@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION

IN THE JUNCTION KEEL BEAM FITTING AT FR.40

MODIFICATION No.: 56467S18944

This page transmits Revision No.02 of Service Bulletin No.A330-57-3098

ADDITIONAL WORK

**CONF ALL

NOTE: No additional work is required by this revision for aircraft modified by revision No. 01 of

this Service Bulletin.

Additional work is required by this revision for aircraft modified at initial issue.

REASON

Revision No. 02 issued to update the installation of the bolts and the washers.

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-FSAAA Minor editorial or document structure change N

Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N

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REVISION No.: 02 - Jun 15/11 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FSBAA Minor editorial or document structure change N

Fig. A-FSBAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

CONF 002 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

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

REVISION No.: 02 - Jun 15/11 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Kit 573098A01R03 Minor editorial or document structure change N

Kit 573098A03R04 Minor editorial or document structure change N

Supplementary Kit 573098A01S01 Minor editorial or document structure change N

Supplementary Kit 573098A01S02 Minor editorial or document structure change N

Supplementary Kit 573098A03S01 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLA01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 573098- 831-801-001-

MODIFICATION

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Task associated data - 002 Minor editorial or document structure change N

Subtask 573098-831-001-001 Minor editorial or document structure change N

Subtask 573098-900-002-001 Minor editorial or document structure change N

Subtask 573098-831-001-001 Minor editorial or document structure change N

Subtask 573098-900-002-001 Minor editorial or document structure change N

Subtask 573098-831-003-001 Minor editorial or document structure change N

Subtask 573098-831-003-001 Minor editorial or document structure change N

Subtask 573098-010-001-001 Minor editorial or document structure change N

Subtask 573098-831-005-001 Minor editorial or document structure change N

Subtask 573098-831-006-001 Minor editorial or document structure change N

Subtask 573098-410-001-001 Minor editorial or document structure change N

Subtask 573098-010-001-002 Minor editorial or document structure change N

Subtask 573098-831-005-002 Minor editorial or document structure change N

Subtask 573098-831-010-001 Minor editorial or document structure change N

Subtask 573098-831-011-001 Minor editorial or document structure change N

Subtask 573098-410-001-001 Minor editorial or document structure change N

Subtask 573098-831-014-001 Minor editorial or document structure change N

Subtask 573098-831-014-001 Minor editorial or document structure change N

Subtask 573098-831-015-001 Minor editorial or document structure change N

Subtask 573098-831-015-001 Minor editorial or document structure change N

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

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REVISION TRANSMITTAL SHEET

TASK 573098- 839-801-001-Administrative

- ADDITIONAL WORK

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Task associated data - 002 Minor editorial or document structure change N

Subtask 573098-839-001-001 Minor editorial or document structure change N

Subtask 573098-839-001-001 Minor editorial or document structure change N

Subtask 573098-839-002-001 Minor editorial or document structure change N

Subtask 573098-839-002-002 Minor editorial or document structure change N

Fig. A-FCAAA Minor editorial or document structure change N

Fig. A-FCAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FDAAA Minor editorial or document structure change N

Fig. A-FDAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBAAA Minor editorial or document structure change N

Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBAAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBBAA Minor editorial or document structure change N

Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBBAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBCAA Minor editorial or document structure change N

Fig. A-FBCAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBCAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBCAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBCAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBCAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBDAA Minor editorial or document structure change N

Fig. A-FBDAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBDAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBDAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBDAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBDAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBEAA Minor editorial or document structure change N

Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBEAA Sheet 04 Minor editorial or document structure change N

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

REVISION No.: 02 - Jun 15/11 Page: 4

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FBEAA Sheet 05 Minor editorial or document structure change N

Fig. A-FBFAA Minor editorial or document structure change N

Fig. A-FBFAA Sheet 01 Minor editorial or document structure change N

Fig. A-FBFAA Sheet 02 Minor editorial or document structure change N

Fig. A-FBFAA Sheet 03 Minor editorial or document structure change N

Fig. A-FBFAA Sheet 04 Minor editorial or document structure change N

Fig. A-FBFAA Sheet 05 Minor editorial or document structure change N

APPENDIX 01 - Inspection Report

APPENDIX CONTENT Minor editorial or document structure change N

Fig. A-FAAAA Minor editorial or document structure change N

Fig. A-FAAAA Sheet 01 Minor editorial or document structure change N

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 extend the effectivity to aircraft post mod. No. 44360S13013 and pre mod.

No. 49202S16307 with specific Kit A03 and to amend accomplishment instruction for hole 5 without

bush installed.

The ADDITIONAL WORK is for aircraft in Config. 01 and is only necessary on those MSN on which a

crack was detected at hole 5 before oversizing of the keel beam (Refer for details to para. 3.B (1)(b)

step 3).

REVISION SEQUENCE

ORIGINAL: Aug 30/07

REVISION No. : 02 - Jun 15/11

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

REVISION No.: 02 - Jun 15/11 Page: 5

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

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

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION

IN THE JUNCTION KEEL BEAM FITTING AT FR.40

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 56467S18944

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating

at the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091

(WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT)

production solution configuration.

The intention of the production solution was also proposed by Service Bulletin No. A330-57-3032 for

retrofit.

The structural analysis has led to the issue of the Inspection Service Bulletin A330-57-3081 (WINGS

- CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40

(UNREPAIRED AIRCRAFT)).

The Inspection Service Bulletin requires a detailed inspection on A330 aircraft pre Mod. No.

55306S18660 (FUSELAGE-CENTER FUSELAGE-REPLACE THE ONE-PIECE FITTING BY A SPLICE

AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) including mandatory and recommended

thresholds and repetitive inspection intervals.

This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam

fitting at FR40.

Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin

A330-57-3081 for aircraft on which Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE -

REINFORCE SECTION 15/21) is not embodied.ALI 57.11.63 is created for Post Mod. SB configuration

(Post Mod. No. 56467S18944).

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

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SERVICE BULLETIN

SUMMARY

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573098A01R03 2 878.00 Bolts, nuts, washers

Supplementary kit

573098A01S01

2 182.00 Bolts

Supplementary kit

573098A01S02

2 1,180.00 Bolts, washers

TOTAL 2,240.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573098A03R04 2 5,580.00 Plugs, bolts, nuts, washers

Supplementary kit

573098A03S01

2 1,460.00 Bolts, washers

TOTAL 7,040.00

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

ACA ACI AEA AFR ALK AZA BMA BTV CPA CRL CYP DGA EDW

EIN FWI GFA GIA GRL HDA HVN I2L IAC JST KAL KKK LTU

MAS MON OHY PAL QAF QTR SAS SGX STZ SWR TAM TAP TCX

THA THY TSC UAE USA VKG VOZ XLF

NOTE: This Service Bulletin is only applicable to aircraft on which modification No.

41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY

ITEMS) is embodied and modification No. 49202S16307 (FUSELAGE - CENTER

FUSELAGE - REINFORCE SECTION 15/21) is not embodied.

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

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SERVICE BULLETIN

SUMMARY

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.005

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 573098-831-801-001: MODIFICATION

TOTAL MANHOURS 65.00

ELAPSED TIME (HOURS) 38.00

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF 002

Task 573098-831-801-001: MODIFICATION

TOTAL MANHOURS 93.50

ELAPSED TIME (HOURS) 42.00

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

APPENDICES

**CONF ALL

APPENDIX 01 - Inspection Report

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

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SERVICE BULLETIN

SUMMARY

**CONF 001

Z141−142

FR40

FR47

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STGR 1

Y−1959

FR40 DATUM

STGR1

Y1959

FASTENERS TO BE REPLACED OR MODIFIED FOR CONFIG. 01 (POST MOD. 41652 AND PRE MOD. 44360)

B

C

A

F

W

D

C

A

B

B

G_SB_573098_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

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

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SERVICE BULLETIN

SUMMARY

**CONF 002

Z141−142

FR40

FR47

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

VIEW INSIDE CENTER TANK AT FR40

STGR 1

Y−1959

FR40 DATUM

STGR1

Y1959

A

B

C

F

W

D

C

A

B

B

FASTENERS TO BE REPLACED OR MODIFIED FOR CONFIG. 02 (POST MOD. 41652 AND POST MOD. 44360)

G_SB_573098_5_SBAA_01_00

Figure A-FSBAA - Sheet 01

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

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

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

REVISION No.: 02 - Jun 15/11 Page: 6

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION

IN THE JUNCTION KEEL BEAM FITTING AT FR.40

MODIFICATION No.: 56467S18944

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin is only applicable to aircraft on which modification

No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340

COMMONALITY ITEMS) is embodied and modification No. 49202S16307

(FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is not

embodied.

(1) Models

330-202 330-203 330-223 330-243 330-301 330-321 330-322 330-323

330-341 330-342 330-343

(2) Effectivity by MSN

0113 0116 0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165

0171-0172 0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206

0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251

0253-0256 0258-0259 0261-0262 0265-0267 0269 0271-0272 0275-0277 0279 0281

0283-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0317

0320 0322-0324 0326 0328 0330 0333-0334 0337-0340 0342-0346 0348-0351 0353

0356-0358 0361-0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386

0388-0389 0392-0393 0396-0398 0400-0401 0403-0405 0407-0409 0412 0418-0423

0425 0427-0428 0432 0437 0439 0441 0443-0444 0448 0451-0452 0454-0456 0458

0461-0463 0465-0466 0469 0472-0473 0476-0477 0479-0481 0484 0486-0487

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SERVICE BULLETIN

0489-0491 0493-0494 0496-0498 0500-0510 0512 0522

(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

ACA 0277 0279 0284 0344 0400 0408 0412 0419

ACI 0507 0510

AEA 0461

AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503

ALK 0303 0306 0311 0313 0404

AZA 0272 0339

BMA 0398 0401

BTV 0205 0330

CPA 0113 0118 0121 0155 0244 0386 0389 0393 0418 0420 0421 0423

0439

CRL 0285 0320

CYP 0505

DGA 0240

EDW 0291

EIN 0269 0397

FWI 0253

GFA 0276 0281 0286 0287 0334 0340

GIA 0138 0140 0144 0148 0153 0165

GRL 0230

HDA 0132 0234 0405 0479 0512

HVN 0255 0262 0275 0294 0299 0366

I2L 0211

IAC 0353 0362

JST 0506 0508 0522

KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350

0351 0368 0425 0428 0484 0490

KKK 0343 0358 0364

LTU 0120 0127 0171 0403 0432 0444 0454 0469 0476 0493

MAS 0116 0119 0290 0296 0300

MON 0261 0265

OHY 0143

PAL 0183 0184 0188 0189 0191 0198 0200 0203

QAF 0487

QTR 0441 0473 0489

SAS 0496 0497

SGX 0407

STZ 0324

SWR 0229 0249 0288 0322

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SERVICE BULLETIN

OPERATOR MSN

TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486

TAP 0181 0195 0223 0305 0308 0312 0317

TCX 0254 0266 0301 0427 0456

THA 0122 0209 0224 0231 0346

THY 0463 0504

TSC 0177 0250 0271 0369 0480

UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0382

0384 0392 0396 0409 0437 0451 0452 0455 0462 0491 0494 0509

USA 0315 0323 0333 0337 0342 0370 0375 0380 0388

VKG 0309 0349 0356 0357

VOZ 0365 0372

XLF 0501

(4) Configuration by MSN

MSN CONFIGURATION

0113 0116 0118 0119 0120 0121 0122 0127 0132 0138 0140

0143 0144 0148 0153 0155 0162 0165 0171 0172

001

0177 0181 0183 0184 0188 0189 0191 0195 0198 0200 0203

0205 0206 0209 0211 0219 0222 0223 0224 0226 0229 0230

0231 0232 0234 0238 0240 0241 0244 0247 0248 0249 0250

0251 0253 0254 0255 0256 0258 0259 0261 0262 0265 0266

0267 0269 0271 0272 0275 0276 0277 0279 0281 0283 0284

0285 0286 0287 0288 0290 0291 0293 0294 0295 0296 0299

0300 0301 0303 0305 0306 0308 0309 0311 0312 0313 0314

0315 0316 0317 0320 0322 0323 0324 0326 0328 0330 0333

0334 0337 0338 0339 0340 0342 0343 0344 0345 0346 0348

0349 0350 0351 0353 0356 0357 0358 0361 0362 0364 0365

0366 0368 0369 0370 0372 0375 0380 0382 0384 0386 0388

0389 0392 0393 0396 0397 0398 0400 0401 0403 0404 0405

0407 0408 0409 0412 0418 0419 0420 0421 0422 0423 0425

0427 0428 0432 0437 0439 0441 0443 0444 0448 0451 0452

0454 0455 0456 0458 0461 0462 0463 0465 0466 0469 0472

0473 0476 0477 0479 0480 0481 0484 0486 0487 0489 0490

0491 0493 0494 0496 0497 0498 0500 0501 0502 0503 0504

0505 0506 0507 0508 0509 0510 0512 0522

002

(5) Configuration definition

**CONF 001

Config. 01 concerns aircraft on which modification No. 44360S13013 (WING - CENTER

WING - MODIFY FR40 AND FRONT SPAR) is not embodied.

**CONF 002

Config. 02 concerns aircraft on which modification No. 44360S13013 (WING - CENTER

WING - MODIFY FR40 AND FRONT SPAR) is embodied.

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

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(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 573098A01R03 2

Supplementary kit 573098A01S01 2

Supplementary kit 573098A01S02 2

Consumable CMLA01 As required

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 573098A03R04 2

Supplementary kit 573098A03S01 2

Consumable CMLA01 As required

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at

FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in

post Mod. No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING

BEAM/FORWARD LOWER FUSELAGE JOINT) production solution configuration.

The intention of the production solution was also proposed by Service Bulletin No.

A330-57-3032 for retrofit.

The structural analysis has led to the issue of the Inspection Service Bulletin

A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)).

The Inspection Service Bulletin requires a detailed inspection on A330 aircraft pre

Mod. No. 55306S18660 (FUSELAGE-CENTER FUSELAGE-REPLACE THE ONE-PIECE

FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION))

including mandatory and recommended thresholds and repetitive inspection intervals.

(2) Objective/Action

This Service Bulletin recommends to modify the fasteners installation in the junction of

the keel beam fitting at FR40.

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

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SERVICE BULLETIN

(3) Advantages

Accomplishment of this Service Bulletin cancels the inspection requirements of Service

Bulletin A330-57-3081 for aircraft on which Mod. No. 49202S16307 (FUSELAGE -

CENTER FUSELAGE - REINFORCE SECTION 15/21) is not embodied.ALI 57.11.63 is

created for Post Mod. SB configuration (Post Mod. No. 56467S18944).

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 573098-831-801-001: MODIFICATION

(1) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and

FR40, for access.

(2) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

(3) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners, for aircraft with bush installed on hole 5.

(4) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

(1) Additional Work

**CONF 002

Task 573098-831-801-001: MODIFICATION

(1) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1 and

FR40, for access.

(2) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

(3) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.) installed

on hole 5.

(4) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or =

15mm (0.591in.) installed on hole 5.

(5) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

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

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SERVICE BULLETIN

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

(1) Additional Work

**CONF ALL

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

**CONF 001

AIRBUS strongly recommends not to perform modification before the FC/FH values

given in the table below. In case of early embodiment, additional inspection of CWB

lower panel might be required before DSG or ISG.

Aircraft A330-300 Post Mod. No. 41652S11819 and pre

Mod. No. 44360S13013

Recommended NOT before FC or FH whichever

occurs later

Proposed Compliance

20,550 FC / 62,640 FH

**CONF 002

AIRBUS strongly recommends not to perform modification before the FC/FH values

given in the table below. In case of early embodiment, additional inspection of CWB

lower panel might be required before DSG or ISG.

Aircraft A330-300 Post Mod. No.

44360S13013 and pre Mod. No.

49202S16307

A330-200 Post Mod. No.

44360S13013 and pre Mod. No.

49202S16307

Proposed Compliance Recommended NOT before FC or FH whichever occurs later

20,550 FC / 62,640 FH 22,640 FC / 48,160 FH

**CONF ALL

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

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

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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 573098-831-801-001: MODIFICATION

Get Access 12.00

On Aircraft

On the LH and RH sides, remove (only if necessary)

the ducts between FR39.1 and FR40, for access.

6.00

On the LH and RH sides of aircraft between FR40 and

STGR1, replace the keel beam fasteners for aircraft

without bush installed on hole 5.

12.00

On the LH and RH sides of aircraft between FR40 and

STGR1, replace the keel beam fasteners, for aircraft

with bush installed on hole 5.

12.00

On the LH and RH sides, install (if removed) the ducts

between FR39.1 and FR40.

6.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 65.00

ELAPSED TIME (HOURS) 38.00

NOTE: The TOTAL MANHOURS for one aircraft modified is 53.00 hours.

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

On Aircraft

Additional Work 0.50

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF 002

Task 573098-831-801-001: MODIFICATION

Get Access 12.00

On Aircraft

On the LH and RH sides, remove (only if necessary)

the ducts between FR39.1 and FR40, for access.

6.00

On the LH and RH sides of aircraft between FR40 and

STGR1, replace the keel beam fasteners for aircraft

without bush installed on hole 5.

17.50

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SERVICE BULLETIN

Task 573098-831-801-001: MODIFICATION

On the LH and RH sides of aircraft between FR40 and

STGR1, replace the keel beam fasteners for aircraft

with bush with a diameter < or = to 13mm (0.512in.)

installed on hole 5.

17.50

On the LH and RH sides of aircraft between FR40 and

STGR1, replace the keel beam fasteners for aircraft

with bush with a diameter > 13mm (0.512in.) and < or

= 15mm (0.591in.) installed on hole 5.

17.50

On the LH and RH sides, install (if removed) the ducts

between FR39.1 and FR40.

6.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 93.50

ELAPSED TIME (HOURS) 42.00

NOTE: The TOTAL MANHOURS for one aircraft modified is 58.50 hours.

Task 573098-839-801-001: Administrative - ADDITIONAL WORK

On Aircraft

Additional Work 0.50

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11

21-20-00 21-53-18 27-84-45

28-25-00 32-12-00 36-12-41

53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-18

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-05-05

Service Bulletin (SB) A330-57-3032

A330-57-3081

Service Information Letter (SIL) SIL 51-012

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SERVICE BULLETIN

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11

51-48-00 51-76-12

**CONF 002

Aircraft Maintenance Manual (AMM) 06-41-53 12-34-24 20-21-11

21-20-00 21-53-18 27-84-45

28-25-00 32-12-00 36-12-41

53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-18

Process and Material Specification (PMS) Process and Material Specification

(PMS) 01-05-05

Service Bulletin (SB) A330-57-3032

A330-57-3081

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11

51-48-00 51-76-12

**CONF ALL

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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This Page Intentionally Left Blank

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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 573098A01R03

Supplementary kit 573098A01S01

Supplementary kit 573098A01S02

Kit 573098A03R04

Supplementary kit 573098A03S01

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering modification kits by fax: +49 40

50 76 25 90

For ordering of single spares by fax: +49 40

50 76 40 13

(2) Price and Availability

Kit Held by the Operator Supplementary Kits

Required

Latest Status of Kit INST/DISP

573098A01R01 573098A01S01 AND

573098A01S02

573098A01R03

573098A01R01 AND

573098A01S01

573098A01S02 573098A01R03

573098A01R02 573098A01S02 573098A01R03

573098A01R03 None 573098A01R03

NOTE: Kit 573098A01R03 does not require a Kit 573098A01S02 because Kit

573098A01S02 is included in Kit 573098A01R03.

Kit Held by the Operator Supplementary Kits

Required

Latest Status of Kit INST/DISP

573098A03R03 573098A03S01 573098A03R04

573098A03R04 None 573098A03R04

NOTE: Kit 573098A03R04 does not require a Kit 573098A03S01 because Kit

573098A03S01 is included in Kit 573098A03R04.

Kit 573098A01R03

Cost 439.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

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SERVICE BULLETIN

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Supplementary kit 573098A01S01

Cost 91.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Supplementary kit 573098A01S02

Cost 590.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 573098A03R04

Cost 2,790.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Supplementary kit 573098A03S01

Cost 730.00 USD

Availability 180 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP

policy.

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SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 573098A01R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

27 ASNA2531-6 1 NUT

31 ASNA2531-5 1 NUT

33 ASNA2529-6 1 NUT

35 F5332433420000 1 WASHER

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

60 EN6115-6Y17 1 BOLT

61 EN6115-6Y18 1 BOLT

62 EN6115V6Y15 1 BOLT

66 NSA5368-616A 1 WASHER

67 NSA5368-616B 1 WASHER

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

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 573098A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

27 ASNA2531-6 2 NUT

29 EN6115-6Y10 1 BOLT

31 ASNA2531-5 1 NUT

33 ASNA2529-6 1 NUT

35 F5332433420000 1 WASHER

36 EN6115V6X6 1 BOLT

37 F5332433520000 1 PLUG

38 F5332433520200 1 PLUG

39 F5332433520400 1 PLUG

40 F5332433520600 1 PLUG

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

63 EN6115-6Y14 1 BOLT

64 EN6115-6Y11 1 BOLT

65 EN6115-6Y9 1 BOLT

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

70 NSA5372-616A 2 WASHER

71 NSA5372-616B 2 WASHER

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SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 573098A01S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 573098A01S02

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

60 EN6115-6Y17 1 BOLT

61 EN6115-6Y18 1 BOLT

62 EN6115V6Y15 1 BOLT

66 NSA5368-616A 1 WASHER

67 NSA5368-616B 1 WASHER

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Supplementary kit 573098A03S01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

63 EN6115-6Y14 1 BOLT

64 EN6115-6Y11 1 BOLT

65 EN6115-6Y9 1 BOLT

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

70 NSA5372-616A 2 WASHER

71 NSA5372-616B 2 WASHER

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.

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SERVICE BULLETIN

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 Polysulfid 09-002 As required

Corrosion Inhibitive Interfay Sealant 09-005 As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

Adhesion Promoter For Polysulfide

Sealant

09-028 As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Internal Top Coat 16-002 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

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.

- Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6.

Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for

cold working :

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SERVICE BULLETIN

NOTE: For definition of capital, durable and expendable tools, refer to SIL

51-012.

Operators interested in obtaining the FTI tool kit should contact :

Fatigue Technology Inc.

401 Andover Park West

SEATTLE, WA 98188-7605

USA

E.Mail : sales@fatiguetech.com

E.Mail : aog@fatiguetech.com

Phone : (1) 206 2462010

Fax : (1) 206 2449886

- Capital tooling : ref. FTI-A330-57-3098-1

This tool reference include all capital, durable and expendable tooling kits

regardless of effectivity but capital tooling is normally already and previously bought

by the operator as a long term investment or loaned from FTI.

- Durable tooling : ref. DK-A330-00057-3098-1

- Expendable tooling : ref. EK-A330-57-3098-1

(3) Special Tools

None

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 573098-831-801-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO

THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 65.00

ELAPSED TIME (HOURS) 38.00

**CONF 002

Manpower

TOTAL MANHOURS 93.50

ELAPSED TIME (HOURS) 42.00

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 573098-831-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201

Consumable Material List (CML)

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11

51-43-00

51-44-11

51-48-00

51-76-12

(a) 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.

(b) For the specification of the material numbers (Mat. No.) refer to the CML.

(c) Clean the surfaces to be sealed with

Solvent General

Purpose

11-026 As required

(d) Use a non-metallic spatula to remove the sealant and clean the areas with

Solvent General

Purpose

11-026 As required

(e) Drill and deburr the holes (Refer to SRM 51-44-11).

(f) Remove and install the fasteners (Refer to SRM 51-42-11).

(g) Apply

Sealant-Brush

Consistency

09-013 As required

on all the fasteners to be installed (wet assembly).

(h) For the oversize and alternative fasteners (Refer to SRM 51-43-00).

(i) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201).

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SERVICE BULLETIN

(j) Do the cold expansion of the holes (Refer to SRM 51-48-00).

(k) Apply the sealant (Refer to SRM 51-76-12).

(l) Install the plug with liquid nitrogen (Refer to PMS 01-05-05).

(2) Subtask 573098-900-002-001 - Documentation

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 002

(1) Subtask 573098-831-001-001 - 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

Sealant-Brush Consistency 09-013 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11, Page Block 201

Consumable Material List (CML)

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11

51-43-00

51-44-11

51-48-00

51-76-12

(a) 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.

(b) For the specification of the material numbers (Mat. No.) refer to the CML.

(c) Clean the surfaces to be sealed with

Solvent General

Purpose

11-026 As required

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(d) Use a non-metallic spatula to remove the sealant and clean the areas with

Solvent General

Purpose

11-026 As required

(e) Drill and deburr the holes (Refer to SRM 51-44-11).

(f) Remove and install the fasteners (Refer to SRM 51-42-11).

(g) Apply

Sealant-Brush

Consistency

09-013 As required

on all the fasteners to be installed (wet assembly).

(h) For the oversize and alternative fasteners (Refer to SRM 51-43-00).

(i) Torque the standard threaded fasteners (Refer to AMM 20-21-11 Page Block 201).

(j) Do the cold expansion of the holes (Refer to SRM 51-48-00).

(k) Apply the sealant (Refer to SRM 51-76-12).

(l) Install the plug with liquid nitrogen (Refer to PMS 01-05-05).

(2) Subtask 573098-900-002-001 - Documentation

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 573098-831-003-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

12-34-24, Page Block 201

21-20-00, Page Block 201

21-53-18, Page Block 401

27-84-45, Page Block 401

28-25-00, Page Block 301

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

57-17-11, Page Block 401

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(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Put the access platform(s) in position.

(c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201).

(e) Do the preparation procedure as specified in removal/installation of the pack

discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page

Block 401).

(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401).

(g) Remove the access panels 191FB for the LH side and 192GB for the RH side

(Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(i) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(j) Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45

Page Block 401).

(k) Get access to the work area.

**CONF 002

(1) Subtask 573098-831-003-001 - Preparation

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

12-34-24, Page Block 201

21-20-00, Page Block 201

21-53-18, Page Block 401

27-84-45, Page Block 401

28-25-00, Page Block 301

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Put the access platform(s) in position.

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(c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(d) Do the preparation procedure as specified in removal/installation of the airconditioning distribution ducts (Refer to AMM 21-20-00 Page Block 201).

(e) Do the preparation procedure as specified in removal/installation of the pack

discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page

Block 401).

(f) Do the preparation procedure as specified in removal/installation of the APU bleedair ducts (Refer to AMM 36-12-41 Page Block 401).

(g) Remove the access panels 191FB for the LH side and 192GB for the RH side

(Refer to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(h) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(i) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(j) Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45

Page Block 401).

(k) Get access to the work area.

**CONF ALL

C. PROCEDURE

NOTE: For aircraft on which temporary repair (covered by Repair Design Approval

Sheet (RAS)) have been done following accomplishment of Inspection Service

Bulletin No. A330-57-3081 the operator must contact AIRBUS repair office in

order to issue definitive RAS after embodiment of this Modification Service

Bulletin.

**CONF 001

(1) Subtask 573098-010-001-001 - On the LH and RH sides, remove (only if necessary)

the ducts between FR39.1 and FR40, for access.

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

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References

Fig. A-FCAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

Fig. A-FDAAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40, for

access

Sheet 01

(a) On RH side, remove the air conditioning duct.

Refer to Figure Fig. A-FCAAA

1 Remove :

1 Duct Item (8) Retain

1 Insulation Item (9) Retain

1 Nut Item (10) Retain

1 Bolt Item (11) Retain

1 Washer Item (12) Retain

2 Screw Item (13) Retain

2 Washer Item (14) Retain

2 Nut Item (15) Retain

1 Clamp Item (16) Retain

1 Clamp Item (17) Retain

NOTE (01): Disconnect and move the rod Items (18) and (19) without

removal.

NOTE (02): Remove the Insulation Item (9) with associated clamp Item

(17) from the duct Item (8) only if necessary.

NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18

Page Block 401).

(b) On RH side, remove the air ventilation duct.

Refer to Figure Fig. A-FDAAA

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1 Remove :

1 Duct Item (20) Retain

8 Clamp Item (21) Retain

4 Clamp Item (22) Retain

2 Sleeve Item (23) Retain

1 Sleeve Item (24) Retain

(c) On LH side, remove the necessary APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

(d) Put the blanking plugs on the disconnected line ends.

(2) Subtask 573098-831-005-001 - On the LH and RH sides of aircraft between FR40

and STGR1, replace the keel beam fasteners for aircraft without bush installed on

hole 5.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 573098A01R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

27 ASNA2531-6 1 NUT

31 ASNA2531-5 1 NUT

33 ASNA2529-6 1 NUT

35 F5332433420000 1 WASHER

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

60 EN6115-6Y17 1 BOLT

61 EN6115-6Y18 1 BOLT

62 EN6115V6Y15 1 BOLT

66 NSA5368-616A 1 WASHER

67 NSA5368-616B 1 WASHER

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

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Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfid

09-002 As required

Sealant-Brush Consistency 09-013 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-18

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FBAAA

Replacement of the fasteners of the

Keel Beam (hole 5 without bush)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.)

shall be used.

NOTE: The installed fasteners shall be checked in accordance with the

requirements of SRM 51-42-11 Paragraph 7.C.(g).Table 14 to ensure

that adequate thread protrusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Description below is given for one side of the aircraft, two kits Kit

573098A01R03 are necessary to modify one aircraft.

(a) Inspect the hole 5.

Refer to Figure Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

1 Remove :

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

2 Remove the sealant and clean the hole.

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3 Do a rotating probe inspection (Refer to NTM 51-10-01) through all the layers.

a If no crack is detected, do the operations given in paragraph 3.C.(2)(b).

b If crack is detected do the operations given in paragraph 3.C.(2)(c).

(b) No crack, oversize the hole 5 in the keel beam.

Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA

Sheet 04 andFig. A-FBAAA Sheet 05

1 Ream the hole at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

3 Oversize the hole 5 through all the layers to a diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.).

4 Clean the drilled area.

5 Install :

1 Bolt EN6115V6Y15 Item 62

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616A Item 68

or

1 Washer NSA5368PD616B Item 69

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(c) Crack detected, oversize the hole 5 in the keel beam.

Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA

Sheet 04 and Fig. A-FBAAA Sheet 05

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1 Ream the hole 5 at the level of the keel beam only to a diameter comprised

between 15mm (0.591in.) and 15.2mm (0.598in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 0.5mm (0.02in.) and 0.7mm (0.028in.).

2 Do a rotating probe inspection at the level of the keel beam only (Refer to

NTM 51-10-18).

a Crack finding, contact AIRBUS.

b No crack finding, oversize the hole in the keel beam only to a diameter

comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius

of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is

comprised between 1mm (0.039in.) and 1.2mm (0.047in.).

c Do a rotating probe inspection through all the layers of hole 5 (Refer to

NTM 51-10-01).

<1> Crack finding, contact AIRBUS.

<2> No crack finding, do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on

the hole dia. 17mm (0.669in.).

<3> Oversize the hole 5 through all the layers to a diameter comprised

between 10.177mm (0.401in.) and 10.219mm (0.402in.)

<4> Install :

1 Bolt EN6115V6Y15 Item 62

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616A Item 68

or

1 Washer NSA5368PD616B Item 69

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

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(d) Inspect holes 6 and 7

Refer to Figure Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Bolt Item (1) Discard

1 Bolt Item (3) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in paragraphes 3.C.(2)(e)

and (f).

(e) Do the cold working of the hole 6.

Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA

Sheet 04 and Fig. A-FBAAA Sheet 05

1 Ream the hole to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y17 Item 60

or

1 Bolt EN6115-6Y18 Item 61

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1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616A Item 66

or

1 Washer NSA5368-616B Item 67

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(f) Install the fastener in hole 7.

Refer to Figure Fig. A-FBAAA Sheet 01, Fig. A-FBAAA Sheet 03, Fig. A-FBAAA

Sheet 04 and Fig. A-FBAAA Sheet 05

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

NOTE (03): If necessary, contact AIRBUS for a specific washer solution.

(g) For the report after modification, refer to APPENDIX 01 - Inspection Report .

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

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SERVICE BULLETIN

(3) Subtask 573098-831-006-001 - On the LH and RH sides of aircraft between FR40

and STGR1, replace the keel beam fasteners, for aircraft with bush installed on

hole 5.

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 573098A01R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

27 ASNA2531-6 1 NUT

31 ASNA2531-5 1 NUT

33 ASNA2529-6 1 NUT

35 F5332433420000 1 WASHER

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

60 EN6115-6Y17 1 BOLT

61 EN6115-6Y18 1 BOLT

62 EN6115V6Y15 1 BOLT

66 NSA5368-616A 1 WASHER

67 NSA5368-616B 1 WASHER

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfid

09-002 As required

Sealant-Brush Consistency 09-013 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-18

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FBBAA

Replacement of the fasteners of the

Keel Beam (hole 5 with bush dia. <or=

13mm (0.512 in.))

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

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After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.)

shall be used.

NOTE: The installed fasteners shall be checked in accordance with the

requirements of SRM 51-42-11 Paragraph 7.C.(g).Table.14 to ensure

that adequate thread protrusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table.14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Description below is given for one side of the aircraft, two kits Kit

573098A01R03 are necessary to modify one aircraft.

NOTE: If the diameter of the bush is superior than 13mm (0.512in.) or if the

bush is installed in other layers than keel beam fitting only, contact

AIRBUS.

(a) Inspect the hole 5.

Refer to Figure Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02

1 Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

1 Bush Item (5) Discard

2 Remove the sealant and clean the hole.

3 Do a rotating probe inspection (Refer to NTM 51-10-18) through all the layers.

a If crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in paragraph 3.C.(3)(b).

(b) No crack finding, oversize the hole in the keel beam.

Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03, Fig. A-FBBAA

Sheet 04 and Fig. A-FBBAA Sheet 05

1 Ream the hole at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.)

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2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

3 Oversize the hole through all the layers to a diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.)

4 Install :

1 Bolt EN6115V6Y15 Item 62

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616A Item 68

or

1 Washer NSA5368PD616B Item 69

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(c) Inspect holes 6 and 7.

Refer to Figure Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Bolt Item (1) Discard

1 Bolt Item (41) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

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b If no crack is detected, do the operations given in the paragraphes

3.C.(3)(d) and (e).

(d) Do the cold working of the hole 6.

Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03, Fig. A-FBBAA

Sheet 04 and Fig. A-FBBAA Sheet 05

1 Ream the hole to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

Clean the drilled area.

2 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

3 Ream the hole to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

4 Clean the drilled area.

5 Install :

1 Bolt EN6115-6Y17 Item 60

or

1 Bolt EN6115-6Y18 Item 61

1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616A Item 66

or

1 Washer NSA5368-616B Item 67

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

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(e) Install the fastener in hole 7.

Refer to Figure Fig. A-FBBAA Sheet 01, Fig. A-FBBAA Sheet 03, Fig. A-FBBAA

Sheet 04 and Fig. A-FBBAA Sheet 05

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

NOTE (03): If necessary, contact AIRBUS for a specific washer solution.

(f) For the report after modification, refer to APPENDIX 01 - Inspection Report .

(4) Subtask 573098-410-001-001 - On the LH and RH sides, install (if removed) the

ducts between FR39.1 and FR40.

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

Fig. A-FCAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

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References

Fig. A-FDAAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40, for

access

Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

(b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

(c) On RH side, install (if removed) the air ventilation duct.

Refer to Figure Fig. A-FDAAA

1 Install :

1 Duct Item (20)

8 Clamp Item (21)

4 Clamp Item (22)

2 Sleeve Item (23)

1 Sleeve Item (24)

NOTE: Items (20) thru (24) were retained at removal.

(d) On RH side, install (if removed) the air conditioning duct.

Refer to Figure Fig. A-FCAAA

1 Install :

1 Duct Item (8)

1 Insulation Item (9)

1 Nut Item (10)

1 Bolt Item (11)

1 Washer Item (12)

2 Screw Item (13)

2 Washer Item (14)

2 Nut Item (15)

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1 Clamp Item (16)

1 Clamp Item (17)

NOTE (01): Reconnect the rod Items (18) and (19).

NOTE (02): For the installation of the sensor 542HH (Refer to AMM

21-53-18 Page Block 401).

NOTE (03): Items (8) thru (17) were retained at removal.

**CONF 002

(1) Subtask 573098-010-001-002 - On the LH and RH sides, remove (only if necessary)

the ducts between FR39.1 and FR40, for access.

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

Fig. A-FCAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

Fig. A-FDAAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40, for

access

Sheet 01

NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02

embodiment recommendation.

(a) On RH side, remove the air conditioning duct.

Refer to Figure Fig. A-FCAAA

1 Remove :

1 Duct Item (8) Retain

1 Insulation Item (9) Retain

1 Nut Item (10) Retain

1 Bolt Item (11) Retain

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1 Washer Item (12) Retain

2 Screw Item (13) Retain

2 Washer Item (14) Retain

2 Nut Item (15) Retain

1 Clamp Item (16) Retain

1 Clamp Item (17) Retain

NOTE (01): Disconnect and move the rod Items (18) and (19) without

removal.

NOTE (02): Remove the Insulation Item (9) with associated clamp Item

(17) from the duct Item (8) only if necessary.

NOTE (03): For the removal of the sensor 542HH (Refer to AMM 21-53-18

Page Block 401).

(b) On RH side, remove the air ventilation duct.

Refer to Figure Fig. A-FDAAA

1 Remove :

1 Duct Item (20) Retain

8 Clamp Item (21) Retain

4 Clamp Item (22) Retain

2 Sleeve Item (23) Retain

1 Sleeve Item (24) Retain

(c) On LH side, remove the necessary APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

(d) Put the blanking plugs on the disconnected line ends.

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(2) Subtask 573098-831-005-002 - On the LH and RH sides of aircraft between FR40

and STGR1, replace the keel beam fasteners for aircraft without bush installed on

hole 5.

Manpower Resources

Manhours 17.50

Minimum number of person 1

Subtask elapsed time 17.50

Skills AIRFRAME

Material necessary to do the job

Kit 573098A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

27 ASNA2531-6 2 NUT

29 EN6115-6Y10 1 BOLT

31 ASNA2531-5 1 NUT

33 ASNA2529-6 1 NUT

35 F5332433420000 1 WASHER

36 EN6115V6X6 1 BOLT

37 F5332433520000 1 PLUG

38 F5332433520200 1 PLUG

39 F5332433520400 1 PLUG

40 F5332433520600 1 PLUG

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

63 EN6115-6Y14 1 BOLT

64 EN6115-6Y11 1 BOLT

65 EN6115-6Y9 1 BOLT

68 NSA5368PD616A 1 WASHER

69 NSA5368PD616B 1 WASHER

70 NSA5372-616A 2 WASHER

71 NSA5372-616B 2 WASHER

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfid

09-002 As required

Corrosion Inhibitive Interfay

Sealant

09-005 As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Internal Top Coat 16-002 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-18

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FBCAA

Replacement of the fasteners of the

Keel Beam (hole 5 without bush, without

crack detected)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-FBDAA

Replacement of the fasteners of the

Keel Beam (hole 5 without bush, with

crack detected)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.)

shall be used.

NOTE: The installed fasteners shall be checked in accordance with the

requirements of SRM 51-42-11 Paragraph 7.C.(g).Table.14 to ensure

that adequate thread protrusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table 14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02

embodiment recommendation.

NOTE: Description below is given for one side of the aircraft, two kits Kit

573098A03R04 are necessary to modify one aircraft.

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(a) Inspect the hole 5.

Refer to Figure Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02

1 Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

2 Remove the sealant and clean the hole.

3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM

51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2)(b).

b If a crack is detected, do the operations given in paragraph 3.C.(2)(f).

(b) No crack, oversize the hole 5 in the keel beam.

Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA

Sheet 04 and Fig. A-FBCAA Sheet 05

1 Ream the hole 5 at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.).

2 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

3 Oversize the hole 5 through all the layers to a diameter comprised between

9.784mm (0.385in.) and 9.823mm (0.387in.)

4 Install :

1 Bolt EN6115V6X6 Item 36

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616A Item 68

or

1 Washer NSA5368PD616B Item 69

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

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(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(c) Inspect holes A, 6 and 7.

Refer to Figure Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (3) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A, 6 and 7 (Refer

to NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(2)(d) and (e).

(d) Do the cold working of the holes A and 6.

Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA

Sheet 04 and Fig. A-FBCAA Sheet 05

1 Ream the holes A and 6 to the starting hole diameter for the cold working

comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the holes A and 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

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4 Ream the holes A and 6 to the final hole diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Bolt EN6115-6Y9 Item 65

or

1 Bolt EN6115-6Y10 Item 29

2 Nut ASNA2531-6 Item 27

2 Washer NSA5372-616A Item 70

or

2 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(e) Install the fastener in hole 7.

Refer to Figure Fig. A-FBCAA Sheet 01, Fig. A-FBCAA Sheet 03, Fig. A-FBCAA

Sheet 04 and Fig. A-FBCAA Sheet 05

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

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NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(f) Crack detected at existing diameter.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA

Sheet 04 and Fig. A-FBDAA Sheet 05

1 Ream the hole 5 through all the layer at diameter 9.5mm (0.374in.).

2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to

NTM 51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2)(g).

b If a crack is detected at diameter 9.5mm (0.374in.), do the operations

given in paragraph 3.C.(2)(k).

(g) No crack detected at diameter 9.5mm (0.374in.) for hole 5.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA

Sheet 04 and Fig. A-FBDAA Sheet 05

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

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5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

7 Ream the hole 5 through all the layers to a diameter comprised between

11.5mm (0.4528in.) and 11.518mm (0.4535in.)

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole 5 with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

10 Install :

1 Plug F5332433520000 Item 37

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 37 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 37 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

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Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 37 do a seal bead

with :

Corrosion Inhibiting

Fillet Consistency

09-016 As required

NOTE (06): Do a seal bead on the external edge of the plug Item 37 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(h) Inspect holes A and 7.

Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(2)(i) and (j).

(i) Do the cold working of the hole A.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

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1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(j) Install the fastener in hole 7.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

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1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(k) Crack detected at diameter 9.5mm (0.374in.) for hole 5.

1 Ream the hole 5 through all the layers at diameter 11.1mm (0.437in.).

2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to

NTM 51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2)(l).

b If a crack is detected, do the operations given in paragraph 3.C.(2)(p).

(l) No crack detected at diameter 11.1mm (0.437in.) for hole 5.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03, Fig. A-FBDAA

Sheet 04 and Fig. A-FBDAA Sheet 05

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

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5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

7 Ream the hole 5 through all the layers to a diameter comprised between

13.1mm (0.5157in.) and 13.118mm (0.5165in.).

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole 5 with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

10 Install :

1 Plug F5332433520200 Item 38

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 38 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 38 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

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Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 38 do a seal bead

with :

Corrosion Inhibiting

Fillet Consistency

09-016 As required

NOTE (06): Do a seal bead on the external edge of the plug Item 38 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(m) Inspect holes A and 7.

Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(2)(n) and (o).

(n) Do the cold working of the hole A.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

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1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(o) Install the fastener in hole 7.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

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

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SERVICE BULLETIN

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(p) Crack detected at diameter 11.1mm (0.437in.) for hole 5.

1 Ream the hole 5 through all the layers at diameter 13.1mm (0.516in.).

2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to

NTM 51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2)(q).

b If crack is detected, do the operations given in paragraph 3.C.(2)(u).

(q) No crack detected at diameter 13.1mm (0.516in.) for hole 5.

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

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

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SERVICE BULLETIN

7 Ream the hole 5 through all the layers to a diameter comprised between

15mm (0.5906in.) and 15.018mm (0.5913in.).

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole 5 with

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

.

10 Install :

1 Plug F5332433520400 Item 39

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 39 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 39 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 39 do a seal bead

with :

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

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SERVICE BULLETIN

Corrosion Inhibiting

Fillet Consistency

09-016 As required

NOTE (06): Do a seal bead on the external edge of the plug Item 39 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(r) Inspect holes A and 7.

Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(2)(s) or (t).

(s) Do the cold working of the hole A.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

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SERVICE BULLETIN

2 Clean the drilled area.

3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(t) Install the fastener in hole 7.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

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

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SERVICE BULLETIN

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(u) Crack detected at diameter 13.1mm (0.516in.) for hole 5.

1 Ream the hole 5 through all the layers at diameter of 15mm (0.591in.).

2 Perform a rotating probe inspection through all the layers of hole 5.(Refer to

NTM 51-10-01).

a If no crack is detected, do the operations given in paragraph 3.C.(2)(v).

b If crack is detected, contact AIRBUS.

(v) No crack detected at diameter 15mm (0.591in.) for hole 5.

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

7 Ream the hole 5 through all the layers to a diameter comprised between

17mm (0.6693in.) and 17.018mm (0.67in.).

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SERVICE BULLETIN

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole 5 with

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

.

10 Install :

1 Plug F5332433520600 Item 40

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 40 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 40 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 40 do a seal bead

with :

Corrosion Inhibiting

Fillet Consistency

09-016 As required

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

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SERVICE BULLETIN

NOTE (06): Do a seal bead on the external edge of the plug Item 40 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(w) Inspect holes A and 7.

Refer to Figure Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(2)(x) and (y).

(x) Do the cold working of the hole A.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

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3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(y) Install the fastener in hole 7.

Refer to Figure Fig. A-FBDAA Sheet 01, Fig. A-FBDAA Sheet 03 and Fig. AFBDAA Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

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

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SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(3) Subtask 573098-831-010-001 - On the LH and RH sides of aircraft between FR40

and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter

< or = to 13mm (0.512in.) installed on hole 5.

Manpower Resources

Manhours 17.50

Minimum number of person 1

Subtask elapsed time 17.50

Skills AIRFRAME

Material necessary to do the job

Kit 573098A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

27 ASNA2531-6 2 NUT

31 ASNA2531-5 1 NUT

39 F5332433520400 1 PLUG

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

63 EN6115-6Y14 1 BOLT

64 EN6115-6Y11 1 BOLT

70 NSA5372-616A 2 WASHER

71 NSA5372-616B 2 WASHER

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfid

09-002 As required

Corrosion Inhibitive Interfay

Sealant

09-005 As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

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

REVISION No.: 02 - Jun 15/11 Page: 59

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Internal Top Coat 16-002 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-18

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FBEAA

Replacement of the fasteners of the

Keel Beam (hole 5 with bush dia. <or=

13mm (0.512 in.) without crack detected)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.)

shall be used.

NOTE: The installed fasteners shall be checked in accordance with the

requirements of SRM 51-42-11 Paragraph 7.C.(g).Table.14 to ensure

that adequate thread protrusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table.14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02

embodiment recommendation.

NOTE: Description below is given for one side of the aircraft, two kits Kit

573098A03R04 are necessary to modify one aircraft.

(a) Inspect the hole 5.

Refer to Figure Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02

1 Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

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SERVICE BULLETIN

1 Bush Item (5) Discard

2 Remove the sealant and clean the hole.

3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM

51-10-18).

a If no crack is detected, do the operations given in paragraph 3.C.(3)(b).

b If a crack is detected, contact AIRBUS.

(b) No crack detected at original diameter on hole 5.

Refer to Figure Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

7 Ream the hole 5 through all the layers to a diameter comprised between

15mm (0.5905in.) and 15.018mm (0.5913in.).

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole 5 with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

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

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@A330

SERVICE BULLETIN

10 Install :

1 Plug F5332433520400 Item 39

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 39 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 39 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 39 do a seal bead

with :

Corrosion Inhibiting

Fillet Consistency

09-016 As required

NOTE (06): Do a seal bead on the external edge of the plug Item 39 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

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@A330

SERVICE BULLETIN

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(c) Inspect holes A and 7.

Refer to Figure Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02

1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(3)(d) and (e).

(d) Do the cold working of the hole A.

Refer to Figure Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 03 and Fig. A-FBEAA

Sheet 04

1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

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@A330

SERVICE BULLETIN

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(e) Install the fastener in hole 7.

Refer to Figure Fig. A-FBEAA Sheet 01, Fig. A-FBEAA Sheet 03 and Fig. A-FBEAA

Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

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

REVISION No.: 02 - Jun 15/11 Page: 64

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@A330

SERVICE BULLETIN

(4) Subtask 573098-831-011-001 - On the LH and RH sides of aircraft between FR40

and STGR1, replace the keel beam fasteners for aircraft with bush with a diameter

> 13mm (0.512in.) and < or = 15mm (0.591in.) installed on hole 5.

Manpower Resources

Manhours 17.50

Minimum number of person 1

Subtask elapsed time 17.50

Skills AIRFRAME

Material necessary to do the job

Kit 573098A03R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

27 ASNA2531-6 2 NUT

31 ASNA2531-5 1 NUT

40 F5332433520600 1 PLUG

51 EN6115-5-13 1 BOLT

52 EN6115-5-14 1 BOLT

63 EN6115-6Y14 1 BOLT

64 EN6115-6Y11 1 BOLT

70 NSA5372-616A 2 WASHER

71 NSA5372-616B 2 WASHER

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfid

09-002 As required

Corrosion Inhibitive Interfay

Sealant

09-005 As required

Sealant-Brush Consistency 09-013 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

Internal Top Coat 16-002 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-18

Process and Material Specification

(PMS)

Process and Material Specification (PMS)

01-05-05

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-42-11 Paragraph 7.C.(g).Table 14

51-48-00

Fig. A-FBFAA

Replacement of the fasteners of the

Keel Beam (hole 5 with bush 13mm

(0.512 in.) <dia.< or = 15mm (0.591 in.))

without crack detected)

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

NOTE: Firstly, the stack up assembly must be checked to determine the actual

length of the bolt to be used.

After measurement, if the shank protusion above the stack up assembly

is lower than 0.8mm (0.031in.), then a washer with a thickness of 0.8mm

(0.031in.) shall be used.

Otherwise if the shank protusion is between 0.8mm (0.031in.) and

1.6mm (0.063in.), then a washer with a thickness of 1.6mm (0.063in.)

shall be used.

NOTE: The installed fasteners shall be checked in accordance with the

requirements of SRM 51-42-11 Paragraph 7.C.(g).Table.14 to ensure

that adequate thread protrusion is maintained after installation.

Remark : SRM 51-42-11 Paragraph 7.C.(g).Table.14 is applicable for all Hi-Lite / HiTigue (Bull Nose or Lead-in radius) and nut combinations.

NOTE: Refer to paragraph E.(2) Accomplishment Timescale for Config. 02

embodiment recommendation.

NOTE: Description below is given for one side of the aircraft, two kits Kit

573098A03R04 are necessary to modify one aircraft.

(a) Inspect the hole 5.

Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02

1 Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

1 Bush Item (5) Discard

2 Remove the sealant and clean the hole.

3 Do a rotating probe inspection through all the layers of hole 5 (Refer to NTM

51-10-18).

a If no crack is detected, do the operations given in paragraph 3.C.(4)(b).

b If a crack is detected, contact AIRBUS.

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

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(b) No crack detected at original diameter for hole 5

Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02

1 Remove the fastener of hole 6.

a Remove:

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

2 Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

3 Clean the drilled area.

4 Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

5 Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

6 Clean the drilled area.

7 Ream the hole 5 through all the layers to a diameter comprised between

17mm (0.6693in.) and 17.018mm (0.67in.).

8 Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

9 Protect the hole with :

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

.

10 Install :

1 Plug F5332433520600 Item 40

1 Bolt EN6115-6Y11 Item 64

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

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

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1 Washer NSA5372-616B Item 71

NOTE (01): Install the plug Item 40 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE (02): Between the plug Item 40 and the structure apply :

Corrosion Inhibitive

Interfay Sealant

09-005 As required

NOTE (03): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (04): After assembly in the hole apply :

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

and

Internal Top Coat 16-002 As required

NOTE (05): In the hole on the edge of the plug Item 40 do a seal bead

with :

Corrosion Inhibiting

Fillet Consistency

09-016 As required

NOTE (06): Do a seal bead on the external edge of the plug Item 40 with :

Fuel Tank Sealant

Polysulfid

09-002 As required

and

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

NOTE (07): Coat the nut and washer with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(c) Inspect holes A and 7.

Refer to Figure Fig. A-FBFAA Sheet 01 and Fig. A-FBFAA Sheet 02

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1 Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

2 Remove the sealant and clean the holes.

3 Do a rotating probe inspection through all the layers of holes A and 7 (Refer to

NTM 51-10-01).

a If a crack is detected, contact AIRBUS.

b If no crack is detected, do the operations given in the paragraphes

3.C.(4)(d) and (e).

(d) Do the cold working of the hole A.

Refer to Figure Fig. A-FBFAA Sheet 01, Fig. A-FBFAA Sheet 03 and Fig. A-FBFAA

Sheet 04

1 Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A330-57-3098-1.

2 Clean the drilled area.

3 Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A330-57-3098-1 and EK-A330-57-3098-1.

4 Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A330-57-3098-1.

5 Clean the drilled area.

6 Install :

1 Bolt EN6115-6Y14 Item 63

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616A Item 70

or

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

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1 Washer NSA5372-616B Item 71

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(e) Install the fastener in hole 7.

Refer to Figure Fig. A-FBFAA Sheet 01, Fig. A-FBFAA Sheet 03 and Fig. A-FBFAA

Sheet 04

1 Oversize the hole to a diameter comprised between 7.809mm (0.307in.) and

7.849mm (0.309in.).

2 Install :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE (01): Before installation of the fasteners, apply :

Sealant-Brush

Consistency

09-013 As required

(wet assembly).

NOTE (02): Coat the nut with :

Fuel Tank Sealant

Polysulfid

09-002 As required

(5) Subtask 573098-410-001-001 - On the LH and RH sides, install (if removed) the

ducts between FR39.1 and FR40.

Manpower Resources

Manhours 6.00

Minimum number of person 1

Subtask elapsed time 6.00

Skills NON SPECIFIC

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

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References

Aircraft Maintenance Manual (AMM) 21-53-18, Page Block 401

36-12-41, Page Block 401

Fig. A-FCAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

Fig. A-FDAAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40, for

access

Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

(b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41 Page Block 401).

(c) On RH side, install (if removed) the air ventilation duct.

Refer to Figure Fig. A-FDAAA

1 Install :

1 Duct Item (20)

8 Clamp Item (21)

4 Clamp Item (22)

2 Sleeve Item (23)

1 Sleeve Item (24)

NOTE: Items (20) thru (24) were retained at removal.

(d) On RH side, install (if removed) the air conditioning duct.

Refer to Figure Fig. A-FCAAA

1 Install :

1 Duct Item (8)

1 Insulation Item (9)

1 Nut Item (10)

1 Bolt Item (11)

1 Washer Item (12)

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2 Screw Item (13)

2 Washer Item (14)

2 Nut Item (15)

1 Clamp Item (16)

1 Clamp Item (17)

NOTE (01): Reconnect the rod Items (18) and (19).

NOTE (02): For the installation of the sensor 542HH (Refer to AMM

21-53-18 Page Block 401).

NOTE (03): Items (8) thru (17) were retained at removal.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 573098-831-014-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-20-00, Page Block 201

21-53-18, Page Block 401

27-84-45, Page Block 201

27-84-45, Page Block 401

28-25-00, Page Block 301

36-12-41, Page Block 401

57-17-11, Page Block 401

57-17-11, Page Block 401

(a) Preparation

1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page

Block 401).

2 Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45

Page Block 201).

4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00

Page Block 201).

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

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(b) Tests

1 Do the test after the removal/installation of the pack discharge temperaturesensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).

2 Do the test after the removal/installation of the APU bleed air ducts (Refer to

AMM 36-12-41 Page Block 401).

3 Do the test after the removal/installation of the covers (147AZ and 148AZ)

(Refer to AMM 57-17-11 Page Block 401).

4 Do the test after the removal/installation of the torque shaft assy (5010CW and

5070CW)(Refer to AMM 27-84-45 Page Block 401).

5 Do the test after the removal/installation of the air conditioning distribution

ducts (Refer to AMM 21-20-00 Page Block 201).

**CONF 002

(1) Subtask 573098-831-014-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 21-20-00, Page Block 201

21-53-18, Page Block 401

27-84-45, Page Block 201

27-84-45, Page Block 401

28-25-00, Page Block 301

36-12-41, Page Block 401

57-17-11, Page Block 401

57-17-11, Page Block 401

(a) Preparation

1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page

Block 401).

2 Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45

Page Block 201).

4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00

Page Block 201).

(b) Tests

1 Do the test after the removal/installation of the pack discharge temperaturesensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).

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

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2 Do the test after the removal/installation of the APU bleed air ducts (Refer to

AMM 36-12-41 Page Block 401).

3 Do the test after the removal/installation of the covers (147AZ and 148AZ)

(Refer to AMM 57-17-11 Page Block 401).

4 Do the test after the removal/installation of the torque shaft assy (5010CW and

5070CW)(Refer to AMM 27-84-45 Page Block 401).

5 Do the test after the removal/installation of the air conditioning distribution

ducts (Refer to AMM 21-20-00 Page Block 201).

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 573098-831-015-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

21-53-18, Page Block 401

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

(a) Do the close-up procedure as specified in removal/installation of the pack discharge

temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).

(b) Do the close-up procedure as specified in removal/installation of the APU bleed-air

ducts (Refer to AMM 36-12-41 Page Block 401).

(c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer

to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal operating condition.

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

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**CONF 002

(1) Subtask 573098-831-015-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53

21-53-18, Page Block 401

32-12-00, Page Block 201

36-12-41, Page Block 401

53-35-13, Page Block 401

(a) Do the close-up procedure as specified in removal/installation of the pack discharge

temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18 Page Block 401).

(b) Do the close-up procedure as specified in removal/installation of the APU bleed-air

ducts (Refer to AMM 36-12-41 Page Block 401).

(c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer

to AMM 53-35-13 Page Block 401 and AMM 06-41-53).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal operating condition.

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

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This Page Intentionally Left Blank

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SERVICE BULLETIN

Task 573098-839-801-001 - Administrative - ADDITIONAL WORK

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF 002

Manpower

TOTAL MANHOURS 0.50

ELAPSED TIME (HOURS) 0.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 573098-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

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

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**CONF 002

(1) Subtask 573098-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

None

**CONF 002

None

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 573098-839-002-001 - Additional Work

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Aircraft which has got the SUBTASK 573098-831-005 001 accomplished at the original

Service Bulletin issue contact AIRBUS for advise on the ADDITIONAL WORK.

**CONF 002

(1) Subtask 573098-839-002-002 - Additional Work

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

Aircraft which has got the SUBTASK 573098-831-005 002 accomplished at the original

Service Bulletin issue contact AIRBUS for advise on the ADDITIONAL WORK.

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

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**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF ALL

E. CLOSE-UP

**CONF 001

None

**CONF 002

None

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

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**CONF ALL

FR39.2

B

FR40.2

Z192

A

542HH

A

B

(9)

(17)

(8)

(15)

(18)

(15)

(13)

(14)

(13)

(14) (19)

(10)

(11)

(12)

(16)

G_SB_573098_5_CAAA_01_00

Figure A-FCAAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access

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

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**CONF ALL

B C

D

Z191−Z192

FR40

FR47

A

B

A

D

C

D

(21) (23) (21)

(22) (22) (24)

(20)

G_SB_573098_5_DAAA_01_00

Figure A-FDAAA - Sheet 01

Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for access

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

REVISION No.: 02 - Jun 15/11 Page: 81

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**CONF 001

A

Z141−142

A

FR40

FR47

B

B

B

FR40 DATUM

STGR1

C

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

Y1959

G_SB_573098_5_BAAA_01_00

Figure A-FBAAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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

REVISION No.: 02 - Jun 15/11 Page: 82

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**CONF 001

FR40

D

C

Y1959

VIEW INSIDE CENTER TANK AT FR40

BEFORE

BEFORE

(1)

(2) (4)

SHIM

GUSSET

CWB LOWER PANEL

KEEL BEAM

FASTENER NOT AFFECTED

(3) (41)

D

HOLE 5

HOLE 6

HOLE 7 STGR 1

STGR 1

SECTION

D−D

FR40 DATUM

G_SB_573098_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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

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SERVICE BULLETIN

**CONF 001

11.8mm MINIMUM

(0.465in.)

STGR1

31

27

35

FR40

1

STGR1

D

D

C

Y1959

EXPANSION SLEEVE INSTALLATION

ORIENTATION SCHEMATIC DIAGRAM

FASTENER NOT AFFECTED

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STEP 1 DIA 15mm THRU 15.2mm

(0.591in. THRU 0.598in.)

33

HOLE 5

HOLE 6

HOLE 7

DETAIL E

AFTER

AFTER

APPLY SEALANT MAT No. 09−002B

NOTE :

1

STEP 2 DIA. 17mm THRU 17.2mm

SECTION

D−D

62

(0.669in. THRU 0.677in.)

1

1

1

2 IF NECESSARY CONTACT AIRBUS FOR A SPECIFIC WASHER SOLUTION.

2

2

51

OR

52

G_SB_573098_5_BAAA_03_00

68

OR

69

60

OR

61

66

OR

67

Figure A-FBAAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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

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SERVICE BULLETIN

**CONF 001

35

1mm THRU 1.2mm MAX.

AFTER

0.5mm THRU 0.7mm

DETAIL E

(0.02in. THRU 0.028in.)

(0.039in. THRU 0.047in.) MAX.

(0.02in.x 0.02in.)

CHAMFER 0.5mm x 0.5mm

RADIUS 2mm

(0.079in)

G_SB_573098_5_BAAA_04_00

Figure A-FBAAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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

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SERVICE BULLETIN

**CONF 001

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

F5332433420000

ASNA2529−6

BOLT

WASHER

BOLT

PN DESCRIPTION

7.849mm

(0.309in.)

REMARKS

NOMINAL

NUT

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

NUT 12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

SECOND

OVERSIZE

62

35

33

51

7.809mm

(0.307in.)

10.219mm

(0.402in.)

61

27

10.177mm

(0.401in.)

1

EN6115−6Y18

ASNA2531−6 9.53mm

(0.375in.)

10.177mm

(0.401in.)

9.60mm

(0.378in.)

STDN

EN6115V6Y15

66 NSA5368−616A

NSA5368PD616A

WASHER

68

52

31 ASNA2531−5 NUT

OR

EN6115−5−13

EN6115−5−14

69

OR

NSA5368PD616B

67 NSA5368−616B

60 EN6115−6Y17

WASHER

BOLT

OR

G_SB_573098_5_BAAA_05_02

Figure A-FBAAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 without bush)

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

REVISION No.: 02 - Jun 15/11 Page: 86

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**CONF 001

A

Z141−142

A

FR40

FR47

B

B

B

FR40 DATUM

STGR1

C

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

Y1959

G_SB_573098_5_BBAA_01_00

Figure A-FBBAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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

REVISION No.: 02 - Jun 15/11 Page: 87

5

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

SERVICE BULLETIN

**CONF 001

FR40

C

Y1959

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

BEFORE

(41) (1)

(2)

DIA 13mm

(0.512in.)

(5)

(3)

(4) SHIM

GUSSET

CWB LOWER PANEL

KEEL BEAM

FASTENER NOT AFFECTED

D

D

D−D

SECTION

HOLE 5

HOLE 6

HOLE 7

BEFORE

STGR 1

STGR 1

G_SB_573098_5_BBAA_02_00

Figure A-FBBAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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

REVISION No.: 02 - Jun 15/11 Page: 88

5

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@A330

SERVICE BULLETIN

**CONF 001

11.8mm MINIMUM

(0.465in.)

27

62

35

FR40

C

EXPANSION SLEEVE INSTALLATION

ORIENTATION SCHEMATIC DIAGRAM

FASTENER NOT AFFECTED

VIEW INSIDE CENTER TANK AT FR40

33

D−D

SECTION

DETAIL E

DIA 17mm THRU 17.2mm

(0.669in. THRU 0.677in.)

AFTER

AFTER

STGR 1

STGR1

D

D Y1959

FR40 DATUM

HOLE 5

HOLE 6

HOLE 7

1

1 APPLY SEALANT MAT No. 09−002B

NOTE :

1

1

1

31

2 IF NECESSARY CONTACT AIRBUS FOR A SPECIFIC WASHER SOLUTION.

2

2

51

OR

52

G_SB_573098_5_BBAA_03_00

60

OR

61

66

OR

67

68

OR

69

Figure A-FBBAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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

REVISION No.: 02 - Jun 15/11 Page: 89

5

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@A330

SERVICE BULLETIN

**CONF 001

35

1mm THRU 1.2mm MAX.

(0.02in.x 0.02in.)

CHAMFER 0.5mm x 0.5mm

AFTER

DETAIL E

(0.039in. THRU 0.047in.) MAX.

RADIUS 2mm

(0.079in)

G_SB_573098_5_BBAA_04_00

Figure A-FBBAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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

REVISION No.: 02 - Jun 15/11 Page: 90

5

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

SERVICE BULLETIN

**CONF 001

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

F5332433420000

ASNA2529−6

BOLT

WASHER

BOLT

PN DESCRIPTION

7.849mm

(0.309in.)

REMARKS

NOMINAL

NUT

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

NUT 12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

SECOND

OVERSIZE

62

35

33

51

7.809mm

(0.307in.)

10.219mm

(0.402in.)

61

27

10.177mm

(0.401in.)

1

EN6115−6Y18

ASNA2531−6 9.53mm

(0.375in.)

10.177mm

(0.401in.)

9.60mm

(0.378in.)

STDN

EN6115V6Y15

66 NSA5368−616A

NSA5368PD616A

WASHER

68

52

31 ASNA2531−5 NUT

OR

EN6115−5−13

EN6115−5−14

69

OR

NSA5368PD616B

67 NSA5368−616B

60 EN6115−6Y17

WASHER

BOLT

OR

G_SB_573098_5_BBAA_05_01

Figure A-FBBAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

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

REVISION No.: 02 - Jun 15/11 Page: 91

5

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@A330

SERVICE BULLETIN

**CONF 002

A

Z141−142

A

FR40

FR47

B

B

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STGR1

C

Y1959

G_SB_573098_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 92

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

SECTION

E−E

C

VIEW SIDE CENTRE TANK AT FR 40 E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

STGR 1

(4) (4) (2)

(1) (3) (3)

BEFORE

BEFORE

HOLE 7

HOLE A

HOLE 6

STGR 1

SECTION

D−D

(6)

(7)

BEFORE

HOLE 5

G_SB_573098_5_BCAA_02_00

Figure A-FBCAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 93

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

SECTION

E−E

SECTION

D−D

C

E

E

D

D

FASTENER NOT AFFECTED

AFTER

AFTER

AFTER

63

VIEW INSIDE CENTER TANK AT FR40

3

HOLE A

HOLE 5

HOLE 6

HOLE 7

4

FR40

KEEL BEAM

CWB LOWER PANEL

STGR 1 31

11.8mm MINIMUM

(0.465in.) 33 27

35

36

DIA. 17mm THRU 17.2mm

(0.669in. THRU 0.677in.)

DETAIL F

STGR 1

1 APPLY SEALANT MAT No. 09−002B

NOTE :

1

1

1

1

27

OR

51

52

G_SB_573098_5_BCAA_03_00

OR

29

65

OR

70

71

OR

68

69

OR

70

71

Figure A-FBCAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 94

5

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

SERVICE BULLETIN

**CONF 002

(0.02in x 0.02in)

1mm THRU 1.2mm

(0.039in THRU 0.047in)

(0.072in)

CHAMFER 0.5mm x 0.5mm

36

DETAIL F

RADIUS 2mm

AFTER

33

35

G_SB_573098_5_BCAA_04_00

OR

68

69

Figure A-FBCAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 95

5

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

SERVICE BULLETIN

**CONF 002

68

33

NSA5368PD616A

ASNA2529−6

WASHER

9.823mm

(0.387in.)

FIRST

OVERSIZE

NUT

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

NSA5372−616B

WASHER 12−1−N

12−1−N

9.80mm

(0.378in.)

10.219mm

(0.402in.)

9.80mm

(0.378in.)

10.219mm

(0.402in.)

SECOND

OVERSIZE

SECOND

OVERSIZE

9.784mm

(0.385in.)

63

71

10.177mm

(0.401in.)

10.177mm

(0.401in.)

3

4

STDN

BOLT

9.53mm

(0.375in.)

9.53mm

(0.375in.)

EN6115−6Y14

27 ASNA2531−6 NUT

BOLT

7.849mm

(0.309in.) NOMINAL

51

7.809mm

(0.307in.) 52

31 ASNA2531−5 NUT

OR

EN6115−5−13

EN6115−5−14

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

36 BOLT

PN DESCRIPTION REMARKS

EN6115V6X6

35 F5332433420000 WASHER

69 NSA5368PD616B

OR

70 NSA5372−616A

OR

65

29

OR

NSA5372−616B

WASHER

71

70 NSA5372−616A

OR

27 ASNA2531−6 NUT

BOLT

EN6115−6Y10

EN6115−6Y9

G_SB_573098_5_BCAA_05_01

Figure A-FBCAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 96

5

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

SERVICE BULLETIN

**CONF 002

A

Z141−142

A

FR40

FR47

B

B

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STGR1

C

Y1959

G_SB_573098_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 97

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

SECTION

E−E

SECTION

D−D

C

VIEW SIDE CENTRE TANK AT FR 40

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

STGR 1

(4)

(2)

(1) (3)

(3)

(6)

(7)

BEFORE

BEFORE

BEFORE

HOLE 7

HOLE A

HOLE 6

HOLE 5

STGR 1

G_SB_573098_5_BDAA_02_00

Figure A-FBDAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 98

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

11.8mm MINIMUM

C

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

AFTER

(0.465in.)

STGR 1 27

OR

37

OR

OR

38

39

40 31

VIEW INSIDE CENTER TANK AT FR40

3

2

HOLE A

HOLE 5

HOLE 6

HOLE 7

DETAIL F

STGR 1

SECTION

D−D

AFTER

SECTION

AFTER

E−E

63

27

3

3

3

3

APPLY MAT No. 09−002B

51

52

OR

G_SB_573098_5_BDAA_03_00

64

OR

70

71

OR

70

71

Figure A-FBDAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 99

5

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@A330

SERVICE BULLETIN

**CONF 002

ITEM PN DESCRIPTION

HOLE Y DIAMETER

37

38

39

40

F5332433520000

F5332433520200

F5332433520400

F5332433520600

PLUG

PLUG

PLUG

PLUG

11.5mm

(0.4528in.)

11.518mm

(0.4535in.)

13.1mm

(0.5157in.)

15mm

(0.5906in.)

15.018mm

(0.5913in.)

17mm

(0.6693in.)

17.018mm

(0.67in.)

APPLY MAT No. 09−005

1

2

3

4

27

MIN MAX

13.118mm

(0.5165in.)

DETAIL F

5 AFTER ASSEMBLY

APPLY MAT No. 09−002B AND 09−028A

APPLY MAT No. 09−002B

APPLY MAT No. 09−016B

OR

OR

OR

AFTER

37

38

39

40

NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C

(0.02in x 0.02in)

CHAMFER 0.5mm x 0.5mm

6 APPLY MAT No. 16−001B AFTER ASSEMBLY

1

2

3

4 5

6

OR

70

71

64

G_SB_573098_5_BDAA_04_00

Figure A-FBDAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 100

5

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

SERVICE BULLETIN

**CONF 002

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

BOLT

PN DESCRIPTION

7.849mm

(0.309in.)

REMARKS

NOMINAL

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

51

7.809mm

(0.307in.)

63

71

27 ASNA2531−6 NUT

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

9.53mm

(0.375in.)

9.53mm

(0.375in.)

9.60mm

(0.378in.)

9.60mm

(0.378in.) 2

3

STDN

10.177mm

(0.401in.)

10.177mm

(0.401in.)

BOLT

BOLT

EN6115−6Y14

27 ASNA2531−6 NUT

WASHER

NSA5372−616B

52

31 ASNA2531−5 NUT

EN6115−5−13

EN6115−5−14

OR

70 NSA5372−616A

OR

71

WASHER

NSA5372−616B

70 NSA5372−616A

OR

64 EN6115−6Y11

G_SB_573098_5_BDAA_05_01

Figure A-FBDAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 101

5

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

SERVICE BULLETIN

**CONF 002

A

Z141−142

A

FR40

FR47

B

B

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STGR1

C

Y1959

G_SB_573098_5_BEAA_01_00

Figure A-FBEAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without

crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 102

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40

SECTION

E−E

C

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

(4) (2)

(1)

BEFORE

BEFORE

STRG 1

FR40 DATUM

VIEW INSIDE CENTER TANK AT FR40

(3)

(0.512in.)

(5)

DIA 13mm

(41)

HOLE A

HOLE 5

HOLE 6

HOLE 7

STGR 1

SECTION

D−D

(6)

(7)

BEFORE

G_SB_573098_5_BEAA_02_00

Figure A-FBEAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without

crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 103

5

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

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

FR40

11.8mm MINIMUM

C

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

AFTER

(0.465in.)

STGR 1 27

39

31

VIEW INSIDE CENTER TANK AT FR40

3

2

HOLE A

HOLE 5

HOLE 6

HOLE 7

DETAIL F

STGR 1

SECTION

AFTER

SECTION

D−D

AFTER

E−E

63

27

3

3

3

3

APPLY MAT No. 09−002B

51

52

OR

G_SB_573098_5_BEAA_03_00

64

70

71

OR

70

71

OR

Figure A-FBEAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without

crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 104

5

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

SERVICE BULLETIN

**CONF 002

ITEM PN DESCRIPTION

HOLE Y DIAMETER

39 F5332433520400 PLUG 15mm

(0.5906in.)

15.018mm

(0.5913in.)

27

39

MIN MAX

DETAIL F

AFTER

(0.02in x 0.02in)

CHAMFER 0.5mm x 0.5mm

APPLY MAT No. 09−005

1

2

3

4

5 AFTER ASSEMBLY

APPLY MAT No. 09−002B AND 09−028A

APPLY MAT No. 09−002B

APPLY MAT No. 09−016B

NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C

6 APPLY MAT No. 16−001B AFTER ASSEMBLY

1

2

3

5 4

6

G_SB_573098_5_BEAA_04_00

70

71

OR

64

Figure A-FBEAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without

crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 105

5

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

SERVICE BULLETIN

**CONF 002

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

BOLT

PN DESCRIPTION

7.849mm

(0.309in.)

REMARKS

NOMINAL

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

51

7.809mm

(0.307in.)

63

71

27 ASNA2531−6 NUT

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

9.53mm

(0.375in.)

9.53mm

(0.375in.)

9.60mm

(0.378in.)

9.60mm

(0.378in.) 2

3

STDN

10.177mm

(0.401in.)

10.177mm

(0.401in.)

BOLT

BOLT

EN6115−6Y14

27 ASNA2531−6 NUT

WASHER

NSA5372−616B

52

31 ASNA2531−5 NUT

EN6115−5−13

EN6115−5−14

OR

70 NSA5372−616A

OR

71

WASHER

NSA5372−616B

70 NSA5372−616A

OR

64 EN6115−6Y11

G_SB_573098_5_BEAA_05_01

Figure A-FBEAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.) without

crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 106

5

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

SERVICE BULLETIN

**CONF 002

A

Z141−142

A

FR40

FR47

B

B

B

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

FR40 DATUM

STGR1

C

Y1959

G_SB_573098_5_BFAA_01_00

Figure A-FBFAA - Sheet 01

Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm

(0.591 in.)) without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 107

5

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

SERVICE BULLETIN

**CONF 002

FR40 DATUM

FR40

SECTION

E−E

SECTION

C

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

STGR 1

(4) (4) (2)

(1) (3)

(6)

(7)

D−D

13mm DIA 15mm

(0.512in.) (0.591in.)

(41)

(5)

BEFORE

BEFORE

BEFORE

VIEW INSIDE CENTER TANK AT FR40

HOLE A

HOLE 5

HOLE 6

HOLE 7

Y1959

STGR 1

G_SB_573098_5_BFAA_02_00

Figure A-FBFAA - Sheet 02

Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm

(0.591 in.)) without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 108

5

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@A330

SERVICE BULLETIN

**CONF 002

Y1959

FR40 DATUM

31 40 27

FR40

11.8mm MINIMUM

C

E

E

D

D

KEEL BEAM

CWB LOWER PANEL

FASTENER NOT AFFECTED

(0.465in.)

STGR 1

3

2

HOLE A

HOLE 5

HOLE 6

HOLE 7

VIEW INSIDE CENTER TANK AT FR40

DETAIL F

SECTION

AFTER

AFTER

STGR 1

E−E

SECTION

D−D

AFTER

63

27

3

3

3

3

APPLY MAT No. 09−002B

51

52

OR

G_SB_573098_5_BFAA_03_00

64

70

71

OR

70

71

OR

Figure A-FBFAA - Sheet 03

Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm

(0.591 in.)) without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 109

5

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SERVICE BULLETIN

**CONF 002

ITEM PN DESCRIPTION

HOLE Y DIAMETER

40 F5332433520600 PLUG 17mm

(0.6693in.)

17.018mm

(0.67in.)

27

40

MIN MAX

DETAIL F

(0.02in x 0.02in)

CHAMFER 0.5mm x 0.5mm

APPLY MAT No. 09−005

1

2

3

4

5 AFTER ASSEMBLY

APPLY MAT No. 09−002B AND 09−028A

APPLY MAT No. 09−002B

APPLY MAT No. 09−016B

NOTE :

APPLY MAT. No. 13−002 ATER BORING AND APPLY MAT. No 16−001B AND 16−002C

6 APPLY MAT No. 16−001B AFTER ASSEMBLY

1

2

3

5 4

6

G_SB_573098_5_BFAA_04_00

70

71

OR

64

AFTER

Figure A-FBFAA - Sheet 04

Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm

(0.591 in.)) without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 110

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SERVICE BULLETIN

**CONF 002

MIN. MAX.

HOLE

SYMBOL ITEM

HOLE DIAMETER

BOLT

PN DESCRIPTION

7.849mm

(0.309in.)

REMARKS

NOMINAL

MIN. MAX.

HOLE

SYMBOL ITEM PN DESCRIPTION REMARKS

MIN. MAX.

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

51

7.809mm

(0.307in.)

63

71

27 ASNA2531−6 NUT

12−1−N 10.219mm

(0.402in.)

SECOND

OVERSIZE

9.53mm

(0.375in.)

9.53mm

(0.375in.)

9.60mm

(0.378in.)

9.60mm

(0.378in.) 2

3

STDN

10.177mm

(0.401in.)

10.177mm

(0.401in.)

BOLT

BOLT

EN6115−6Y14

27 ASNA2531−6 NUT

WASHER

NSA5372−616B

52

31 ASNA2531−5 NUT

EN6115−5−13

EN6115−5−14

OR

70 NSA5372−616A

OR

71

WASHER

NSA5372−616B

70 NSA5372−616A

OR

64 EN6115−6Y11

G_SB_573098_5_BFAA_05_01

Figure A-FBFAA - Sheet 05

Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or = 15mm

(0.591 in.)) without crack detected)

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

REVISION No.: 02 - Jun 15/11 Page: 111

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SERVICE BULLETIN

This Page Intentionally Left Blank

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

REVISION No.: 02 - Jun 15/11 Page: 112

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SERVICE BULLETIN

APPENDIX 01 - Inspection Report

**CONF ALL

(1) Inspection Report

The results of the accomplishment of this Service Bulletin, including no findings, replacement

or actions to be done, must be forwarded to AIRBUS Department AI/SEES1, on the attached

inspection report sheet.

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

REVISION No.: 02 - Jun 15/11 Page: 1

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SERVICE BULLETIN

APPENDIX 01 - Inspection Report

**CONF ALL

SERVICE BULLETIN No. : A330−57−3098

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

FINDINGS : YES NO

DATE OF INSPECTION

INSPECTION METHOD : SPECIAL DETAILED

HOLE 5 LH

SIDE NO CRACK CRACK DIAMETER

HOLE 6 LH

HOLE 7 LH

HOLE A LH

HOLE 5 RH

HOLE 6 RH

HOLE 7 RH

HOLE A RH

PLEASE PRECISE OTHER FINDINGS :

LH

RH

HOLE 5 HOLE 6 HOLE 7 HOLE A

NOMINAL DIAMETER

HOLE 5 HOLE 6 HOLE 7 HOLE A

FIRST OVERSIZE

HOLE 5 HOLE 6 HOLE 7 HOLE A

SECOND OVERSIZE

INSTALLATION OF THE FASTENER AT :

G_SB_573098_5_AAAA_01_00

INSPECTION REPORT

Figure A-FAAAA - Sheet 01

Inspection Report

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

REVISION No.: 02 - Jun 15/11 Page: 2

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SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION

IN THE JUNCTION KEEL BEAM FITTING AT FR.40

MODIFICATION No.: 56467S18944

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

REVISION No.: 02 - Jun 15/11 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: Aug 30/07 SERVICE BULLETIN No.: A330-57-3098

REVISION No.: 02 - Jun 15/11 Page: 1

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