# @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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). MODIFICATION No.: None This page transmits Revision No.05 of Service Bulletin No.A330-57-3081 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 05 issued to update the threshold and intervals and to add the grace period value. CHANGES SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R Fig. A-FSAAA Fig. A-FSAAA Sheet 01 SHEET UPDATED R Fig. A-FSAAB Fig. A-FSAAB Sheet 01 SHEET UPDATED R

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
PLANNING INFORMATION EFFECTIVITY Validation note added. Configuration notes simplified. Effectivity updated. R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 004 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 005 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 006 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R REASON Objective/Action OBJECTIVE/ACTION UPDATED R Advantages ADVANTAGES UPDATED R COMPLIANCE Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R Accomplishment Timescale Table title, values and sentence modified. R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R MATERIAL INFORMATION TOOLING TOOLING UPDATED R Tooling - Price and Availability TOOLING - PRICE AND AVAILABILITY PARAGRAPH ADDED N Tools TOOLS PARAGRAPH ADDED N Special Tools SPECIAL TOOLS PARAGRAPH ADDED N

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
ACCOMPLISHMENT INSTRUCTIONS TASK573081- 832-801-001-INSPECTION TASK SOLUTION UPDATED NOTE UPDATED R Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 002 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 003 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 004 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 005 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 006 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 573081-941-001-003 The paragraphs concerning the job set-up of the FWD cargo are deleted. N Subtask 573081-941-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-941-001-003 The paragraphs concerning the job set-up of the FWD cargo are deleted. N Subtask 573081-941-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-941-001-003 The paragraphs concerning the job set-up of the FWD cargo are deleted. N Subtask 573081-941-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. R Subtask 573081-941-001-001 The paragraphs concerning the job set-up of the FWD cargo are deleted. R Subtask 573081-941-001-003 The paragraphs concerning the job set-up of the FWD cargo are deleted. N Subtask 573081-941-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-010-001-001 Removal procedure of the air conditioning duct deleted. R Subtask 573081-010-002-001 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-001 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-001 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-001 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-410-002-001 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-010-001-002 Removal procedure of the air conditioning duct deleted. R

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 573081-010-002-002 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-002 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-002 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-002 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-410-002-002 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-010-001-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-010-002-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-410-002-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-010-001-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-010-002-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-410-002-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-010-001-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-010-002-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-410-002-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-010-001-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-010-002-003 Removal procedure of the air conditioning duct deleted. R Subtask 573081-832-006-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-832-007-003 Reference to NTM 51-10-01 Part 6 added. R Subtask 573081-410-001-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 573081-410-002-003 Installation procedure of the air conditioning duct deleted. Sealing sentence added. R Subtask 573081-710-001-002 AMM 12-33-21 and AMM 21-28-00 deleted. N Subtask 573081-710-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-710-001-002 AMM 12-33-21 and AMM 21-28-00 deleted. N Subtask 573081-710-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-710-001-002 AMM 12-33-21 and AMM 21-28-00 deleted. N Subtask 573081-710-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 573081-710-001-002 AMM 12-33-21 and AMM 21-28-00 deleted. N Subtask 573081-710-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Fig. A-FBAAA Fig. A-FBAAA Sheet 01 SHEET UPDATED R Fig. A-FBAAB Fig. A-FBAAB Sheet 01 SHEET UPDATED R Fig. A-FFAAA Fig. A-FFAAA Sheet 01 SHEET UPDATED R Fig. A-FFAAA Sheet 02 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAB Fig. A-FFAAB Sheet 01 SHEET UPDATED R Fig. A-FFAAB Sheet 02 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAB Sheet 03 SRM 51-41-11 becomes 51-44-11. R Fig. A-FFAAC Fig. A-FFAAC Sheet 01 SHEET UPDATED R Fig. A-FFAAC Sheet 02 SHEET UPDATED R Fig. A-FFAAC Sheet 03 SRM 51-41-11 becomes 51-44-11. R Fig. A-FCAAA Fig. A-FCAAA Sheet 01 SHEET UPDATED R Fig. A-FCAAB Fig. A-FCAAB Sheet 01 SHEET UPDATED R Fig. A-FCAAC Fig. A-FCAAC Sheet 02 SHEET UPDATED R Appendix 01 - Inspection Report Fig. A-FRAAA FIGURE SOLUTION ADDED N Fig. A-FRAAA Sheet 01 SHEET ADDED N Fig. A-FRAAB FIGURE SOLUTION ADDED N Fig. A-FRAAB Sheet 01 SHEET ADDED N Fig. A-FAA FIGURE DELETED FOR APPLICABLE MSN D

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 5 5

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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 Revision No. 01 issued to modify the content of Kit 573081A01R04 and to include minor improvements. Revision No. 02 issued to inform the operators that this Service Bulletin is rendered mandatory. The inspection requirements of this Service Bulletin are cancelled by accomplishment of Service Bulletin No. A330-57-3090 (FUSELAGE - CENTER FUSELAGE - MODIFY FASTENERS IN FR40 KEEL BEAM / BOTTOM SKIN PANEL JUNCTION AREA) which is scheduled early 2006 on A330 aircraft PRE MOD 41652S11819. Revision No. 03 issued to extend the effectivity of this Service Bulletin and to propose a modification Service Bulletin to cancel the repetitive inspection requirements. This Service Bulletin has been validated on A330 aircraft MSN 0649.

Revision No. 04 issued to include minor improvements after validation : to update the flow chart for Config. 003 thru 006, to delete the access procedure of the FWD cargo compartment, to delete the removal/installation procedures of the air conditioning duct. REVISION SEQUENCE ORIGINAL: Oct 30/03 REVISION No.: 01 - May 18/04 REVISION No.: 02 - Jan 24/06 REVISION No.: 03 - Jul 31/09 REVISION No. : 04 - May 31/11 REVISION No. : 05 - Nov 13/12

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A330 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame FR40, initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD No. 41652S12091 (serial Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) configuration. Results for this configuration have been extended to POST MOD No. 43577S12677 (retrofit Mod.) (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION) configuration which is similar. This Service Bulletin requires a special detailed inspection on A330 aircraft PRE MOD 55306S18660 and PRE MOD 55792S18775. Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of Frame FR40 datum after fastener removal (Rotating Probe Inspection following NTM 51-10-01 Part 6) and subsequent action. For the Config. 1 accomplishment of Service Bulletin No. A330-57-3090 (Mod. No. 54459S18477) cancels the Inspection requirements of this Service Bulletin No. A330-57-3081. For the Config. 2,3,4,5 and 6, accomplishment of Service Bulletin No A330-57-3098 (Mod. No. 56467S18944) cancels the Inspection requirements of this Service Bulletin No. A330-57-3081. Accomplishment of this Service Bulletin will permit early detection of cracking in the keel beam and will avoid extensive repair and aircraft down time.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A330 SERVICE BULLETIN SUMMARY 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 DE-FUELLING/VENTILATING YES 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 573081A01R00 2 556.00 Screw, Washer, Nut **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573081A01R00 2 556.00 Screw, Washer, Nut **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573081A02R04 2 466.00 Screw, Washer, Nut **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573081A02R04 2 466.00 Screw, Washer, Nut **CONF 005 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573081A02R04 2 466.00 Screw, Washer, Nut

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A330 SERVICE BULLETIN SUMMARY **CONF 006 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573081A02R04 2 466.00 Screw, Washer, Nut EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

AAR ACA ACI AEA AFR ALK ASY AZA BEL BER BMA BTV CAL CCA CES CPA CRL CSC CSN DAH DAL DGA DLH EDW EIN ETD EVA FWI GFA GIA GRL HDA HFY HVN I2L IAC ISS IWD IYE JAI JAV JST KAL KLM MAS MON MSR OHY PAL QAF QFA QTR RSY RYN SAI SAS SWR TAM TAP TCX THA THY TSC UAE USA VKG VLK VOZ XAX XLF NOTE: This Service Bulletin has been validated on A330 aircraft MSN 0649. CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.005 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHERS Operator Information Telex (OIT) No. 999.0083/03 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY **CONF 002 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00 **CONF 003 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00 **CONF 004 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 005 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 006 Task 573081-832-801-001: INSPECTION TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00 APPENDICES **CONF ALL Appendix 01 - Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

G_SB_573081_5_SAAA_01_02 Figure A-FSAAA - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 5 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

G_SB_573081_5_SAAB_01_01 Figure A-FSAAB - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF 003 thru 006

LH SIDE SHOWN RH SIDE SYMMETRICAL FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

G_SB_573081_5_SAAC_01_00 DATUM Y2390 Y1959

AREA TO INSPECT STGR1 RIB1 FR40

**F W**  **D**

Figure A-FSAAC - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 7 5

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# @A330 SERVICE BULLETIN SUMMARY

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DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 8 5

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# @A330 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). MODIFICATION No.: None 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 has been validated on A330 aircraft MSN 0649. NOTE: This Service Bulletin is only applicable to aircraft on which modification No. 55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and modification No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) is not embodied. (1) Models 330-202 330-203 330-223 330-243 330-301 330-302 330-303 330-321 330-322 330-323 330-341 330-342 330-343 (2) Effectivity by MSN 0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0067 0069-0073 0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 0116 0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172 0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 0253-0256
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A330 SERVICE BULLETIN
0258-0259 0261-0262 0265-0267 0269 0271-0272 0275-0277 0279 0281 0283-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0317 0320 0322-0324 0326 0328 0330 0333-0334 0337-0340 0342-0346 0348-0351 0353 0356-0358 0361-0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386 0388-0389 0392-0393 0396-0398 0400-0401 0403-0405 0407-0409 0412 0418-0423 0425 0427-0428 0432 0437 0439 0441 0443-0444 0448 0451-0452 0454-0456 0458 0461-0463 0465-0466 0469 0472-0473 0476-0477 0479-0481 0484 0486-0487 0489-0491 0493-0494 0496-0498 0500-0513 0515-0516 0518-0519 0521-0522 0524-0527 0529-0530 0532-0533 0535-0536 0539 0542 0548-0553 0555 0558 0564-0565 0567-0568 0570-0571 0573-0574 0576 0578-0579 0581 0584 0587-0588 0591 0593 0595 0597 0600 0602-0603 0605 0607 0609-0610 0612 0614 0616 0618 0620-0621 0623 0625 0627 0629 0631-0638 0640-0642 0644-0645 0647-0650 0652-0659 0661-0667 0669-0671 0673-0676 0678-0680 0682-0684 0686-0688 0690-0693 0695-0697 0699-0701 0703-0705 0707-0709 0711-0714 0716-0718 0720-0722 0724-0726 0728-0730 0732-0735 0737-0739 0741-0743 0745-0747 0749-0752 0754-0756 0758-0760 0769-0770 0772-0774 0776-0778 0780-0782 0784-0786 0788-0789 0791-0792 0795-0797 0799 0801-0803 0805-0807 0809-0811 0813-0815 0817-0823 0826 (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 AAR 0640 0676 0708 0772 0803 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AEA 0505 0526 0551 0597 0733 0745 0749 0814 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519 0567 0584 0657 ALK 0303 0306 0311 0313 0404 0456 0627 ASY 0747 AZA 0272 0339 BEL 0030 0037 0045 0082 0095 0229 0249 BER 0120 0127 0288 0322 0403 0432 0444 0454 0469 0476 0493 0665 0739 BMA 0398 0401 BTV 0205 0330 CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0725 0752 0769 0805 0823 CCA 0750 0756 0759 0780 0785 0797 0810 0815 CES 0713 0720 0728 0732 0735 0773 0777 0781 0782 0791 0821 CPA 0012 0017 0071 0102 0113 0118 0121 0155 0386 0389 0393 0418 0420 0421 0423 0439 0539 0548 0565 0669 0673 0679 0776 CRL 0285 0320 CSC 0462 CSN 0649 0652 0656 0664 0818
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN DAH 0644 0647 0650 0653 0667 DAL 0524 0533 0542 0549 0552 0578 0588 0591 0609 0614 0618 0620 0621 0631 0633 0663 0674 0690 0718 0722 0778 0784 0796 0799 0806 0817 DGA 0240 DLH 0570 0576 0579 0629 0636 0642 0645 0648 0687 0701 EDW 0291 EIN 0269 0397 ETD 0658 0688 0717 0724 0729 0730 0737 0751 0788 0809 EVA 0530 0535 0555 0573 0587 0634 0655 0661 0678 0693 0755 FWI 0253 0758 GFA 0276 0281 0286 0287 0334 0340 0527 0529 0532 GIA 0138 0140 0144 0148 0153 0165 GRL 0230 HDA 0083 0099 0106 0109 0234 0244 0405 0479 0512 0581 0654 0662 0692 0716 0741 0786 HFY 0096 0211 0262 HVN 0275 0294 0299 0366 I2L 0358 0364 IAC 0353 0362 ISS 0802 0822 IWD 0461 0670 IYE 0625 0632 JAI 0807 JAV 0255 JST 0506 0508 0513 0522 KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 0550 KLM 0682 0686 0703 0738 0770 0801 0811 0819 MAS 0067 0069 0073 0077 0100 0107 0110 0116 0119 0290 0296 0300 MON 0261 0265 MSR 0600 0610 0666 0683 0696 0709 0726 OHY 0072 0087 0098 0143 PAL 0183 0184 0188 0189 0191 0198 0200 0203 QAF 0487 0605 QFA 0553 0558 0564 0574 0593 0595 0603 0695 0705 0712 QTR 0441 0473 0489 0511 0521 0571 0612 0616 0623 0637 0638 0659 0680 0684 0711 0721 0734 0743 0746 0760 0789 0792 0813 0820 0826 RSY 0171 RYN 0343 SAI 0055 0070 SAS 0496 0497 0515 0568 SWR 0324 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 0700 TAP 0181 0195 0223 0305 0308 0312 0317
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN TCX 0254 0266 0301 THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346 THY 0463 0504 0697 0704 0742 0754 0774 TSC 0111 0132 0177 0250 0271 0369 0407 0427 0480 0795 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0382 0384 0392 0396 0409 0437 0451 0452 0455 0491 0494 0509 0518 0525 0536 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0309 0349 0356 0357 VLK 0086 VOZ 0365 0372 XAX 0054 XLF 0501 0635 (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082 0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107 0109 0110 0111 0112 001

0113 0116 0118 0119 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171 0172 002 0177 0183 0184 0188 0189 0191 0198 0200 0203 0206 0209 0219 0224 0231 0234 0241 0244 0256 0267 0277 0279 0284 0315 0323 0333 0337 0338 0342 0344 0346 0349 0350 0351 0356 0357 0368 0370 0375 0380 0386 0388 0389 0393 0400 0405 0407 0408 0412 0418 0419 0420 0421 0423 0425 0428 0439 0479 0484 0490 0496 0497 0512 003

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 0522 004

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 4 5

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# @A330 SERVICE BULLETIN

MSN CONFIGURATION 0511 0513 0516 0518 0519 0521 0525 0526 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 0632 0633 0634 0635 0638 0644 0647 0649 0650 0652 0653 0655 0656 0657 0658 0661 0664 0665 0666 0667 0678 0682 0683 0684 0686 0688 0693 0696 0697 0700 0703 0704 0709 0717 0718 0722 0724 0726 0728 0729 0730 0732 0733 0735 0737 0738 0739 0742 0743 0745 0746 0747 0749 0750 0751 0754 0755 0756 0759 0760 0770 0774 0778 0780 0785 0788 0792 0795 0796 0797 0801 0802 0807 0809 0810 0811 0814 0815 0818 0819 0820 0821 0822 005

0515 0524 0533 0539 0542 0548 0549 0550 0552 0553 0558 0564 0565 0568 0570 0574 0576 0578 0579 0581 0588 0591 0593 0595 0602 0603 0607 0623 0629 0636 0637 0640 0641 0642 0645 0648 0654 0659 0662 0663 0669 0670 0671 0673 0674 0675 0676 0679 0680 0687 0690 0691 0692 0695 0699 0701 0705 0707 0708 0711 0712 0713 0714 0716 0720 0721 0725 0734 0741 0752 0758 0769 0772 0773 0776 0777 0781 0782 0784 0786 0789 0791 0799 0803 0805 0806 0813 0817 0823 0826 006

(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft model A330-300 on which Service Bulletin No. A330-57-3032 has been accomplished or Mod. No. 43577S12677 is embodied and on which Service Bulletin No. A330-57-3090 (Mod. No.54459S18477) has not been accomplished and Mod. No. 41652S12091 is not embodied. **CONF 002 Config. 002 is valid for aircraft model A330-300 on which Mod. No. 41652S12091 is embodied and on which Service Bulletin No. A330-57-3098 (Mod. No.56467S18944) has not been accomplished and Mod. No. 44360S13013 or Mod. No. 44360S13482 are not embodied. **CONF 003 Config. 003 is valid for aircraft model A330-300 on which Mod. No. 44360S13013 or Mod. No. 44360S13482 is embodied and on which Service Bulletin No. A330-57-3098 (Mod. No.56467S18944) has not been accomplished and Mod. No. 49202S16307 is not embodied. **CONF 004 Config. 004 is valid for aircraft model A330-200 on which Mod. No. 44360S13013 or Mod. No. 44360S13482 is embodied and on which Service Bulletin No. A330-57-3098 (Mod. No.56467S18944) has not been accomplished and Mod. No. 49202S16307 is not embodied. **CONF 005 Config. 005 is valid for aircraft model A330-200 on which Mod. No. 49202S16307 is embodied and on which Service Bulletin No. A330-57-3098 (Mod. No.56467S18944) has not been accomplished.
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 5 5

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# @A330 SERVICE BULLETIN
**CONF 006 Config. 006 is valid for aircraft model A330-300 on which Mod. No. 49202S16307 is embodied and on which Service Bulletin No. A330-57-3098 (Mod. No.56467S18944) has not been accomplished. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 573081A01R00 2 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 573081A01R00 2 Consumable CMLA01 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 573081A02R04 2 Consumable CMLA01 1 **CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit 573081A02R04 2 Consumable CMLA01 1 **CONF 005 MATERIAL QTY PER A/C SEE NOTES Kit 573081A02R04 2 Consumable CMLA01 1 **CONF 006 MATERIAL QTY PER A/C SEE NOTES Kit 573081A02R04 2 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 6 5

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# @A330 SERVICE BULLETIN
C. REASON (1) History During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame FR40, initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD No. 41652S12091 (serial Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) configuration. Results for this configuration have been extended to POST MOD No. 43577S12677 (retrofit Mod.) (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECTION) configuration which is similar. (2) Objective/Action This Service Bulletin requires a special detailed inspection on A330 aircraft PRE MOD 55306S18660 and PRE MOD 55792S18775. Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of Frame FR40 datum after fastener removal (Rotating Probe Inspection following NTM 51-10-01 Part 6) and subsequent action. (3) Advantages For the Config. 1 accomplishment of Service Bulletin No. A330-57-3090 (Mod. No. 54459S18477) cancels the Inspection requirements of this Service Bulletin No. A330-57-3081. For the Config. 2,3,4,5 and 6, accomplishment of Service Bulletin No A330-57-3098 (Mod. No. 56467S18944) cancels the Inspection requirements of this Service Bulletin No. A330-57-3081. Accomplishment of this Service Bulletin will permit early detection of cracking in the keel beam and will avoid extensive repair and aircraft down time. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 573081-832-801-001: INSPECTION (1) Remove the Fastener on the LH Side (2) Remove the Fastener on the RH Side (3) Do a Special Detailed Inspection of the Hole at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Hole at FR40, on the RH Side DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 7 5

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# @A330 SERVICE BULLETIN (5) Install the Fastener on the LH Side (6) Install the Fastener on the RH Side **CONF 002 Task 573081-832-801-001: INSPECTION (1) Remove the Fastener on the LH Side (2) Remove the Fastener on the RH Side (3) Do a Special Detailed Inspection of the Hole at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Hole at FR40, on the RH Side (5) Install the Fastener on the LH Side (6) Install the Fastener on the RH Side **CONF 003 Task 573081-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a Special Detailed Inspection of the Holes at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF 004 Task 573081-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a Special Detailed Inspection of the Holes at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 8 5

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# @A330 SERVICE BULLETIN
**CONF 005 Task 573081-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a Special Detailed Inspection of the Holes at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF 006 Task 573081-832-801-001: INSPECTION (1) Remove the Fasteners on the LH Side (2) Remove the Fasteners on the RH Side (3) Do a Special Detailed Inspection of the Holes at FR40, on the LH Side (4) Do a Special Detailed Inspection of the Holes at FR40, on the RH Side (5) Install the Fasteners on the LH Side (6) Install the Fasteners on the RH Side **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 9 5

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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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 14,200 (01) SR: 46,400 (01) SR: 12,000 SR: 39,300 SR: 3,600 (01) SR: 11,800 (01) SR: 2,400 SR: 7,800 Config. 001

LR: 13,000 (01) LR: 88,200 (01) LR: 11,000 LR: 74,700 LR: 3,300 (01) LR: 22,400 (01) LR: 2,150 LR: 14,800 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 14,590 FC - 43,790 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 12,360 FC

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 10 5

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# @A330 SERVICE BULLETIN
- 37,080 FH NOTE (01): On aircraft pre Mod. No. 41652S12091, the threshold is only valid from accomplishment of Service Bulletin No. A330-57-3032 or embodiment of the Mod. No. 43577S12677. NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 001 A330-57-3090 20,400 58,800

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 11 5

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# @A330 SERVICE BULLETIN

CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 15,000 SR: 49,200 SR: 10,700 SR: 34,900 SR: 4,650 SR: 15,200 SR: 2,300 SR: 7,600 Config. 002 LR: 13,800 LR: 93,400 LR: 9,800 LR: 66,300 LR: 3,750 LR: 25,300 LR: 1,850 LR: 12,600 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 15,460 FC - 46,400 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,970 FC - 32,910 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 002 A330-57-3098 21,000 60,600

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 12 5

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# @A330 SERVICE BULLETIN
**CONF 003 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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 15,000 SR: 49,200 SR: 10,700 SR: 34,900 SR: 6,250 SR: 20,500 SR: 2,700 SR: 8,900 Config. 003 WV010 Series LR: 13,800 LR: 93,400 LR: 9,800 LR: 66,300 LR: 5,750 LR: 38,900 LR: 2,500 LR: 16,900 SR: 15,200 SR: 49,700 SR: 10,800 SR: 35,200 SR: 6,350 SR: 20,700 SR: 2,750 SR: 9,000 Config. 003 WV020 Series except WV022 LR: 13,900 LR: 94,300 LR: 9,850 LR: 66,900 LR: 5,800 LR: 39,300 LR: 2,500 LR: 17,000 SR: 15,000 SR: 49,000 SR: 10,600 SR: 34,800 SR: 6,250 SR: 20,400 SR: 2,700 SR: 8,850 Config. 003 WV022 LR: 13,700 LR: 93,100 LR: 9,750 LR: 66,000 LR: 5,700 LR: 38,800 LR: 2,450 LR: 16,800 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 15,460 FC - 46,400 FH

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 13 5

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# @A330 SERVICE BULLETIN
NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,970 FC - 32,910 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 003 WV010 Series A330-57-3098 21,000 60,600 Config. 003 WV020 Series except WV022 A330-57-3098 21,000 60,600 Config. 003 WV022 A330-57-3098 21,000 60,600

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 004 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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 14 5

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# @A330 SERVICE BULLETIN

CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 13,500 SR: 44,200 SR: 9,600 SR: 31,400 SR: 5,650 SR: 18,400 SR: 2,450 SR: 8,000 Config. 004 LR: 12,000 LR: 78,400 LR: 8,550 LR: 55,600 LR: 5,000 LR: 32,700 LR: 2,150 LR: 14,200 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 12,870 FC - 64,380 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 9,130 FC - 45,660 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 004 A330-57-3098 22,100 64,400

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 15 5

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# @A330 SERVICE BULLETIN
**CONF 005 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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 18,500 SR: 60,600 SR: 9,600 SR: 31,400 SR: 11,300 SR: 39,700 SR: 2,450 SR: 8,000 Config. 005 LR: 16,500 LR: 107,400 LR: 8,550 LR: 55,600 LR: 9,150 LR: 59,600 LR: 2,150 LR: 14,200 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 17,630 FC - 88,190 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 9,130 FC - 45,660 FH

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 16 5

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# @A330 SERVICE BULLETIN
NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 005 A330-57-3098 22,100 64,400

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. **CONF 006 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 a trade off between FC/FH to better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used to cover any type of utilization, for the 1st inspection and the 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 changed whenever. Threshold and Interval are whichever occurs first between FC and FH for a 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). Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or 582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection which is requested at the inspection threshold of this Service Bulletin. CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 20,800 SR: 67,900 SR: 10,700 SR: 35,200 SR: 13,300 SR: 43,400 SR: 2,750 SR: 8,950 Config. 006 WV020 Series except WV022 LR: 19,000 LR: 128,900 LR: 9,850 LR: 66,700 LR: 10,600 LR: 72,300 LR: 2,500 LR: 17,000

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# @A330 SERVICE BULLETIN

CONDITION MANDATORY THRESHOLD MANDATORY INTERVAL RECOMMENDED THRESHOLD (02) RECOMMENDED INTERVAL (02) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) Flight Cycles (FC) Flight Hours (FH) SR: 20,500 SR: 67,100 SR: 10,600 SR: 34,700 SR: 13,000 SR: 42,400 SR: 2,700 SR: 8,850 Config. 006 WV022 and WV050 Series LR: 18,800 LR: 127,300 LR: 9,700 LR: 65,900 LR: 10,400 LR: 70,700 LR: 2,450 LR: 16,800 Table 1 : Accomplishment of this Service Bulletin is required within the following thresholds and intervals, whichever occurs first
NOTE: Grace Period for the threshold (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 21,180 FC - 63,560 FH NOTE: Grace Period for the interval (whichever occurs first) : - 24 months from the Service Bulletin Revision No. 05 issuance - 10,970 FC - 32,910 FH NOTE (02): Mandatory inspection is based on airworthiness considerations but we recommend to perform the inspection according to recommended thresholds and intervals to prevent large repairs. CONDITION SB MOD No. PROPOSED COMPLIANCE RECOMMENDED NOT BEFORE WHICHEVER OCCURS LATEST : Flight Cycles (FC) Flight Hours (FH) Config. 006 WV020 Series except WV022 A330-57-3098 21,000 60,600 Config. 006 WV022 and WV050 Series A330-57-3098 21,000 60,600

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever occurs latest. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

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# @A330 SERVICE BULLETIN
**CONF ALL F. APPROVAL The technical content of this document is approved under authority of Design Organization 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 573081-832-801-001: INSPECTION Get Access 5.00 On Aircraft Remove the Fastener on the LH Side 1.00 Remove the Fastener on the RH Side 1.00 Do a Special Detailed Inspection of the Hole at FR40, on the LH Side 1.00 Do a Special Detailed Inspection of the Hole at FR40, on the RH Side 1.00 Install the Fastener on the LH Side 1.00 Install the Fastener on the RH Side 1.00 Tests 1.00 Close-Up 6.00 TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00 **CONF 002 Task 573081-832-801-001: INSPECTION Get Access 5.00 On Aircraft Remove the Fastener on the LH Side 1.00 Remove the Fastener on the RH Side 1.00 Do a Special Detailed Inspection of the Hole at FR40, on the LH Side 1.00 Do a Special Detailed Inspection of the Hole at FR40, on the RH Side 1.00

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# @A330 SERVICE BULLETIN

Task 573081-832-801-001: INSPECTION Install the Fastener on the LH Side 1.00 Install the Fastener on the RH Side 1.00 Tests 1.00 Close-Up 6.00 TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00 **CONF 003 Task 573081-832-801-001: INSPECTION Get Access 5.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a Special Detailed Inspection of the Holes at FR40, on the LH Side 3.00 Do a Special Detailed Inspection of the Holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 1.00 Close-Up 6.00 TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00 **CONF 004 Task 573081-832-801-001: INSPECTION Get Access 12.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a Special Detailed Inspection of the Holes at FR40, on the LH Side 3.00 Do a Special Detailed Inspection of the Holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 005 Task 573081-832-801-001: INSPECTION Get Access 12.00
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# @A330 SERVICE BULLETIN

Task 573081-832-801-001: INSPECTION On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a Special Detailed Inspection of the Holes at FR40, on the LH Side 3.00 Do a Special Detailed Inspection of the Holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 2.00 Close-Up 15.00 TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 006 Task 573081-832-801-001: INSPECTION Get Access 5.00 On Aircraft Remove the Fasteners on the LH Side 2.00 Remove the Fasteners on the RH Side 2.00 Do a Special Detailed Inspection of the Holes at FR40, on the LH Side 3.00 Do a Special Detailed Inspection of the Holes at FR40, on the RH Side 3.00 Install the Fasteners on the LH Side 2.00 Install the Fasteners on the RH Side 2.00 Tests 1.00 Close-Up 6.00 TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 21 5

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# @A330 SERVICE BULLETIN Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3032 A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 002 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 003 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 004 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12
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# @A330 SERVICE BULLETIN
**CONF 005 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF 006 Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-11-00 28-25-00 32-12-00 53-35-13 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-06 Service Bulletin (SB) A330-57-3090 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571150 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : Kit 573081A01R00 Kit 573081A02R04 AIRBUS Material logistics 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 (2) Price and Availability

Kit 573081A01R00 Cost 278.00 USD Availability 30 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 573081A02R04 Cost 233.00 USD Availability 30 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.

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# @A330 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 573081A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 1 Screw 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 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 3 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required (2) Components None

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# @A330 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6. Tools necessary to do the check by ROTOTEST : Instrument : Rototest B588 and rotor standard. Probe RS35 dia. 6.2 mm (0.244 in.). Probe RS50 dia. 7.8 mm (0.307 in.). Calibration standard : 99A53003001001-103 and 99A53003001001-106. Supplier : ROHMANN Gmbh Rudolf Diesel Str.13 67227 FRANKENTHAL Tel.0 62 33 - 7881 Telex 468602 esro d GERMANY (2) Tools None (3) Special Tools None

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 573081-832-801-001 - INSPECTION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START A REFUEL/DEFUEL PROCEDURE. IN THIS SAFE AREA, DO NOT LET PERSONS: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR THE TASK. AIRCRAFT FUEL IS FLAMMABLE. WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The purpose of flow charts are for information only to show the various Inspection/Repair phases described in this Service Bulletin. Task Associated Data **CONF 001 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00 **CONF 002 Zone 141 142 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 29 5

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# @A330 SERVICE BULLETIN

Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 18.00 ELAPSED TIME (HOURS) 15.00 **CONF 003 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00 **CONF 004 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 005 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 43.00 ELAPSED TIME (HOURS) 36.00 **CONF 006 Zone 141 142 Access Panel 147AZ 148AZ Manpower TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 17.00

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# @A330 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11).

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# @A330 SERVICE BULLETIN (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - 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 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12
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# @A330 SERVICE BULLETIN (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11). (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - 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 003 (1) Subtask 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

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# @A330 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11). (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 34 5

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# @A330 SERVICE BULLETIN (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - 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 004 (1) Subtask 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 35 5

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

# @A330 SERVICE BULLETIN (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11). (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - 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 005 (1) Subtask 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML)
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 36 5

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# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11). (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12). (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 37 5

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# @A330 SERVICE BULLETIN
**CONF 006 (1) Subtask 573081-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 20-21-11 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11 51-76-12 (a) For the specification of the material numbers (Mat. No.) refer to the CML. (b) Clean the surfaces to be sealed with : Solvent General Purpose 11-026 As required (c) Use a non-metallic spatula to remove the sealant and clean the areas with : Solvent General Purpose 11-026 As required (d) Drill and deburr the holes (Refer to SRM 51-44-11). (e) Remove and install the fasteners (Refer to SRM 51-42-11). (f) Torque the standard threaded fasteners (Refer to AMM 20-21-11). (g) 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. (h) Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 38 5

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# @A330 SERVICE BULLETIN (i) On all the fasteners to be installed (wet assembly), apply : Fuel Tank Sealant Polysulfide 09-001 As required (j) Install all the fasteners with : Corrosion Inhibiting fillet Consistency 09-016 As required (2) Subtask 573081-839-001-001 - 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 573081-941-001-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 39 5

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# @A330 SERVICE BULLETIN
**CONF 002 (1) Subtask 573081-941-001-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). **CONF 003 (1) Subtask 573081-941-001-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 40 5

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# @A330 SERVICE BULLETIN
**CONF 004 (1) Subtask 573081-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). **CONF 005 (1) Subtask 573081-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 28-00-00, Page Block 301 28-10-00, Page Block 301 28-25-00, Page Block 301 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 41 5

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# @A330 SERVICE BULLETIN (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301). (f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (g) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and (Refer to AMM 28-10-00 Page Block 301). **CONF 006 (1) Subtask 573081-941-001-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 32-12-00, Page Block 201 53-35-13, Page Block 401 57-17-11, Page Block 401 (a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201). (b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block 201). (c) Put the access platform(s) in position. (d) Remove the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (e) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 42 5

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# @A330 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 573081-010-001-001 - Remove the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove : Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 43 5

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# @A330 SERVICE BULLETIN (2) Subtask 573081-010-002-001 - Remove the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove : Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw Item (7) Discard
or 1 screw Item (10) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 44 5

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# @A330 SERVICE BULLETIN (3) Subtask 573081-832-006-001 - Do a Special Detailed Inspection of the Hole at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3090 Fig. A-FBAAA Area to Inspect Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 (a) For the inspection area, refer to Fig. A-FBAAA Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet 01, Fig. A-FFAAA Sheet 02

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3090 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 001 Install the Fastener on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 45 5

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# @A330 SERVICE BULLETIN (4) Subtask 573081-832-007-001 - Do a Special Detailed Inspection of the Hole at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3090 Fig. A-FBAAA Area to Inspect Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 (a) For the inspection area, refer to Fig. A-FBAAA Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet 01, Fig. A-FFAAA Sheet 02

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3090 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 001 Install the Fastener on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 46 5

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# @A330 SERVICE BULLETIN (5) Subtask 573081-410-001-001 - Install the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 573081A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 47 5

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# @A330 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 9:
a Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11. b Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 9: Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 nut NAS1726-5E Item 9 1 screw NSA5357-5-18 Item 10 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 48 5

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# @A330 SERVICE BULLETIN (6) Subtask 573081-410-002-001 - Install the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 573081A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 49 5

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# @A330 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 9:
a Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11. b Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 9: Install: Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 1 nut NAS1726-5E Item 9 1 screw NSA5357-5-18 Item 10 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 50 5

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# @A330 SERVICE BULLETIN
**CONF 002 (1) Subtask 573081-010-001-002 - Remove the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove : Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw Item (7) Discard or 1 screw Item (10) Discard
or 1 screw Item (11) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 51 5

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# @A330 SERVICE BULLETIN (2) Subtask 573081-010-002-002 - Remove the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove : Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw Item (7) Discard
or 1 screw Item (10) Discard
or 1 screw Item (11) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 52 5

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# @A330 SERVICE BULLETIN (3) Subtask 573081-832-006-002 - Do a Special Detailed Inspection of the Hole at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAB Area to Inspect Sheet 01 Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAB Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet 01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 002 Install the Fastener on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 53 5

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# @A330 SERVICE BULLETIN (4) Subtask 573081-832-007-002 - Do a Special Detailed Inspection of the Hole at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAB Area to Inspect Sheet 01 Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAB Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2). (b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet 01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 002 Install the Fastener on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 54 5

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# @A330 SERVICE BULLETIN (5) Subtask 573081-410-001-002 - Install the Fastener on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 573081A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 55 5

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# @A330 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Do a check of the diameter of the hole, refer to table 9 and 10 of the SRM 51-44-11. <1> If the diameter do not respect the tolerance of the table 9: <a> The diameter is included between the First oversize and the Second oversize: - Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
<b> The diameter is included between the Nominal diameter and the First oversize: - Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 56 5

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# @A330 SERVICE BULLETIN <2> If the diameter respect the tolerance of the table 9: <a> Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8: Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw EN6115V5-18 Item 11 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 573081-410-002-002 - Install the Fastener on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 57 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 573081A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 7 NSA5359-5-18 1 Screw 8 NSA5368PD516B 1 Washer 9 NAS1726-5E 1 Nut 10 NSA5357-5-18 1 Screw 11 EN6115V5-18 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAB Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 58 5

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# @A330 SERVICE BULLETIN (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Do a check of the diameter of the hole, refer to table 9 and 10 of the SRM 51-44-11. <1> If the diameter do not respect the tolerance of the table 9: <a> The diameter is included between the First oversize and the Second oversize: - Ream hole to second oversize, refer to the table 10 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5359-5-18 Item 7 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
<b> The diameter is included between the Nominal diameter and the First oversize: - Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11 and install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 59 5

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# @A330 SERVICE BULLETIN <2> If the diameter respect the tolerance of the table 9: <a> Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw NSA5357-5-18 Item 10 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8: Install: Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 1 screw EN6115V5-18 Item 11 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. **CONF 003 (1) Subtask 573081-010-001-003 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 60 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard
or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 61 5

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# @A330 SERVICE BULLETIN
1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 573081-010-002-003 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard
or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 62 5

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# @A330 SERVICE BULLETIN (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 573081-832-006-003 - Do a Special Detailed Inspection of the Holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 63 5

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# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 003 Install the Fasteners on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 573081-832-007-003 - Do a Special Detailed Inspection of the Holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 64 5

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# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 003 Install the Fasteners on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 573081-410-001-003 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 65 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 66 5

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# @A330 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 67 5

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# @A330 SERVICE BULLETIN (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 573081-410-002-003 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 68 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 69 5

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# @A330 SERVICE BULLETIN

1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. **CONF 004 (1) Subtask 573081-010-001-003 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 70 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard
or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 71 5

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# @A330 SERVICE BULLETIN
1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 573081-010-002-003 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard
or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 72 5

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# @A330 SERVICE BULLETIN (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 573081-832-006-003 - Do a Special Detailed Inspection of the Holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 73 5

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

# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 003 Install the Fasteners on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 573081-832-007-003 - Do a Special Detailed Inspection of the Holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 74 5

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

# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 003 Install the Fasteners on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 573081-410-001-003 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 75 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 76 5

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# @A330 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 77 5

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# @A330 SERVICE BULLETIN (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 573081-410-002-003 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 78 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 79 5

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# @A330 SERVICE BULLETIN

1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. **CONF 005 (1) Subtask 573081-010-001-003 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 80 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard
or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 81 5

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# @A330 SERVICE BULLETIN
1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 573081-010-002-003 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard
or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 82 5

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

# @A330 SERVICE BULLETIN (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 573081-832-006-003 - Do a Special Detailed Inspection of the Holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 83 5

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# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 003 Install the Fasteners on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 573081-832-007-003 - Do a Special Detailed Inspection of the Holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 84 5

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# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 003 Install the Fasteners on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 573081-410-001-003 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 85 5

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

# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 86 5

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# @A330 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 87 5

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

# @A330 SERVICE BULLETIN (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 573081-410-002-003 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 88 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 89 5

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# @A330 SERVICE BULLETIN

1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. **CONF 006 (1) Subtask 573081-010-001-003 - Remove the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 90 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard
or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 91 5

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

# @A330 SERVICE BULLETIN
1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (2) Subtask 573081-010-002-003 - Remove the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Depending on fastener installed, remove from the hole A : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (15) Discard 1 nut Item (9) Discard
or 1 screw Item (13) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 92 5

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

# @A330 SERVICE BULLETIN (b) Depending on fastener installed, remove from the hole B : Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw Item (16) Discard 1 nut Item (9) Discard or 1 screw Item (14) Discard 1 nut Item (9) Discard and if installed 1 washer Item (8) Discard (c) Remove the sealant and clean the areas with: Solvent General Purpose 11-026 As required (3) Subtask 573081-832-006-003 - Do a Special Detailed Inspection of the Holes at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 93 5

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

# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-001 003 Install the Fasteners on the LH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 573081-832-007-003 - Do a Special Detailed Inspection of the Holes at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 3.00 Minimum number of person 1 Subtask elapsed time 3.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Service Bulletin (SB) A330-57-3098 Fig. A-FBAAC Area to Inspect Sheet 01 Fig. A-FFAAC Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) For the inspection area, refer to Fig. A-FBAAC Sheet 01

. At the threshold given in the Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 94 5

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

# @A330 SERVICE BULLETIN (b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAC Sheet 01, Fig. A-FFAAC Sheet 02, Fig. A-FFAAC Sheet 03

. Do a rotating probe inspection, refer to NTM 51-10-01 Part 6. 1 If no crack is found: - Accomplish Service Bulletin No. A330-57-3098 at the threshold given in Planning Information Paragraph E.(2).
or - Refer to SUBTASK 573081-410-002 003 Install the Fasteners on the RH Side

. 2 If crack found: - Contact Airbus before next flight. (c) For the inspection report, refer to Appendix 01 - Inspection Report . (5) Subtask 573081-410-001-003 - Install the Fasteners on the LH Side Work Zones and Access Panels Zone Access/Work location 141 Access Panel 147AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 95 5

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

# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12 Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 96 5

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# @A330 SERVICE BULLETIN and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 97 5

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# @A330 SERVICE BULLETIN (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. (6) Subtask 573081-410-002-003 - Install the Fasteners on the RH Side Work Zones and Access Panels Zone Access/Work location 142 Access Panel 148AZ Work location Frame 40 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 573081A02R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NSA5368PD516B 2 Washer 9 NAS1726-5E 2 Nut 13 EN6115V5-14 1 Screw 14 EN6115V5-9 1 Screw 15 NSA5357-5-14 1 Screw 16 NSA5357-5-9 1 Screw 17 EN6115V5-10 1 Screw Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Inhibiting fillet Consistency 09-016 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-06 Part 6 Structural Repair Manual (SRM) 51-24-00 51-44-11 51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 98 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAC Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Clean the hole with: Solvent General Purpose 11-026 As required (b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11 1 If the diameter do not respect the tolerance of the table 8:
a Ream hole to First oversize, refer to the table 9 of the SRM 51-44-11. b Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-14 Item 15 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required

c Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw NSA5357-5-9 Item 16 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
2 If the diameter respect the tolerance of the table 8:
a Install for the hole A: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 99 5

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# @A330 SERVICE BULLETIN

1 screw EN6115V5-14 Item 13 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required
b Install for the hole B: Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02 1 screw EN6115V5-9 Item 14 or 1 screw EN6115V5-10 Item 17 NOTE: Depending on the grip length measured on aircraft install the screw Item 14 or the screw Item 17. 1 nut NAS1726-5E Item 9 and if necessary, use 1 washer NSA5368PD516B Item 8 And install with: Fuel Tank Sealant Polysulfide 09-001 As required (c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12: Corrosion Inhibiting fillet Consistency 09-016 As required (d) Do a repetitive inspection at interval given in Planning Information Paragraph E.(2), refer to NTM 51-10-06 Part 6. **CONF ALL D. TEST **CONF 001 (1) Subtask 573081-710-001-002 - Test Manpower Resources Skills NON SPECIFIC DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 100 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 002 (1) Subtask 573081-710-001-002 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 003 (1) Subtask 573081-710-001-002 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 101 5

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# @A330 SERVICE BULLETIN
**CONF 004 (1) Subtask 573081-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 005 (1) Subtask 573081-710-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301). (c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501). (d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF 006 (1) Subtask 573081-710-001-002 - Test Manpower Resources Skills NON SPECIFIC

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 102 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501 28-25-00, Page Block 301 57-17-11, Page Block 401 (a) Install the access cover 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block 401). (b) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11 Page Block 401). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 002 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 103 5

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# @A330 SERVICE BULLETIN (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 003 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 004 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition.
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 104 5

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# @A330 SERVICE BULLETIN (e) Remove the access platform(s). **CONF 005 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s). **CONF 006 (1) Subtask 573081-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201 53-35-13, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH side (Refer to AMM 53-35-13 Page Block 401). (c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201). (d) Restore the systems and the aircraft to normal operating condition. (e) Remove the access platform(s).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 105 5

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# @A330 SERVICE BULLETIN

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 G_SB_573081_5_BAAA_01_02 Figure A-FBAAA - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 106 5

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# @A330 SERVICE BULLETIN

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 G_SB_573081_5_BAAB_01_01 Figure A-FBAAB - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 107 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

LH SIDE SHOWN RH SIDE SYMMETRICAL FR40 FR47

− Z141 Z142 

### A **B B** 



## A

DATUM Y2390 Y1959

AREA TO INSPECT STGR1 RIB1 FR40

**F W**  **D**

G_SB_573081_5_BAAC_01_00 VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 

## B

Figure A-FBAAC - Sheet 01 Area to Inspect
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 108 5

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# @A330 SERVICE BULLETIN

**CONF 001

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAA. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION
FINDING YES

REFER TO FIGURE A−FFAAA SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 573081−010−001−001 AND ON THE RH SIDE REFER TO SUBTASK 573081−010−002−001

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 573081−832−007−001 REFER TO SUBTASK 573081−832−006−001 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

G_SB_573081_5_FAAA_01_01

Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 109 5

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# @A330 SERVICE BULLETIN

**CONF 001

OR

DO A CHECK OF THE DIAMETER OF THE HOLE

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 9 OF THE SRM 51−44−11. FROM FIGURE A−FFAAA SHEET 1

CLEAN THE HOLE

NO YES

INSTALL NEW SAME DIAMETER FASTENER :

NSA5357−5−18 AND NAS1726−5E. REFER TO THE TABLE 9 OF THE SRM 51−44−11. REAM HOLE TO SECOND OVERSIZE. REFER TO THE TABLE 10 OF THE SRM 51−44−11.

INSTALL SECOND OVERSIZE FASTENER : NSA5359−5−18, NSA5368PD516B AND

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A330−57−3090 BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

APPLY MOD SERVICE BULLETIN No. A330−57−3090

NAS1726−5E.

QUESTION ACTION
FINDING

G_SB_573081_5_FAAA_02_01 Figure A-FFAAA - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 110 5

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# @A330 SERVICE BULLETIN

**CONF 002

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAB. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION
FINDING YES

REFER TO FIGURE A−FFAAB SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 573081−010−001−002 AND ON THE RH SIDE REFER TO SUBTASK 573081−010−002−002

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 573081−832−007−002 REFER TO SUBTASK 573081−832−006−002 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

G_SB_573081_5_FAAB_01_01

Figure A-FFAAB - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 111 5

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# @A330 SERVICE BULLETIN

**CONF 002

OR

DO A CHECK OF THE DIAMETER OF THE HOLE

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAB SHEET 1

CLEAN THE HOLE

NO YES IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A330−57−3098 BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

APPLY MOD SERVICE BULLETIN No. A330−57−3098

QUESTION ACTION
FINDING REFER TO FIGURE A−FFAAB SHEET 3 INSTALL NEW SAME DIAMETER FASTENER : EN6115V5−18 AND NAS1726−5E. REFER TO THE TABLE 8 OF THE SRM 51−44−11.

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6.

G_SB_573081_5_FAAB_02_01 Figure A-FFAAB - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 112 5

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# @A330 SERVICE BULLETIN

**CONF 002

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH

THE TABLE 9 AND 10 OF THE SRM 51−44−11. FROM FIGURE A−FFAAB SHEET 2

NO YES

INSTALL NEW SAME DIAMETER FASTENER :

NSA5357−5−18 AND NAS1726−5E. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

REAM HOLE TO SECOND OVERSIZE. REFER TO THE TABLE 10 OF THE SRM 51−44−11.

INSTALL SECOND OVERSIZE FASTENER : NSA5359−5−18, NSA5368PD516B AND

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. NAS1726−5E.

QUESTION ACTION
FINDING OR

FIRST OVERSIZE DIAMETER

REAM HOLE TO FIRST OVERSIZE. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

INSTALL FIRST OVERSIZE FASTENER : NSA5357−5−18 AND NAS1726−5E.

DIAMETER NOMINAL DIAMETER

FIRST OVERSIZE SECOND OVERSIZE

G_SB_573081_5_FAAB_03_01 Figure A-FFAAB - Sheet 03 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 113 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

CRACK REMOVE THE FASTENERS ON THE LH SIDE DO A SPECIAL DETAILED INSPECTION OF THE HOLE ON KEEL BEAM AT FRAME 40. REFER TO FIGURE A−FBAAC. FOR THE THRESHOLD, REFER TO PLANNING INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION ACTION
FINDING YES

REFER TO FIGURE A−FFAAC SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER AIRBUS ADVISE REFER TO SUBTASK 573081−010−001−003 AND ON THE RH SIDE REFER TO SUBTASK 573081−010−002−003

DO A SPECIAL DETAILED INSPECTION OF REFER TO SUBTASK 573081−832−007−003 REFER TO SUBTASK 573081−832−006−003 THE HOLE AT FR40 ON THE LH SIDE AND DO A SPECIAL DETAILED INSPECTION OF THE HOLE AT FR40 ON THE RH SIDE

G_SB_573081_5_FAAC_01_02

Figure A-FFAAC - Sheet 01 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 114 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

OR

DO A CHECK OF THE DIAMETER OF THE HOLES

DIAMETER IN TOLERANCE OF TRANSITION FIT FASTENER WITH THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAC SHEET 1

CLEAN THE HOLES

NO YES IT IS RECOMMENDED NOT TO APPLY MOD SERVICE BULLETIN No. A330−57−3098 BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING INFORMATION PARAGRAPH TABLE 2

APPLY MOD SERVICE BULLETIN No. A330−57−3098

QUESTION ACTION
FINDING REFER TO FIGURE A−FFAAC SHEET 3 REFER TO FIGURE A−FFAAC SHEET 3

G_SB_573081_5_FAAC_02_03 Figure A-FFAAC - Sheet 02 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 115 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

FROM FIGURE A−FFAAC SHEET 2

INSTALL NEW SAME DIAMETER FASTENERS : EN6115V5−14 AND NAS1726−5E FOR HOLE A. REAM HOLES TO FIRST OVERSIZE. REFER TO THE TABLE 9 OF THE SRM 51−44−11.

INSTALL FIRST OVERSIZE FASTENERS : NSA5357−5−14 AND NAS1726−5E FOR HOLE A.

DO A SEALING OF THE FASTENERS. REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION AT INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2). REFER TO NTM 51−10−01 PART 6. INSTALL NSA5357−5−9 AND

QUESTION ACTION
FINDING NAS1726−5E FOR HOLE B. INSTALL EN6115V5−9 OR EN6115V5−10 AND NAS1726−5E FOR HOLE B. REFER TO THE TABLE 8 OF THE SRM 51−44−11. FROM FIGURE A−FFAAC SHEET 2

G_SB_573081_5_FAAC_03_02 Figure A-FFAAC - Sheet 03 Flow Chart
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 116 5

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# @A330 SERVICE BULLETIN

**CONF 001

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

VIEW FROM INSIDE CENTER TANK AT FR40 

### C

G_SB_573081_5_CAAA_01_01 Figure A-FCAAA - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 117 5

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# @A330 SERVICE BULLETIN

**CONF 001

Y1959

DATUM

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED OR DEPENDS ON AIRCRAFT CONFIGURATION F

APPLY MAT No. 09−001

F VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY FR40

**NOTE:** 01 (7) (8) (9) 7 8 9 (10) (8) (9) 10 8 9

(8) 8 01

STGR1



## C **F W**  **D**

G_SB_573081_5_CAAA_02_01 Figure A-FCAAA - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 118 5

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# @A330 SERVICE BULLETIN

**CONF 002

LH SIDE SHOWN RH SIDE SYMMETRICAL Y1959

STGR1 FR40DATUM FR40 FR47

− Z141 Z142 

### A **B B** 



## A

**B**

VIEW FROM INSIDE CENTER TANK AT FR40 

### C

G_SB_573081_5_CAAB_01_01 Figure A-FCAAB - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 119 5

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# @A330 SERVICE BULLETIN

**CONF 002

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED OR DEPENDS ON AIRCRAFT CONFIGURATION

APPLY MAT No. 09−001

F VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY **NOTE:** 01 (7) (8) (9) 7 8 9 (10) (8) (9) 10 8 9

(8) 8 01

STGR1



## C OR(11) (8) (9) 11 8 9 Y1959
DATUM

F FR40

**F W**  **D**

G_SB_573081_5_CAAB_02_01 Figure A-FCAAB - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 120 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

LH SIDE SHOWN RH SIDE SYMMETRICAL FR40 FR47

− Z141 Z142 

### A **B B** 



## A

DATUM Y2390 Y1959

STGR1 RIB1 FR40

**F W**  **D**

VIEW FROM INSIDE CENTER TANK AT FR40 

## B

G_SB_573081_5_CAAC_01_00 

### C

Figure A-FCAAC - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 121 5

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# @A330 SERVICE BULLETIN

**CONF 003 thru 006

F F HOLE B HOLE A

VIEW INSIDE CENTER TANK AT FR40

HEAD ON HIDDEN SIDE FASTENERS NOT AFFECTED APPLY MAT No. 09−001

F **NOTE:** 01 01

OR DEPENDS ON AIRCRAFT CONFIGURATION (9) (16) 9 16 (9) (14) 9 14 OR DEPENDS ON AIRCRAFT CONFIGURATION (9) (15) 9 15 (9) (13) 9 13

**F W**  **D** (8) 8 (8) 8 (8) 8 (8) 8



## D

ITEM AND ONLY IF NECESSARY (8) 8 OR (9) (14) 9 17 (8) 8

G_SB_573081_5_CAAC_02_02 Figure A-FCAAC - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 122 5

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# @A330 SERVICE BULLETIN Appendix 01 - Inspection Report **CONF ALL (1) The results of the inspection, including no findings, replacement or action to be done, must be forwarded to Airbus department SEES1, on the attached inspection report sheet.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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# @A330 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF 001 thru 002

SIDE

LH
RH NO CRACK CRACK DIAMETER

LH
RH

LH
RH HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE SECOND OVERSIZE INSTALLATION OF THE FASTENER AT:

PLEASE PRECISE OTHER FINDINGS : **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3081

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

G_SB_573081_5_RAAA_01_00 Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 2 5

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# @A330 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF 003 thru 006

SIDE NO CRACK CRACK DIAMETER

LH
RH

LH
RH HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE INSTALLATION OF THE FASTENER AT: HOLE A HOLE A RH RH LH LH HOLE B HOLE B

HOLE A HOLE B

HOLE A HOLE A HOLE B HOLE B

PLEASE PRECISE OTHER FINDINGS : **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3081

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

G_SB_573081_5_RAAB_01_00 Figure A-FRAAB - Sheet 01 Inspection Report
DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 3 5

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT). MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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

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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081 REVISION No.: 05 - Nov 13/12 Page: 1 5

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