pin DAN5-6-8X Item 82 5 Pin DAN7-8-9X Item 83 4 Pin DAN7-8-10X Item 84 5 Pin DAN7-8-11X Item 85 5 Pin DAN7-10-11X Item 86 5 Pin DAN7-10-12X Item 87 4 Pin DAN7-10-17X Item 88 4 Pin DAN5-6-10Y Item 89 5 Pin DAN7-10-13 Item 90 5 Pin DAN7-10-15 Item 91 5 Pin DAN7-10-16 Item 92 5 Bolt EN6115K5-7 Item 93 DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 144 6

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# @A330 SERVICE BULLETIN
5 Bolt EN6115K5-8 Item 94 2 Bolt EN6115K5-15 Item 95 2 Bolt EN6115K5-16 Item 96 5 Collar DAN12-10X Item 97 5 Collar NSA5075-8 Item 98 4 Pin DAN5-8-8 Item 100 2 Pin DAN5-8-7 Item 99 5 Pin DAN7-10-10 Item 101 5 Bolt EN6115K3X3 Item 102 5 Bolt EN6115K3X4 Item 103 5 Bolt EN6115K3X5 Item 104 2 Bolt EN6115K4-7 Item 105 5 Bolt EN6115K3X7 Item 106 5 Bolt EN6115K3X8 Item 107 2 Bolt EN6115K4-8 Item 108 5 Bolt EN6115K5X10 Item 109 5 Bolt EN6115K5X11 Item 110 5 Bolt EN6115K5X12 Item 111 5 Bolt EN6115K5X17 Item 112 5 Bolt EN6115K5X19 Item 113 **CONF ALL D. TEST **CONF 001 None **CONF 002 None
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 145 6

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# @A330 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 533160-831-223-001 - Close-up Manpower Resources Skills AIRFRAME ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301 25-33-48, Page Block 401 25-33-53, Page Block 401 25-33-54, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 36-12-14, Page Block 401 36-22-17, Page Block 401 52-10-00, Page Block 201 55-31-11, Page Block 401 (a) Install the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401). (b) Reinstall the Bleed Air pipe between FR85 and FR87 (Refer to AMM 36-12-14, Page Block 401). (c) Reinstall the Bleed Air pipe sense line between FR85 and FR87 (Refer to AMM 36-22-17, Page Block 401). (d) Install the AFT galley (Refer to AMM 25-33-53, Page Block 401 and AMM 25-33-54, Page Block 401). (e) Install the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401). (f) Make sure that the work areas are clean and clear of tools and other items of equipment. (g) Close the access door 312AR in the REAR fuselage area. (h) Remove the access platform(s) from the aircraft REAR section. (i) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM 29-14-00, Page Block 201). (j) Fill the Green hydraulic tank (Refer to AMM 12-12-29, Page Block 301). (k) Pressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM 29-00-00, Page Block 201).
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 146 6

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# @A330 SERVICE BULLETIN (l) Remove the warning notices : 1 in the cockpit from the hydraulic section 40VU of the overhead panel, 2 on the ground service panel from each hydraulic system. (m) Close the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block 201). (n) Remove the access platform from the passenger/crew doors. **CONF 002 (1) Subtask 533160-831-223-001 - Close-up Manpower Resources Skills AIRFRAME ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301 25-33-48, Page Block 401 25-33-53, Page Block 401 25-33-54, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 36-12-14, Page Block 401 36-22-17, Page Block 401 52-10-00, Page Block 201 55-31-11, Page Block 401 (a) Install the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401). (b) Reinstall the Bleed Air pipe between FR85 and FR87 (Refer to AMM 36-12-14, Page Block 401). (c) Reinstall the Bleed Air pipe sense line between FR85 and FR87 (Refer to AMM 36-22-17, Page Block 401). (d) Install the AFT galley (Refer to AMM 25-33-53, Page Block 401 and AMM 25-33-54, Page Block 401). (e) Install the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401). (f) Make sure that the work areas are clean and clear of tools and other items of equipment. (g) Close the access door 312AR in the REAR fuselage area. (h) Remove the access platform(s) from the aircraft REAR section.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 147 6

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# @A330 SERVICE BULLETIN (i) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM 29-14-00, Page Block 201). (j) Fill the Green hydraulic tank (Refer to AMM 12-12-29, Page Block 301). (k) Pressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM 29-00-00, Page Block 201). (l) Remove the warning notices : 1 in the cockpit from the hydraulic section 40VU of the overhead panel, 2 on the ground service panel from each hydraulic system. (m) Close the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block 201). (n) Remove the access platform from the passenger/crew doors.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 148 6

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

# @A330 SERVICE BULLETIN

**CONF 001 Z310



### B



## A AD Z270 

### A

**C C**  **B** STGR8

STGR8 FR91

FR87

FR79

G_SB_533160_6_BAAA_01_00 Figure A-GBAAA - Sheet 01 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 149 6

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

# @A330 SERVICE BULLETIN

**CONF 001

LH SHOWN RH SYMMETRICAL FASTENERS NOT EFFECTED NOTE: REMOVE AND REUSE REMOVE AND DISCARD LH SIDE ONLY CHECK THESE FASTENER HOLES FOR EDGE CLEARANCE AND REWORK IF POSSIBLE, REFER TO FIGURE 1. AD



## B 01 03 (130)
(131) 01 04

04

01 02 03 04 04

04 02 03

01 (132)

(131) 

### D

**D C** 

**C B**  **B**

**A**

**A** FR84 FR85 FR86

STGR3

STGR6

STGR8

G_SB_533160_6_BAAA_02_00 Figure A-GBAAA - Sheet 02 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 150 6

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

# @A330 SERVICE BULLETIN

**CONF 001

LH SHOWN RH SYMMETRICAL

FASTENERS NOT EFFECTED P/N DESCRIPTION MIN MAX ITEM KIT HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

COLLAR
COLLAR COLLAR NOMINAL SIZE PIN UNI
PIN UNI

PIN UNI NSA5075−6 TRANSITION FIT 4.78mm (0.188in.) 4.78mm (0.188in.) 6.31mm (0.248in.)

4.78mm (0.188in.) 4.06mm (0.160in.) 6.31mm (0.248in.) 6.31mm (0.248in.) 6.31mm (0.248in.) 6.31mm (0.248in.) 4.82mm (0.190in.) 4.82mm (0.190in.) 6.35mm (0.250in.)

4.82mm (0.190in.) D01
D01
D01

D01 DAN5−6−5 NSA5075−6 DAN5−6−7
DAN5−8−7 NSA5075−8

COLLAR PIN UNI D01 DAN5−8−11 NSA5075−8 DAN5−8−14 COLLAR D01 NSA5075−8 4.17mm (0.164in.) D01 NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT LN9198−4000CF LN9198−4800CF RIVET RIVET PIN, UNI

COLLAR PIN UNI D01 NSA5075−8 NOMINAL SIZE TRANSITION FIT

COLLAR PIN UNI D01 DAN5−8−10 NSA5075−8 NOMINAL SIZE TRANSITION FIT DAN5−8−8

NOTE: (36) (54) (37) (54) (38) (51) (39) (51) (40) (51) (41) (51) (42) (51) (43) (44) 6.35mm (0.250in.) 6.35mm (0.250in.) 6.35mm (0.250in.) 6.35mm (0.250in.) 

## C FR80 STGR2A

STGR5A

G_SB_533160_6_BAAA_03_00 Figure A-GBAAA - Sheet 03 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 151 6

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

# @A330 SERVICE BULLETIN

**CONF 001

**NOTE:** ONLY IN CASE OF LESS EDGE CLEARANCE AND NON REWORKABLE DRILL HOLE INSTALL AN UNDERSIZE FASTENER WHICH IS PART OF KIT 533160D03 AND GIVEN IN THE FASTENER TABLE AS ALTERNATIVE. 

### A A **B B**

**D D C C** (0.57in.)(14.5mm)(0.52in.)(13.3mm)(0.52in.)(13.1mm)(0.49in.)(12.4mm)(0.49in.)(12.4mm)(0.51in.)(13.0mm)(0.53in.)(13.4mm)(0.51in.)(13.0mm)

THE GIVEN VALUES ARE FOF INFORMATION ONLY. IF THE MEASURED VALUES ON THE AIRCRAFT ARE SMALLER, REFER TO THE SRM 51−47−00 FOR THE MINIMUM EDGE CLEARANCE.06050605060506050605060506050605

05 06 

## A **A B**  **B**

**C C**  **D D** 

G_SB_533160_6_BAAA_04_00 Figure A-GBAAA - Sheet 04 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 152 6

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

# @A330 SERVICE BULLETIN

**CONF 002 Z310



### B



## A AD Z270 

### A

**C C**  **B** STGR8

STGR8 FR91

FR87

FR79

G_SB_533160_6_BAAB_01_00 Figure A-GBAAB - Sheet 01 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 153 6

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

# @A330 SERVICE BULLETIN

**CONF 002

LH SHOWN RH SYMMETRICAL FASTENERS NOT EFFECTED NOTE: REMOVE AND REUSE REMOVE AND DISCARD LH SIDE ONLY CHECK THESE FASTENER HOLES FOR EDGE CLEARANCE AND REWORK IF POSSIBLE, REFER TO FIGURE 1. AD



## B 01 03 (130)
(131) 01 04

04

01 02 03 04 04

04 02 03

01 (132)

(131) 

### D

**D C** 

**C B**  **B**

**A**

**A**

G_SB_533160_6_BAAB_02_00 FR84 FR85 FR86

STGR3

STGR6

STGR8

Figure A-GBAAB - Sheet 02 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 154 6

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

# @A330 SERVICE BULLETIN

**CONF 002

LH SHOWN RH SYMMETRICAL

FASTENERS NOT EFFECTED P/N DESCRIPTION MIN MAX ITEM KIT HOLE SYMBOL REMARKS
NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT NOMINAL SIZE TRANSITION FIT FINAL HOLE DIAMETER

COLLAR
COLLAR COLLAR PIN UNI
PIN UNI

PIN UNI NSA5075−6 4.78mm (0.188in.) 4.82mm (0.190in.) 4.78mm (0.188in.) 4.82mm (0.190in.) 6.31mm (0.248in.) 6.35mm (0.250in.)

4.78mm (0.188in.) 4.82mm (0.190in.) D04
D04
D04

D04 DAN5−6−5 NSA5075−6 DAN5−6−7
DAN5−8−7 NSA5075−8

COLLAR PIN UNI D04 DAN5−8−11 NSA5075−8 DAN5−8−14 COLLAR D04 NSA5075−8 4.06mm (0.160in.) 4.17mm (0.164in.) D04 LN9198−4000CF LN9198−4800CF RIVET RIVET PIN, UNI

COLLAR PIN UNI D04 NSA5075−8
COLLAR PIN UNI D04 DAN5−8−10 NSA5075−8 DAN5−8−8

NOTE: (36) (54) (37) (54) (38) (51) (39) (51) (40) (51) (41) (51) (42) (51) (43) (44) 6.31mm (0.248in.) 6.35mm (0.250in.) 6.31mm (0.248in.) 6.35mm (0.250in.) 6.31mm (0.248in.) 6.35mm (0.250in.) 6.31mm (0.248in.) 6.35mm (0.250in.) 

## C FR80 STGR2A

STGR5A

G_SB_533160_6_BAAB_03_00 Figure A-GBAAB - Sheet 03 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 155 6

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

# @A330 SERVICE BULLETIN

**CONF 002

**NOTE:** ONLY IN CASE OF LESS EDGE CLEARANCE AND NON REWORKABLE DRILL HOLE INSTALL AN UNDERSIZE FASTENER WHICH IS PART OF KIT 533160D06 AND GIVEN IN THE FASTENER TABLE AS ALTERNATIVE. THE GIVEN VALUES ARE FOF INFORMATION ONLY. IF THE MEASURED VALUES ON THE AIRCRAFT ARE SMALLER, REFER TO THE SRM 51−47−00 FOR THE MINIMUM EDGE CLEARANCE. 05 06 

### A A **B B**

**D D C C** (0.57in.)(14.5mm)(0.52in.)(13.3mm)(0.52in.)(13.1mm)(0.49in.)(12.4mm)(0.49in.)(12.4mm)(0.51in.)(13.0mm)(0.53in.)(13.4mm)(0.51in.)(13.0mm)06050605060506050605060506050605



## A **A B**  **B**

**C C**  **D D** 

G_SB_533160_6_BAAB_04_00 Figure A-GBAAB - Sheet 04 Removal of Fastener from the upper fuselage shell between FR80 and FR86
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 156 6

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

# @A330 SERVICE BULLETIN

**CONF 001
Z310 

### A Z270

FR91



## A FR80 FR84 FR86 

### B

**C C** 

G_SB_533160_6_BBAA_01_00 Figure A-GBBAA - Sheet 01 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 157 6

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

# @A330 SERVICE BULLETIN

**CONF 001

01 FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 

## C LH SHOWN RH SYMMETRICAL

**FWD** AD 

### T **V H** 

**H**
**V**

**T L**  **Q D**  **F**



## B FR87

FR86
FR85

FR84 STGR2A

STGR5A FR80

G_SB_533160_6_BBAA_02_02 Figure A-GBBAA - Sheet 02 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 158 6

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

# @A330 SERVICE BULLETIN

**CONF 001

(3 POS.)

(3 POS.) 1

38

5

51

9 

### E

75



## D LH SHOWN 

### A **A**

75 

## A **A** G_SB_533160_6_BBAA_03_00 STGR2B FR86

Figure A-GBBAA - Sheet 03 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 159 6

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

# @A330 SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. AD

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **F W**  **D**

**NOTE:** 01 01

01



## E LH SHOWN 01 FR86

G_SB_533160_6_BBAA_04_00 STGR2B

Figure A-GBBAA - Sheet 04 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 160 6

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

# @A330 SERVICE BULLETIN

**CONF 001

2

6

51 38 

### G



## F RH SHOWN (3 POS.)

(3 POS.)

FR86 STGR2B

G_SB_533160_6_BBAA_05_00 Figure A-GBBAA - Sheet 05 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 161 6

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

# @A330 SERVICE BULLETIN

**CONF 001

AD **F W**  **D**



## G RH SHOWN

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01 01 01FR86

STGR2B

G_SB_533160_6_BBAA_06_00 Figure A-GBBAA - Sheet 06 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 162 6

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

# @A330 SERVICE BULLETIN

**CONF 001

(5 POS.)

(5 POS.)20.0mm(0.79in.)(0.79in.) 3 LH

RH 4

LH

RH 7 8

76 77 (131)

38

51 

### J **K**



## H

**J**
**FWD** LH SHOWN RH SYMMETRICAL20.0mm FR86 STGR5A

G_SB_533160_6_BBAA_07_00 Figure A-GBBAA - Sheet 07 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 163 6

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

# @A330 SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01

01 **F W**  **D**



## K LH SHOWN RH SYMMETRICAL 

### B **B** 8.0mm (0.31in.) max 16.0mm (0.63in.)

SPOT FACING TOOL 1.6mm (0.06in.)



## B **B**R 1.5mm(0.059in.) STGR5A

STGR5AFR86

G_SB_533160_6_BBAA_08_00 Figure A-GBBAA - Sheet 08 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 164 6

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

# @A330 SERVICE BULLETIN

**CONF 00122.0mm(0.87in.) 22.0mm (0.87in.) (2 POS.) 10

14

77 (131)

(130) 

### P

**N**

73 74



## N **FWD** 

## L LH SHOWN FR84 STGR2A

G_SB_533160_6_BBAA_09_00 Figure A-GBBAA - Sheet 09 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 165 6

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

# @A330 SERVICE BULLETIN

**CONF 001

0.2mm (0.008in.)56.5mm(2.22in.)

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01 **F W**  **D**



## P LH SHOWN FR84

STGR2A

G_SB_533160_6_BBAA_10_00 Figure A-GBBAA - Sheet 10 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 166 6

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

# @A330 SERVICE BULLETIN

**CONF 001

(2 POS.)22.0mm(0.87in.) 11

15

77 (131) 

### S

**R**



## R **FWD** 

## Q RH SHOWN FR84 STGR2A

G_SB_533160_6_BBAA_11_00 Figure A-GBBAA - Sheet 11 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 167 6

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

# @A330 SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 RH SHOWN 

## S 01 0.2mm (0.008in.)56.5mm(2.22in.) **F W**  **D** FR84

STGR2A

G_SB_533160_6_BBAA_12_00 Figure A-GBBAA - Sheet 12 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 168 6

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

# @A330 SERVICE BULLETIN

**CONF 001

LH RH 

### U

13 12

LH RH 17 16



## T LH SHOWN RH SYMMETRICAL FR84 STGR5A

G_SB_533160_6_BBAA_13_00 Figure A-GBBAA - Sheet 13 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 169 6

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

# @A330 SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01



## U LH SHOWN RH SYMMETRICAL **F W**  **D** FR84 STGR2A

G_SB_533160_6_BBAA_14_00 Figure A-GBBAA - Sheet 14 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 170 6

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

# @A330 SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 AD

01

01 01 01



## V LH SHOWN RH SYMMETRICAL **FWD** FR85

G_SB_533160_6_BBAA_15_01 Figure A-GBBAA - Sheet 15 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 171 6

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

# @A330 SERVICE BULLETIN

**CONF 002
Z310 

### A Z270

FR91



## A FR80 FR84 FR86 

### B

**C C** 

G_SB_533160_6_BBAB_01_00 Figure A-GBBAB - Sheet 01 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 172 6

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

# @A330 SERVICE BULLETIN

**CONF 002

01 FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 

## C LH SHOWN RH SYMMETRICAL

**FWD** AD 

### T **V H** 

**H**
**V**

**T L**  **Q D**  **F**



## B FR87

FR86
FR85

FR84 STGR2A

STGR5A FR80

G_SB_533160_6_BBAB_02_02 Figure A-GBBAB - Sheet 02 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 173 6

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

# @A330 SERVICE BULLETIN

**CONF 002

(3 POS.)

(3 POS.) 1

38

5

51

9 

### E

75



## D LH SHOWN 

### A **A**

75 

## A **A** G_SB_533160_6_BBAB_03_00 STGR2B FR86

Figure A-GBBAB - Sheet 03 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 174 6

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

# @A330 SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. AD

POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **F W**  **D**

**NOTE:** 01 01

01



## E LH SHOWN 01 FR86

G_SB_533160_6_BBAB_04_00 STGR2B

Figure A-GBBAB - Sheet 04 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 175 6

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

# @A330 SERVICE BULLETIN

**CONF 002

2

6

51 38 

### G



## F RH SHOWN (3 POS.)

(3 POS.)

FR86 STGR2B

G_SB_533160_6_BBAB_05_00 Figure A-GBBAB - Sheet 05 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 176 6

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

# @A330 SERVICE BULLETIN

**CONF 002

AD **F W**  **D**



## G RH SHOWN

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01 01 01FR86

STGR2B

G_SB_533160_6_BBAB_06_00 Figure A-GBBAB - Sheet 06 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 177 6

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

# @A330 SERVICE BULLETIN

**CONF 002

(5 POS.)

(5 POS.)20.0mm(0.79in.)(0.79in.) 3 LH

RH 4

LH

RH 7 8

76 77 (131)

38

51 

### J **K**



## H

**J**
**FWD** LH SHOWN RH SYMMETRICAL20.0mm FR86 STGR5A

G_SB_533160_6_BBAB_07_00 Figure A-GBBAB - Sheet 07 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 178 6

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

# @A330 SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01

01 **F W**  **D**



## K LH SHOWN RH SYMMETRICAL 8.0mm (0.31in.) max 16.0mm (0.63in.)

SPOT FACING TOOL 1.6mm (0.06in.)



## B **B B**  **B**

STGR5A

STGR5AFR86

G_SB_533160_6_BBAB_08_00R 1.5mm(0.059in.)

Figure A-GBBAB - Sheet 08 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 179 6

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

# @A330 SERVICE BULLETIN

**CONF 00222.0mm(0.87in.) (2 POS.) 10

14

77 (131)

(130) 

### P

**N**

73 74



## N **FWD** 

## L LH SHOWN FR84 STGR2A

G_SB_533160_6_BBAB_09_00 (0.87in.) 22.0mm

Figure A-GBBAB - Sheet 09 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 180 6

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

# @A330 SERVICE BULLETIN

**CONF 002

0.2mm (0.008in.)56.5mm(2.22in.)

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01 **F W**  **D**



## P LH SHOWN FR84

STGR2A

G_SB_533160_6_BBAB_10_00 Figure A-GBBAB - Sheet 10 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 181 6

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

# @A330 SERVICE BULLETIN

**CONF 002

(2 POS.)22.0mm(0.87in.) 11

15

77 (131) 

### S

**R**



## R **FWD** 

## Q RH SHOWN FR84 STGR2A

G_SB_533160_6_BBAB_11_00 Figure A-GBBAB - Sheet 11 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 182 6

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

# @A330 SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 RH SHOWN 

## S 01 0.2mm (0.008in.)56.5mm(2.22in.) **F W**  **D** FR84

STGR2A

G_SB_533160_6_BBAB_12_00 Figure A-GBBAB - Sheet 12 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 183 6

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

# @A330 SERVICE BULLETIN

**CONF 002

LH RH 

### U

13 12

LH RH 17 16



## T LH SHOWN RH SYMMETRICAL FR84 STGR5A

G_SB_533160_6_BBAB_13_00 Figure A-GBBAB - Sheet 13 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 184 6

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

# @A330 SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 01



## U LH SHOWN RH SYMMETRICAL **F W**  **D** FR84 STGR2A

G_SB_533160_6_BBAB_14_00 Figure A-GBBAB - Sheet 14 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 185 6

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

# @A330 SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED. USE EXISTING RIVETHOLES. POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION. **NOTE:** 01 AD

01

01 01 01



## V LH SHOWN RH SYMMETRICAL **FWD** FR85

G_SB_533160_6_BBAB_15_01 Figure A-GBBAB - Sheet 15 Installation of Reinforcement Brackets and new Fastener with Cold Working
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 186 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

COLLAR PIN UNI COLLAR

COLLAR COLLAR

PIN UNI

PIN UNI PIN, UNI

COLLAR PIN UNI COLLAR PIN UNI

PIN UNI COLLAR COLLAR PIN, UNI

COLLAR PIN UNI

COLLAR PIN UNI

COLLAR PIN UNI

COLLAR PIN UNI

COLLAR PIN UNI

PIN UNI COLLAR P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

TRANSITION FIT

TRANSITION FIT

TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT FIRST OVERSIZE
NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE 4.78mm (0.188in.)

4.78mm (0.188in.) 4.78mm (0.188in.)

4.78mm (0.188in.)

4.78mm (0.188in.)

4.78mm (0.188in.) 4.78mm (0.188in.) 4.13mm (0.162in.)

5.11mm (0.201in.)

5.11mm (0.201in.)

5.11mm (0.201in.)

5.11mm (0.201in.)

5.11mm (0.201in.)

5.11mm (0.201in.) 4.82mm (0.190in.)

4.82mm (0.190in.) 4.82mm (0.190in.)

4.82mm (0.190in.)

4.82mm (0.190in.)

4.82mm (0.190in.) 4.82mm (0.190in.) 4.16mm (0.164in.)

5.15mm (0.203in.)

5.15mm (0.203in.)

5.15mm (0.203in.)

5.15mm (0.203in.)

5.15mm (0.203in.)

5.15mm (0.203in.) NSA5075−6 DAN5−6−5

DAN5−6−8 DAN5−5−4 NSA5075−5 DAN5−6−4 NSA5075−6
NSA5075−6 DAN5−6−3

DAN11−6X DAN5−6−3X
DAN5−6−4 NSA5075−6 DAN5−6−4X DAN11−6X

DAN5−6−5X DAN11−6X DAN5−6−6 NSA5075−6 DAN5−6−6X DAN11−6X DAN5−6−7 NSA5075−6 DAN5−6−7X DAN11−6X
NSA5075−6 DAN5−6−8X DAN11−6X 01

01

01

01

01

01

01

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 18 45 20 46 19 46 78 56 20 46 79 56 21 46 80 56 22 46 81 56 23 46 32 56 24 46 82 56

G_SB_533160_6_BCAA_01_00 Figure A-GBCAA - Sheet 01 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 187 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

COLLAR PIN UNI PIN UNI COLLAR TRANSITION FIT
TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT 2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE

NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE

PIN UNI COLLAR COLLAR PIN UNI COLLAR PIN UNI PIN UNI COLLAR 4.78mm (0.188in.) 4.82mm (0.190in.) DAN5−6−10 NSA5075−6

PIN UNI COLLAR DAN5−6−10X DAN11−6X

DAN7−8−10X DAN12−8X

DAN7−8−11X DAN12−8X DAN7−6−9Y DAN12−6Y

COLLAR PIN UNI DAN7−8−10 DAN12−8 DAN7−6−10Y DAN12−6Y

PIN UNI COLLAR DAN7−8−11 DAN12−8 DAN7−6−11Y DAN12−6Y 6.31mm (0.248in.) 6.35mm (0.250in.)

6.31mm (0.248in.) 6.35mm (0.250in.) 5.11mm (0.201in.) 5.15mm (0.203in.) 5.51mm (0.217in.) 5.55mm (0.219in.)

5.51mm (0.217in.) 5.55mm (0.219in.)

5.51mm (0.217in.) 5.55mm (0.219in.) 6.71mm (0.264in.) 6.75mm (0.266in.)

6.71mm (0.264in.) 6.75mm (0.266in.) COLLAR PIN UNI DAN7−8−9X DAN12−8X COLLAR PIN UNI DAN12−8 DAN7−8−9 6.31mm (0.248in.) 6.35mm (0.250in.) 6.71mm (0.264in.) 6.75mm (0.266in.) COLLAR PIN UNI DAN7−8−9X DAN12−8X COLLAR PIN UNI DAN12−8 DAN7−8−9 6.31mm (0.248in.) 6.35mm (0.250in.) 6.71mm (0.264in.) 6.75mm (0.266in.)

COLLAR PIN UNI DAN7−8−10X DAN12−8X COLLAR PIN UNI DAN7−8−10 DAN12−8 6.31mm (0.248in.) 6.35mm (0.250in.) 6.71mm (0.264in.) 6.75mm (0.266in.)

**NOTE:** 01 01

START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 01 01 01 01 25 46 33 56 114 47 26 48 83 55 26 48 83 55 115 47 27 48 84 55 27 48 84 55 34 47 28 48 85 55
G_SB_533160_6_BCAA_02_00 Figure A-GBCAA - Sheet 02 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 188 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

COLLAR COLLAR

PIN UNI PIN, UNI DAN5−6−7X DAN11−6X

DAN5−6−10X DAN11−6X
COLLAR COLLAR

PIN UNI PIN, UNI PIN UNI COLLAR

PIN UNI COLLAR PIN UNI COLLAR NOMINAL SIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE TRANSITION FIT 2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

2ND OVERSIZE NOMINAL SIZE TRANSITION FIT TRANSITION FIT 2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

PIN UNI COLLAR DAN7−10−12 DAN12−10 DAN7−10−12X DAN12−10X

DAN12−10X DAN7−10−17X PIN UNI COLLAR DAN12−10 DAN7−10−17 PIN UNI COLLAR DAN7−8−12Y DAN12−8Y

DAN7−8−17Y DAN12−8Y

DAN5−6−7Y NSA5330−6

DAN5−6−10Y 7.90mm (0.311in.)

7.90mm (0.311in.)

5.51mm (0.217in.) 7.10mm (0.280in.)

8.30mm (0.327in.) 7.10mm (0.280in.)

8.30mm (0.327in.) 5.11mm (0.201in.)

5.51mm (0.217in.) 5.11mm (0.201in.)

7.90mm (0.311in.) 7.10mm (0.280in.)

8.30mm (0.327in.)

7.94mm (0.313in.)

7.94mm (0.313in.)

5.55mm (0.219in.) 7.14mm (0.281in.)

8.34mm (0.328in.) 7.14mm (0.281in.)

8.34mm (0.328in.)

5.15mm (0.203in.)

5.55mm (0.219in.) 5.15mm (0.203in.)
NSA5330−6 PIN UNI COLLAR PIN UNI COLLAR

DAN7−10−11X DAN12−10X PIN UNI COLLAR DAN7−10−11 DAN12−10 DAN7−8−11Y DAN12−8Y 7.94mm (0.313in.) 7.14mm (0.281in.)

8.34mm (0.328in.)

01 01 01 01 01

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 61 54 29 49 86 97 62 54 30 49 87 97 116 54 31 49 88 97 32 56 57 53 33 56 89 53

G_SB_533160_6_BCAA_03_00 Figure A-GBCAA - Sheet 03 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 189 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

COLLAR PIN UNI

COLLAR PIN UNI COLLAR PIN UNI P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

COLLAR PIN UNI

COLLAR PIN UNI COLLAR PIN UNI

COLLAR PIN UNI DAN7−8−16Y DAN12−8Y COLLAR PIN UNI DAN7−8−15Y DAN12−8Y COLLAR PIN UNI DAN7−8−13Y DAN12−8Y DAN7−10−13 DAN12−10 TRANSITION FIT NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT 2ND OVERSIZE

DAN7−8−13X DAN12−8X

DAN7−10−15 DAN12−10 DAN7−8−15X DAN12−8X

DAN7−10−16 DAN12−10 DAN7−8−16X DAN12−8X 7.90mm (0.311in.)

7.90mm (0.311in.)

7.90mm (0.311in.) 6.71mm (0.264in.) 7.10mm (0.280in.)

6.71mm (0.264in.) 7.10mm (0.280in.)

6.71mm (0.264in.) 7.10mm (0.280in.) 6.31mm (0.248in.) 5.51mm (0.217in.) 5.11mm (0.201in.)

7.94mm (0.313in.)

7.94mm (0.313in.)

7.94mm (0.313in.) 6.75mm (0.266in.) 7.14mm (0.281in.)

6.75mm (0.266in.) 7.14mm (0.281in.)

6.75mm (0.266in.) 7.14mm (0.281in.) COLLAR PIN UNI

COLLAR PIN UNI COLLAR PIN UNI DAN7−6−11Y DAN12−6Y DAN7−8−11 DAN12−8 DAN12−6X DAN7−6−11X

6.35mm (0.250in.) 5.55mm (0.219in.) 5.15mm (0.203in.)

01

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 01 01 117 121 34 47 28 48 118 55 35 54 90 49 119 55 36 54 91 49 120 55 37 54 92 49

G_SB_533160_6_BCAA_04_00 Figure A-GBCAA - Sheet 04 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 190 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

COLLAR PIN UNI COLLAR PIN UNI

PIN UNI COLLAR DAN7−8−12X DAN12−8X PIN UNI COLLAR PIN UNI COLLAR DAN5−6−8Y NSA5330−6 PIN UNI COLLAR

COLLAR PIN UNI

COLLAR PIN UNI TRANSITION FIT

TRANSITION FIT TRANSITION FIT

NOMINAL SIZE

NOMINAL SIZE

NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE TRANSITION FIT

NOMINAL SIZE TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE

COLLAR PIN UNI DAN7−8−10Y DAN12−8Y

PIN UNI COLLAR PIN UNI COLLAR DAN7−8−11Y DAN12−8Y DAN5−8−8 NSA5075−8

DAN7−8−12Y DAN12−8Y

DAN7−10−10 DAN12−10 DAN7−8−10X DAN12−8X

DAN7−10−11 DAN12−10 DAN7−8−11X DAN12−8X

7.90mm (0.311in.) 7.90mm (0.311in.) 6.31mm (0.248in.) 6.71mm (0.264in.) 7.10mm (0.280in.) 5.11mm (0.201in.) 5.51mm (0.217in.)

6.71mm (0.264in.) 7.10mm (0.280in.)

6.71mm (0.264in.) 7.10mm (0.280in.) 6.31mm (0.248in.) 5.11mm (0.201in.) 5.51mm (0.217in.)

7.94mm (0.313in.) 7.94mm (0.313in.) 6.35mm (0.250in.) 6.75mm (0.266in.) 7.14mm (0.281in.) 5.15mm (0.203in.) 5.55mm (0.219in.)

6.75mm (0.266in.) 7.14mm (0.281in.)

6.75mm (0.266in.) 7.14mm (0.281in.) DAN5−6−8X DAN11−6X PIN UNI COLLAR DAN5−6−7Y NSA5330−6 PIN UNI COLLAR

PIN UNI COLLAR DAN5−6−7X

DAN5−8−7 NSA5075−8 6.35mm (0.250in.) 5.15mm (0.203in.) 5.55mm (0.219in.) DAN11−6X

01 01 01 01 01

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 32 56 57 53 99 98 82 56 58 53 100 98 59 55 62 54 84 55 60 54 101 49 85 55 61 54 29 49

G_SB_533160_6_BCAA_05_00 Figure A-GBCAA - Sheet 05 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 191 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

NOMINAL SIZE TRANSITION FIT RIVET
NOMINAL SIZE TRANSITION FIT RIVET RIVET NOMINAL SIZE TRANSITION FIT EN6080D5−06 4.06mm (0.16in.) 4.17mm (0.164in.) 4.85mm (0.191in.) 4.95mm (0.195in.) 4.06mm (0.16in.) 4.17mm (0.164in.)
NOMINAL SIZE TRANSITION FIT RIVET RIVET NOMINAL SIZE TRANSITION FIT LN9198−4814CF LN9198−4014CF LN9198−4812CF LN9198−4012CF

4.06mm (0.16in.) 4.17mm (0.164in.) 4.85mm (0.191in.) 4.95mm (0.195in.) PIN UNI COLLAR TRANSITION FIT PIN UNI COLLAR PIN UNI COLLAR DAN7−8−12Y DAN12−8Y DAN7−10−12 DAN12−10 DAN7−8−12X DAN12−8X

NOMINAL SIZE 7.90mm (0.311in.) 7.94mm (0.313in.) TRANSITION FIT
TRANSITION FIT

1ST OVERSIZE
2ND OVERSIZE 6.71mm (0.264in.) 6.75mm (0.266in.) 7.10mm (0.280in.) 7.14mm (0.281in.) P/N DESCRIPTION MIN MAX ITEM HOLE SYMBOL REMARKS FINAL HOLE DIAMETER

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 59 55 62 54 30 49 73 76 75 74 77

G_SB_533160_6_BCAA_06_00 Figure A-GBCAA - Sheet 06 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 192 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

INTERFERENCE FIT NOMINAL SIZE INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT INTERFERENCE FIT

NOMINAL SIZE INTERFERENCE FIT INTERFERENCE FIT

NOMINAL SIZE INTERFERENCE FIT

INTERFERENCE FIT

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

REMARKS

INTERFERENCE FIT
INTERFERENCE FIT

NOMINAL SIZE 2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE ASNA2528−4 BOLT NUT

BOLT NUT

BOLT NUT

BOLT NUT

BOLT NUT BOLT NUT EN6115K4Y7 ASNA2528−4 BOLT NUT EN6115K5−7 ASNA2528−5
ASNA2528−4 EN6115K4Y8 BOLT NUT EN6115K5−8 ASNA2528−5
ASNA2528−4 EN6115K4Y10 BOLT NUT
ASNA2528−5 EN6115K5−10

ASNA2528−4 EN6115K4Y11 BOLT NUT
ASNA2528−5 EN6115K5−11

ASNA2528−4 EN6115K4Y12 BOLT NUT EN6115K5−12 ASNA2528−5

BOLT NUT ASNA2528−5 P/N DESCRIPTION GAGE FINISH REAMER
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088 MIN 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.) MAX 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.) START REAMER

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1

CBSR−8−3−N−1 CBSR−8−1−N−1 ITEM HOLE SYMBOL STDN

8−3−N 8−1−N

8−3−N 8−1−N

8−3−N 8−1−N

8−3−N 8−1−N

8−3−N 8−1−N

8−3−N 8−1−N

8−3−N 8−1−N FINAL HOLE DIAMETER START DRILL

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1

CBSD−8−3−N−1 CBSD−8−1−N−1 ASNA2528−4 EN6115K4Y16 BOLT NUT BOLT NUT EN6115K5−16 ASNA2528−5 EN6115K4Y15
EN6115K5−15

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 01 01 01 01 01 01 38 51 93 52 39 51 94 52 40 51 68 52 41 51 69 52 42 51 70 52 43 51 95 52 44 51 96 52

G_SB_533160_6_BCAA_07_00 Figure A-GBCAA - Sheet 07 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 193 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION GAGE FINISH REAMER

CBR−4−4−N−1−.1859 CBR−4−4−N−1−.1859 CBR−4−4−N−1−.1859 CBR−4−4−N−1−.1859 CBR−4−4−N−1−.1859
CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991
CBR−6−1−N−1−.215
CBR−6−3−N−1−.246

CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991
CBR−6−1−N−1−.215
CBR−6−3−N−1−.246 MIN

4.723mm (0.1859in.) 4.723mm (0.1859in.) 4.723mm (0.1859in.) 4.723mm (0.1859in.) (0.1991in.) 5.056mm
4.723mm (0.1859in.) 5.056mm (0.1991in.)

5.056mm (0.1991in.) 5.452mm (0.215in.) 6.252mm (0.246in.)

5.056 (0.1991in.)

5.056mm (0.1991in.) 5.452mm (0.215in.) 6.252mm (0.246in.) MAX

4.758mm (0.1873in.) 4.758mm (0.1873in.) 4.758mm (0.1873in.) 4.758mm (0.1873in.) 4.758mm (0.1873in.) 5.090mm (0.200in.)

5.090mm (0.200in.)

5.090mm (0.200in.) 5.487mm (0.216in.) 6.287mm (0.248in.)

5.090mm (0.200in.)

5.090mm (0.200in.) 5.487mm (0.216in.) 6.287mm (0.246in.) START REAMER

CBSR−4−4−N−1 CBSR−4−4−N−1 CBSR−4−4−N−1 CBSR−4−4−N−1 CBSR−4−4−N−1
CBSR−6−0−N−1

CBSR−6−0−N−1

CBSR−6−0−N−1

CBSR−6−3−N−1 CBSR−6−1−N−1

CBSR−6−0−N−1

CBSR−6−0−N−1
CBSR−6−1−N−1
CBSR−6−3−N−1 ITEM HOLE SYMBOL REMARKS STDN FINAL HOLE DIAMETER START DRILL

CBSD−4−4−N−1 CBSD−4−4−N−1 CBSD−4−4−N−1 CBSD−4−4−N−1 CBSD−4−4−N−1
CBSD−6−0−N−1

CBSD−6−0−N−1

CBSD−6−0−N−1
CBSD−6−1−N−1

CBSD−6−0−N−1

CBSD−6−0−N−1
CBSD−6−1−N−1
CBSD−6−3−N−1 CBSD−6−3−N−1

INTERFERENCE FIT NOMINAL SIZE INTERFERENCE FIT

NOMINAL SIZE 4−4−N INTERFERENCE FIT NOMINAL SIZE 4−4−N INTERFERENCE FIT NOMINAL SIZE INTERFERENCE FIT

NOMINAL SIZE ASNA2528−3

ASNA2528−3

ASNA2528−3

ASNA2528−3 EN6115K3−4

EN6115K3−5

EN6115K3−7

EN6115K3−8 ASNA2528−3A BOLT NUT

BOLT NUT

BOLT NUT

BOLT NUT

BOLT NUT

BOLT NUT INTERFERENCE FIT BOLT NUT

INTERFERENCE FIT ASNA2528−3 BOLT NUT

INTERFERENCE FIT NOMINAL SIZE BOLT NUT

INTERFERENCE FIT BOLT NUT

INTERFERENCE FIT BOLT NUT
ASNA2528−3A BOLT NUT ASNA2528−3 EN6115K3X4

EN6115K3X5

ASNA2528−4 EN6115K4−7

ASNA2528−3 EN6115K3X7

ASNA2528−3 EN6115K3X8

ASNA2528−4 INTERFERENCE FIT BOLT NUT INTERFERENCE FIT NOMINAL SIZE 4−4−N EN6115K3−3 ASNA2528−3 BOLT NUT EN6115K3X3 ASNA2528−3 1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE EN6115K3A7

EN6115K3A8
EN6115K4−8 6−0−N

6−0−N
4−4−N 4−4−N

6−0−N

6−3−N

6−0−N

6−0−N

6−3−N NOMINAL NOMINAL

6−1−N 6−1−N

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 01 01 01 01 01 01 63 50 102 50 64 50 103 50 65 50 104 50 124 126 105 51 66 50 106 50 67 50 107 50 125 126 108 51

G_SB_533160_6_BCAA_08_00 Figure A-GBCAA - Sheet 08 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 194 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

INTERFERENCE FIT NOMINAL SIZE EN6115K5−10 ASNA2528−5

INTERFERENCE FIT NOMINAL SIZE ASNA2528−5 EN6115K5−11

ASNA2528−5 INTERFERENCE FIT NOMINAL SIZE ASNA2528−5 EN6115K5−12

ASNA2528−5 INTERFERENCE FIT NOMINAL SIZE ASNA2528−5 EN6115K5−17 P/N DESCRIPTION GAGE FINISH REAMER
CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773 CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088 CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245 MIN 7.044mm (0.2773in.)

7.044mm (0.2773in.)

7.044mm (0.2773in.)

7.044mm (0.2773in.) 7.044mm (0.2773in.) 7.845mm (0.3088in.)

7.845mm (0.3088in.)

7.845mm (0.3088in.)

7.845mm (0.3088in.) 8.241mm (0.3245in.)

8.241mm (0.3245in.)

8.241mm (0.3245in.)

8.241mm (0.3245in.) MAX 7.078mm (0.2787in.)

7.078mm (0.2787in.)

7.078mm (0.2787in.)

7.078mm (0.2787in.) 7.078mm (0.2787in.) 7.879mm (0.3102in.)

7.879mm (0.3102in.)

7.879mm (0.3102in.)

7.879mm (0.3102in.) 8.275mm (0.3258in.)

8.275mm (0.3258in.)

8.275mm (0.3258in.)

8.275mm (0.3258in.) START REAMER

CBSR−8−1−N−1

CBSR−8−1−N−1

CBSR−8−1−N−1

CBSR−8−1−N−1 CBSR−8−3−N−1

CBSR−8−3−N−1

CBSR−8−3−N−1

CBSR−8−3−N−1 CBSR−10−0−N−1

CBSR−10−0−N−1

CBSR−10−0−N−1

CBSR−10−0−N−1 ITEM HOLE SYMBOL REMARKS STDN
8−1−N

8−1−N

8−1−N

8−1−N 8−3−N

8−3−N

8−3−N

8−3−N 10−0−N

10−0−N

10−0−N

10−0−N FINAL HOLE DIAMETER START DRILL
CBSD−8−1−N−1

CBSD−8−1−N−1

CBSD−8−1−N−1

CBSD−8−1−N−1 CBSD−8−3−N−1

CBSD−8−3−N−1

CBSD−8−3−N−1

CBSD−8−3−N−1 CBSD−10−0−N−1

CBSD−10−0−N−1

CBSD−10−0−N−1

CBSD−10−0−N−1 EN6115K5X17 EN6115K4Y17 ASNA2528−4 EN6115K5X12 ASNA2528−4 EN6115K4Y12 ASNA2528−5 EN6115K5X11 ASNA2528−4 EN6115K4Y11 EN6115K5X10 ASNA2528−5 EN6115K4Y10 ASNA2528−4

INTERFERENCE FIT 1ST OVERSIZE INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE INTERFERENCE FIT

1ST OVERSIZE

INTERFERENCE FIT

1ST OVERSIZE

INTERFERENCE FIT

1ST OVERSIZE BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT BOLT NUT 01

01

01

01

**NOTE:** 01 START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 40 51 68 52 109 52 41 51 69 52 110 52 42 51 70 52 111 52 122 51 71 52 112 52

G_SB_533160_6_BCAA_09_00 Figure A-GBCAA - Sheet 09 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 195 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION GAGE FINISH REAMER
CBR−8−1−N−1−.2773
CBR−8−3−N−1−.3088
CBR−10−0−N−1−.3245 MIN 7.044mm (0.2773in.) 7.845mm (0.3088in.) 8.241mm (0.3245in.) MAX 7.078mm (0.2787in.) 7.879mm (0.3102in.) 8.275mm (0.3258in.) START REAMER

CBSR−8−1−N−1
CBSR−8−3−N−1
CBSR−10−0−N−1 ITEM HOLE SYMBOL REMARKS STDN
8−1−N
8−3−N
10−0−N FINAL HOLE DIAMETER START DRILL
CBSD−8−1−N−1
CBSD−8−3−N−1
CBSD−10−0−N−1 INTERFERENCE FIT ASNA2528−5 INTERFERENCE FIT
INTERFERENCE FIT

NOMINAL SIZE ASNA2528−5 EN6115K5−19
EN6115K5X19 EN6115K4Y19 ASNA2528−4 2ND OVERSIZE

1ST OVERSIZE BOLT NUT BOLT NUT BOLT NUT **NOTE:** START IN THIS ROW TO DETERMINE THE FINAL FASTENER SIZE. 01 01 123 51 72 52 113 52

G_SB_533160_6_BCAA_10_00 Figure A-GBCAA - Sheet 10 Fastener Table
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 196 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

FR91 Z310 Z270



### A

**B**

**B D** 

**D E** 

**E**



## A FR80 FR84 FR86

G_SB_533160_6_BDAA_01_00 Figure A-GBDAA - Sheet 01 Inspection Areas of Fastener Hole Rototest and for HFEC Inspection
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 197 6

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

# @A330 SERVICE BULLETIN

**CONF ALL



### A

**A** FR80 STGR2A

STGR5A

STGR2A

STGR5A 

### C 

## B

**C**
**A A**  TYPICAL HOLE LH SHOWN RH SYMMETRICAL **FWD** 01

adet = 1.0mm (0.039in.)

**NOTE:** TO BE INSPECTED BY ROTOTEST ONLY. 01 G_SB_533160_6_BDAA_02_00 Figure A-GBDAA - Sheet 02 Inspection Areas of Fastener Hole Rototest and for HFEC Inspection
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 198 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

**FWD** FR84



## D LH SHOWN RH SYMMETRICAL 

### B **B**

**B**

**B** INSPECTION AREA B FROM OUTSIDE AD

**NOTE:** DO THE ROTOTEST ONLY IN THE HOLES OF AREA B WHICH ARE ALREADY REMOVED. STGR3

STGR5A

G_SB_533160_6_BDAA_03_00 Figure A-GBDAA - Sheet 03 Inspection Areas of Fastener Hole Rototest and for HFEC Inspection
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 199 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

LH SHOWN RH SYMMETRICAL

INSPECTION AREA C FROM OUTSIDE FR86



### B **B B**  **B** AD



## E **FWD** STGR3

STGR6

STGR8

**NOTE:** DO THE ROTOTEST ONLY IN THE HOLES OF AREA C WHICH ARE ALREADY REMOVED. G_SB_533160_6_BDAA_04_00 Figure A-GBDAA - Sheet 04 Inspection Areas of Fastener Hole Rototest and for HFEC Inspection
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 200 6

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

# @A330 SERVICE BULLETIN

**CONF ALL



## B **B** 2.0 mm (0.079 in) det = a



### F STGR1.0mm(0.39in.)



## F TYPICAL HOLE FOR ROTOTEST INSPECTION

TYPICAL FOR HFEC INSPECTION

G_SB_533160_6_BDAA_05_00 Figure A-GBDAA - Sheet 05 Inspection Areas of Fastener Hole Rototest and for HFEC Inspection
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 201 6

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

# @A330 SERVICE BULLETIN

**CONF ALL

REMOVE THE FASTENERS AS SHOWN IN FIGURE 2

DO A ROTOTEST OF ALL FASTENER HOLES AND DO A HFEC TEST BETWEEN ALL FASTENER HOLES

CHECK THE EDGE CLEARENCE IN ACCORDANCE WITH THE FINAL DIAMETER OF FASTENER HOLES AND SRM 51−47−00.

IS THE EDGE CLEARANCE

TO MOVE THE HOLE CENTER POINT REWORK THE FASTENER HOLE WITH A MILLING TOOL TO ENSURE THE REQUIRED EDGE CLEARENCE IS THE REWORK OF THE FASTENER HOLES POSSIBLE?

INSTALL THE DOUPLER BY TRANSFER DRILLING THE FASTENER HOLES WITH A DRILL CORESPONDING WITH THE REWORKED FASTENER HOLE DIMENSION.

INSTALL THE DOUBLER WITH THE STANDARD FASTENERS OR

NEXT OVERSIZE FASTENERS AS GIVEN IN THE SERVICE BULLETIN INSTALL THE DOUBLER WITH THE UNDERSIZE FASTENERS NO CHECK IF YOU CAN REWORK THE FASTENER HOLES CORRECT? YES NO

YES

AS GIVEN IN THE SERVICE BULLETIN

FOR ONE DOUBLER INSTALLATION ONLY FIVE UNDERSIZE FASTENERS ARE ALLOWED WITH A MAXIMUM OF TWO FASTENERS ADJACENT TO EACH OTHER. IF IT IS NECESSARY TO INSTALL MORE THAN FIVE UNDERSIZE FASTENERS CONTACT AIRBUS. **NOTE:** 01 01

G_SB_533160_6_BEAA_01_00 Figure A-GBEAA - Sheet 01 Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 202 6

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

# @A330 SERVICE BULLETIN

**CONF ALL



## STEP 1 STEP 2 STEP 3

MILLING DRILL FINAL DRILL

X X Y X+Y REMOVED MATERIAL DIAMETER DRILL HOLE FINAL FASTENER

REWORKED FASTENER HOLE AFTER MILLING = AFFECTED FASTENER HOLES 

### A **C B** 



## A **B C**  **D E**  **F**



## D **E F**  **A A**  

## A **A B**  **B C**  **C**

G_SB_533160_6_BEAA_02_00 Figure A-GBEAA - Sheet 02 Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking
DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 203 6

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

# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH MODIFICATION No.: 53222D44560 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.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 1 6

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

# @A330 SERVICE BULLETIN REPORTING SHEET Alternatively, SB lists via letters or fax are also accepted.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 2 6

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

# @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: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160 REVISION No.: 03 - Jan 06/12 Page: 1 6

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