@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

ACCOMPLISHMENT INSTRUCTIONS

TASK 573081- 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

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

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

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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

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

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

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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A330

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

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

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

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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

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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

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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

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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

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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

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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

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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.

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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

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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

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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

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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

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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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 17

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:

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.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 18

5

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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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 19

5

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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 20

5

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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 22

5

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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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 23

5

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@A330

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 24

5

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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.

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

REVISION No.: 05 - Nov 13/12 Page: 25

5

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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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

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(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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

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This Page Intentionally Left Blank

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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

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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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

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**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).

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

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(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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(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

DATE: Oct 30/03 SERVICE BULLETIN No.: A330-57-3081

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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

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(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

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(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)

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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.

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**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).

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(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).

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**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

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**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).

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(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

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**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

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

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

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

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

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

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

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

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

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

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

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

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

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

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: 61

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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: 74

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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: 75

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: 76

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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

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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

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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

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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

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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

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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: 83

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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

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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

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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

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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: 88

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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

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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

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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: 92

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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: 93

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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: 94

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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: 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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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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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

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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

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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

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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

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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

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