@A330

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT (Full Scale

Fatigue Test). Recently it appears necessary to modify this inspection due to the availability of in

service findings in the Frame 40 Rear Fitting. The latter were discovered thanks to the HF/EC Rototest

inspections done during the embodiment of the modification 52094S17923 through recommended

Service Bulletin No. A330-57-3083 which has pre-modification 44360S13013 and 44360S13482 and

post-modification 44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity.

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web - above

Center Wing Box lower panel, left and right sides for all A330 aircraft pre-modification 55306S18660

and 55792S18775 embodiments. The aim of this Inspection Service Bulletin is to implement the

corrective inspection necessary to the in-service aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair

Instruction R57115092, Inspection task of this ISB is not valid for the repaired side(s); dedicated RDAS

instructions have to be followed.

For aircraft previously inspected as per Technical Disposition ref. LR57D11029170, LR57D11023714,

LR57D11029172 or LR57D11030740, next inspection is due based on ISB 57-3115 interval value or

dedicated RDAS instruction requirements in case of deviation to the Technical Disposition instructions.

Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical web above Center

Wing Box lower panel, left and right sides and will contribute to maintain the structural integrity of the

area.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 1

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@A330

SERVICE BULLETIN

SUMMARY

The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and 44360S13482 , Pre

modification 55306S18660 and Pre modification 55792S18775 will be superseded by accomplishment

of Service Bulletin No. A330-57-3115.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts

Kit 573115A02R02 2 3,600.00 Screws, Washers, Nuts

TOTAL 7,700.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts

Kit 573115A03R02 2 3,100.00 Screws, Washers, Nuts

TOTAL 7,200.00

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts

Kit 573115A04R03 2 2,100.00 Screws, Washers, Nuts

TOTAL 6,200.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 2

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts

Kit 573115A05R02 2 4,500.00 Screws, Washers, Nuts

TOTAL 8,600.00

**CONF 005

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts

**CONF 006

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts

**CONF 007

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts

EFFECTIVITY

**CONF ALL

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

38W AAR ACA ACI AEA AFR ALK ASY AZA BEL BER BMA BTV

C9G CAL CCA CES CPA CRL CSC CSN DAH DAL DGA DLH EDW

EIN ETD EVA FWI GFA GIA GRL HDA HFY HVN I2L IAC ISS

IWD IYE JAV JST KAL KLM MAS MON MSR OHY PAL QAF QFA

QTR RSY RYN SAI SAS TAM TAP TCX THA THY TSC UAE USA

VKG VOZ XAX XLF

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.007

OEB None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

SUMMARY

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT ref. 999.0086/11 and 999.0082/12

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 002

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 003

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

SUMMARY

**CONF 004

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 005

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 006

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 007

Task 573115-832-801-001: Inspection

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

Task 573115-833-801-001: Repair

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

APPENDICES

**CONF ALL

Appendix 01 : Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

NOTE:

HOLE OF THE AREA A TO BE INSPECTED

A

HOLES OF THE AREA B TO BE INSPECTED

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

Z141 Z142 − 

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, B

A 260

24, 261, 262, 263

G_SB_573115_5_SAAA_01_04

Figure A-FSAAA - Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 6

5

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

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

55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN

ANGLE AT FR.40 (ADAPTATION SOLUTION)) and Mod. No. 55792S18775

(REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) are not embodied.

(1) Models

330-202 330-203 330-223 330-243 330-301 330-302 330-303 330-321

330-322 330-323 330-341 330-342 330-343

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0066 0070-0072 0077

0082-0083 0086-0087 0095-0096 0098-0099 0102 0106-0107 0109 0111-0113 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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

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

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

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

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

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

0489-0491 0493-0494 0496-0498 0500-0513 0515-0516 0518-0519 0521-0522

0524-0527 0529-0530 0532-0533 0535-0536 0539 0542 0548-0553 0555 0558

0564-0565 0567-0568 0570-0571 0573-0574 0576 0578-0579 0581 0584 0587-0588

0591 0593 0595 0597 0600 0602-0603 0605 0607 0609-0610 0612 0614 0616 0618

0620-0621 0623 0625 0627 0629 0631-0638 0640-0642 0644-0645 0647-0650

0652-0659 0661-0667 0669-0671 0673-0676 0678-0680 0682-0684 0686-0688

0690-0693 0695-0697 0699-0701 0703-0705 0707-0709 0711-0714 0716-0718

0720-0722 0724-0726 0728-0730 0732-0735 0737-0739 0741-0743 0745-0747

0749-0752 0754-0756 0758-0760 0769-0770 0772-0774 0776-0778 0780-0782

0784-0786 0788-0789 0791-0792 0795-0797 0799 0801-0803 0805-0807 0809-0811

0813-0815 0817-0823 0826

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

38W 0401

AAR 0640 0676 0708 0772 0803

ACA 0277 0279 0284 0344 0400 0408 0412 0419

ACI 0507 0510

AEA 0505 0526 0551 0597 0733 0745 0749 0814

AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519

0567 0584 0657

ALK 0303 0306 0311 0313 0404 0456 0627

ASY 0747

AZA 0272 0339

BEL 0030 0037 0045 0082 0095 0229 0249 0324

BER 0288 0322 0403 0432 0444 0454 0469 0476 0493 0665 0739

BMA 0398

BTV 0205 0330

C9G 0461

CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0725 0752 0769

0805 0823

CCA 0750 0756 0759 0780 0785 0797 0810 0815

CES 0713 0720 0728 0732 0735 0773 0777 0781 0782 0791 0821

CPA 0012 0102 0113 0118 0121 0155 0386 0389 0393 0418 0420 0421

0423 0439 0539 0548 0565 0669 0673 0679 0776

CRL 0285 0320

CSC 0462

CSN 0649 0652 0656 0664 0818

DAH 0644 0647 0650 0653 0667

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

OPERATOR MSN

DAL 0524 0533 0542 0549 0552 0578 0588 0591 0609 0614 0618 0620

0621 0631 0633 0663 0674 0690 0718 0722 0778 0784 0796 0799

0806 0817

DGA 0240

DLH 0570 0576 0579 0629 0636 0642 0645 0648 0687 0701

EDW 0291

EIN 0269 0397

ETD 0658 0688 0717 0724 0729 0730 0737 0751 0788 0807 0809

EVA 0530 0535 0555 0573 0587 0634 0655 0661 0678 0693 0755

FWI 0253 0758

GFA 0276 0281 0286 0287 0334 0340 0532

GIA 0138 0140 0144 0148 0153 0165

GRL 0230

HDA 0017 0071 0083 0099 0106 0109 0234 0244 0405 0479 0512 0581

0654 0662 0692 0716 0741 0786

HFY 0096 0127 0211 0262

HVN 0275 0294 0299 0366

I2L 0358 0364 0527 0529 0822

IAC 0353 0362

ISS 0802

IWD 0670

IYE 0625 0632

JAV 0255

JST 0506 0508 0513 0522

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

0351 0368 0425 0428 0484 0490 0550

KLM 0682 0686 0703 0738 0770 0801 0811 0819

MAS 0077 0107 0116 0119 0290 0296 0300

MON 0261 0265

MSR 0600 0610 0666 0683 0696 0709 0726

OHY 0072 0087 0098 0143

PAL 0183 0184 0188 0189 0191 0198 0200 0203

QAF 0487 0605

QFA 0553 0558 0564 0574 0593 0595 0603 0695 0705 0712

QTR 0441 0473 0489 0511 0521 0571 0612 0616 0623 0637 0638 0659

0680 0684 0711 0721 0734 0743 0746 0760 0789 0792 0813 0820

0826

RSY 0120 0171

RYN 0343

SAI 0055 0070 0086

SAS 0496 0497 0515 0568

TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 0700

TAP 0181 0195 0223 0305 0308 0312 0317

TCX 0254 0266 0301

THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346

THY 0463 0504 0697 0704 0742 0754 0774

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

OPERATOR MSN

TSC 0111 0132 0177 0250 0271 0369 0407 0427 0480 0795

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

0384 0392 0396 0409 0437 0451 0452 0455 0491 0494 0509 0518

0525 0536

USA 0315 0323 0333 0337 0342 0370 0375 0380 0388

VKG 0309 0349 0356 0357

VOZ 0365 0372

XAX 0054

XLF 0501 0635

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064

0065 0066 0070 0071 0072 0077 0082 0083 0086 0087 0095

0096 0098 0099 0102 0106 0107 0109 0111 0112

001

0113 0116 0118 0119 0120 0121 0122 0127 0132 002

0138 0140 0143 0144 0155 004

0148 0153 0162 0165 0171 0172 003

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

005

0511 006

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

MSN CONFIGURATION

0513 0515 0516 0518 0519 0521 0524 0525 0526 0527 0529

0530 0532 0533 0535 0536 0539 0542 0548 0549 0550 0551

0552 0553 0555 0558 0564 0565 0567 0568 0570 0571 0573

0574 0576 0578 0579 0581 0584 0587 0588 0591 0593 0595

0597 0600 0602 0603 0605 0607 0609 0610 0612 0614 0616

0618 0620 0621 0623 0625 0627 0629 0631 0632 0633 0634

0635 0636 0637 0638 0640 0641 0642 0644 0645 0647 0648

0649 0650 0652 0653 0654 0655 0656 0657 0658 0659 0661

0662 0663 0664 0665 0666 0667 0669 0670 0671 0673 0674

0675 0676 0678 0679 0680 0682 0683 0684 0686 0687 0688

0690 0691 0692 0693 0695 0696 0697 0699 0700 0701 0703

0704 0705 0707 0708 0709 0711 0712 0713 0714 0716 0717

0718 0720 0721 0722 0724 0725 0726 0728 0729 0730 0732

0733 0734 0735 0737 0738 0739 0741 0742 0743 0745 0746

0747 0749 0750 0751 0752 0754 0755 0756 0758 0759 0760

0769 0770 0772 0773 0774 0776 0777 0778 0780 0781 0782

0784 0785 0786 0788 0789 0791 0792 0795 0796 0797 0799

0801 0802 0803 0805 0806 0807 0809 0810 0811 0813 0814

0815 0817 0818 0819 0820 0821 0822 0823 0826

007

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT

SPAR (SERIAL SOLUTION)) are not embodied and on which Service Bulletin No.

A330-57-3032 is accomplished (or Mod No. 43577S12677 (MODIFY LOWER KEEL

FITTING AND FORWARD LOWER SHELL CONNECT.(RETROFIT SOLUTION VIA SB

ONLY)) is embodied).

**CONF 002

Config. 002 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and Mod No.

41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) is embodied and on which

Service Bulletin No. A330-57-3046 is accomplished (or Mod No. 44440S13324

(REINFORCE KEEL ANGLE OF FRONT SPAR (RETROFIT SOLUTION)) is embodied).

**CONF 003

Config. 003 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No.

44440S13090 (MODIFY LOWER KEEL FITTING AND FWD LOWER SHELL

CONNECTION (SERIAL SOLUTION)) and Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) are embodied.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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@A330

SERVICE BULLETIN

**CONF 004

Config. 004 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No.

44440S13276 (REINFORCE LOWER KEEL ANGLE OF FRONT SPAR (ADAPTATION

SOLUTION)) and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS)

are embodied.

**CONF 005

Config. 005 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)) and Mod No. 41652S11819 (INTRODUCE

A340 COMMONALITY ITEMS) are embodied and on which Mod No. 49202S16307

(REINFORCE SECTION 15/21) is not embodied.

**CONF 006

Config. 006 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)), Mod No. 50755S16633 (REDUCE

APPLICATION OF MOD 49194 AND 49202), Mod No. 49202S16307 (REINFORCE

SECTION 15/21) and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY

ITEMS) are embodied.

**CONF 007

Config. 007 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND

FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40

AND FRONT SPAR (SERIAL SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340

COMMONALITY ITEMS) and Mod No. 49202S16307 (REINFORCE SECTION 15/21)

are embodied and on which Mod No. 55306S18660 (REPLACE THE ONE-PIECE

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

Mod No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIES AIRCRAFT)) are

not embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 573115A01R02 2

Kit 573115A02R02 2

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 573115A01R02 2

Kit 573115A03R02 2

Consumable CMLA01 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 6

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SERVICE BULLETIN

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 573115A01R02 2

Kit 573115A04R03 2

Consumable CMLA01 1

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Kit 573115A01R02 2

Kit 573115A05R02 2

Consumable CMLA01 1

**CONF 005 thru 007

MATERIAL QTY PER A/C SEE NOTES

Kit 573115A06R03 2

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT

(Full Scale Fatigue Test). Recently it appears necessary to modify this inspection due to

the availability of in service findings in the Frame 40 Rear Fitting. The latter were

discovered thanks to the HF/EC Rototest inspections done during the embodiment of the

modification 52094S17923 through recommended Service Bulletin No. A330-57-3083

which has pre-modification 44360S13013 and 44360S13482 and post-modification

44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity.

(2) Objective/Action

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40

Vertical Web - above Center Wing Box lower panel, left and right sides for all A330

aircraft pre-modification 55306S18660 and 55792S18775 embodiments. The aim of this

Inspection Service Bulletin is to implement the corrective inspection necessary to the inservice aircraft.

For aircraft on which FR40 web is already repaired on one side or on both sides as per

Repair Instruction R57115092, Inspection task of this ISB is not valid for the repaired

side(s); dedicated RDAS instructions have to be followed.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 7

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SERVICE BULLETIN

For aircraft previously inspected as per Technical Disposition ref. LR57D11029170,

LR57D11023714, LR57D11029172 or LR57D11030740, next inspection is due based

on ISB 57-3115 interval value or dedicated RDAS instruction requirements in case of

deviation to the Technical Disposition instructions.

(3) Advantages

Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical

web above Center Wing Box lower panel, left and right sides and will contribute to

maintain the structural integrity of the area.

(4) Operational/Maintenance Consequences

The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and

44360S13482 , Pre modification 55306S18660 and Pre modification 55792S18775 will

be superseded by accomplishment of Service Bulletin No. A330-57-3115.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 8

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SERVICE BULLETIN

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 9

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SERVICE BULLETIN

**CONF 002

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 10

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SERVICE BULLETIN

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 003

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 11

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SERVICE BULLETIN

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 12

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SERVICE BULLETIN

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 004

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 13

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SERVICE BULLETIN

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 005

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 14

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SERVICE BULLETIN

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 15

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@A330

SERVICE BULLETIN

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 006

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

Side

(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the

Area A of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 16

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@A330

SERVICE BULLETIN

transition fit, RH Side

(5) Install New same Fasteners of the Area B in transition fit, LH Side

(6) Install New same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, LH Side

(10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First

Oversize in comparison with the current hole diameter, RH Side

(11) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(12) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side

(16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side

(17) Install New Fasteners of the Area B in transition fit, LH Side

(18) Install New Fasteners of the Area B in transition fit, RH Side

**CONF 007

Task 573115-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH

Side

(2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH

Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 17

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SERVICE BULLETIN

Side

(5) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side

(6) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side

(7) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(8) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 573115-833-801-001: Repair

(1) Install New same Fastener of the Area A in transition fit, LH Side

(2) Install New same Fastener of the Area A in transition fit, RH Side

(3) Install New same Fasteners of the Area B in transition fit, LH Side

(4) Install New same Fasteners of the Area B in transition fit, RH Side

(5) Oversize the Hole of the Area A to First Oversize in comparison with the current hole

diameter, LH Side

(6) Oversize the Hole of the Area A to First Oversize in comparison with the current hole

diameter, RH Side

(7) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, LH Side

(8) Oversize the Holes of the Area B to First Oversize in comparison with the current

hole diameter, RH Side

(9) Install New Fastener of the Area A in transition fit, LH Side

(10) Install New Fastener of the Area A in transition fit, RH Side

(11) Install New Fasteners of the Area B in transition fit, LH Side

(12) Install New Fasteners of the Area B in transition fit, RH Side

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 18

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SERVICE BULLETIN

(2) Accomplishment Timescale

**CONF 001

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

001 for LH Side

and to SUBTASK

573115-832-009

001 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 001 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Config. 001 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 19

5

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@A330

SERVICE BULLETIN

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 001 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

002 for LH Side

and to SUBTASK

573115-832-011

002 for RH Side

Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 001 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

001 for LH Side

and to SUBTASK

573115-832-009

001 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 20

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New same

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-001

004 for LH Side

and/or to

SUBTASK

573115-833-010

002 for RH Side

and

Before next flight None None

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

001 for LH Side

and/or to

SUBTASK

573115-832-009

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

No crack found

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 21

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Pre SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 22

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-007

001 for LH Side

and/or to

SUBTASK

573115-833-018

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

001 for LH Side

and/or to

SUBTASK

573115-832-009

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 23

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 001 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

FC optimized set:

26,000 FC/85,100

FH

or

FH optimized set:

20,500 FC/138,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fastener Post SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-002

001 for LH Side

and/or to

SUBTASK

573115-833-011

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 24

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Post SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 25

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Post SB

57-3083 in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-008

001 for LH Side

and/or to

SUBTASK

573115-833-019

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 26

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 001 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

002 for LH Side

and to SUBTASK

573115-832-011

002 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/ 93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-022

002 for LH Side

and/or to

SUBTASK

573115-833-013

002 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

002 for LH Side

and/or to

SUBTASK

573115-832-011

002 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 27

5

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@A330

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Holes

to First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-023

002 for LH Side

and/or to

SUBTASK

573115-833-017

002 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-024

002 for LH Side

and/or to

SUBTASK

573115-833-021

002 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

002 for LH Side

and/or to

SUBTASK

573115-832-011

002 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 28

5

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@A330

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 002

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

003 for LH Side

and to SUBTASK

573115-832-009

003 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 002 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Config. 002 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 29

5

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@A330

SERVICE BULLETIN

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 002 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

001 for LH Side

and to SUBTASK

573115-832-011

001 for RH Side

Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 002 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

003 for LH Side

and to SUBTASK

573115-832-009

003 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 30

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New same

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-001

001 for LH Side

and/or to

SUBTASK

573115-833-010

001 for RH Side

and

Before next flight None None

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

003 for LH Side

and/or to

SUBTASK

573115-832-009

003 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

No crack found

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 31

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Pre SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 32

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-007

001 for LH Side

and/or to

SUBTASK

573115-833-018

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

003 for LH Side

and/or to

SUBTASK

573115-832-009

003 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 33

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 002 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

FC optimized set:

26,000 FC/85,100

FH

or

FH optimized set:

20,500 FC/138,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fastener Post SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-002

001 for LH Side

and/or to

SUBTASK

573115-833-011

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 34

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Post SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 35

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Post SB

57-3083 in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-008

001 for LH Side

and/or to

SUBTASK

573115-833-019

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 36

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 002 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

001 for LH Side

and to SUBTASK

573115-832-011

001 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/ 93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-022

001 for LH Side

and/or to

SUBTASK

573115-833-013

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

001 for LH Side

and/or to

SUBTASK

573115-832-011

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 37

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Holes

to First Oversize in

comparison with

the current holes

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-023

001 for LH Side

and/or to

SUBTASK

573115-833-017

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-024

001 for LH Side

and/or to

SUBTASK

573115-833-021

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes of the

Fasteners Holes

on LH and/or RH

Sides, refer to

SUBTASK

573115-832-010

001 for LH Side

and/or to

SUBTASK

573115-832-011

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 38

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 003

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

004 for LH Side

and to SUBTASK

573115-832-009

004 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 003 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 39

5

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

SERVICE BULLETIN

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 003 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 003 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

003 for LH Side

and to SUBTASK

573115-832-011

003 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 40

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 003 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

004 for LH Side

and to SUBTASK

573115-832-009

004 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 41

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New same

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-001

005 for LH Side

and/or to

SUBTASK

573115-833-010

003 for RH Side

and

Before next flight None None

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

004 for LH Side

and/or to

SUBTASK

573115-832-009

004 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

No crack found

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 42

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Pre SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 43

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-007

001 for LH Side

and/or to

SUBTASK

573115-833-018

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

004 for LH Side

and/or to

SUBTASK

573115-832-009

004 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 44

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 003 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

FC optimized set:

26,000 FC/85,100

FH

or

FH optimized set:

20,500 FC/138,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fastener Post SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-002

001 for LH Side

and/or to

SUBTASK

573115-833-011

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 45

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Post SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 46

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Post SB

57-3083 in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-008

001 for LH Side

and/or to

SUBTASK

573115-833-019

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 47

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 003 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

003 for LH Side

and to SUBTASK

573115-832-011

003 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/ 93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-022

003 for LH Side

and/or to

SUBTASK

573115-833-013

003 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

003 for LH Side

and/or to

SUBTASK

573115-832-011

003 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 48

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Holes

to First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-023

003 for LH Side

and/or to

SUBTASK

573115-833-017

003 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-024

003 for LH Side

and/or to

SUBTASK

573115-833-021

003 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

003 for LH Side

and/or to

SUBTASK

573115-833-011

003 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 49

5

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

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 004

Table 1: Rototest Inspection of the Fasteners Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

005 for LH Side

and to SUBTASK

573115-832-009

005 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 004 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Config. 004 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 50

5

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

SERVICE BULLETIN

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 004 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

004 for LH Side

and to SUBTASK

573115-832-011

004 for RH Side

Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 004 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

005 for LH Side

and to SUBTASK

573115-832-009

005 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 51

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New same

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-001

008 for LH Side

and/or to

SUBTASK

573115-833-010

004 for RH Side

and

Before next flight None None

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

005 for LH Side

and/or to

SUBTASK

573115-832-009

005 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

No crack found

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 52

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Pre SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 53

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-007

001 for LH Side

and/or to

SUBTASK

573115-833-018

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

005 for LH Side

and/or to

SUBTASK

573115-832-009

005 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 54

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 004 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

FC optimized set:

26,000 FC/85,100

FH

or

FH optimized set:

20,500 FC/138,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fastener Post SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-002

001 for LH Side

and/or to

SUBTASK

573115-833-011

001 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 55

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Post SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 56

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Post SB

57-3083 in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-008

001 for LH Side

and/or to

SUBTASK

573115-833-019

001 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Holes of the

Fastener Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 57

5

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@A330

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 004 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

004 for LH Side

and to SUBTASK

573115-832-011

004 for RH Side

FC optimized set:

17,400 FC/57,100

FH

or

FH optimized set:

13,800 FC/ 93,700

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-022

004 for LH Side

and/or to

SUBTASK

573115-833-013

004 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

004 for LH Side

and/or to

SUBTASK

573115-832-011

004 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 58

5

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@A330

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Holes

to First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-023

004 for LH Side

and/or to

SUBTASK

573115-833-017

004 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-024

004 for LH Side

and/or to

SUBTASK

573115-833-021

004 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

004 for LH Side

and/or to

SUBTASK

573115-832-011

004 for RH Side

None None FC optimized set:

12,800 FC/41,900

FH

or

FH optimized set:

10,300 FC/69,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 59

5

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@A330

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 005

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

006 for LH Side

and to SUBTASK

573115-832-009

006 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 005 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Config. 005 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 60

5

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@A330

SERVICE BULLETIN

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 005 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to SUBTASK

573115-832-011

005 for RH Side

Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 61

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A330-200,

WV020 Serie

FC optimized

set: 16,100

FC/56,600 FH

or

FH optimized

set: 12,600

FC/82,200 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 16,300

FC/53,200 FH

or

FH optimized

set: 12,900

FC/87,300 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 15,900

FC/52,000 FH

or

FH optimized

set: 12,600

FC/85,300 FH

See NOTE (*)

Config. 005 Pre

Service Bulletin

No.

A330-57-3083

A330-300,

WV022

Do a Rototest

Inspection Pre

SB No.

A330-57-3083

of the Hole on

LH and RH

Sides, refer to

SUBTASK

573115-832-003

006 for LH Side

and to

SUBTASK

573115-832-009

006 for RH

Side

FC optimized

set: 15,500

FC/50,800 FH

or

FH optimized

set: 12,300

FC/83,300 FH

See NOTE (*)

2,400 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 62

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

same Fastener

Pre SB No.

A330-57-3083

in transition fit

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-001

007 for LH Side

and/or to

SUBTASK

573115-833-010

005 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No crack found

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection Pre

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 63

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No crack found A330-300,

WV022

Repeat the

Rototest

Inspection Pre

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

Or

All A330 WV Apply Service

Bulletin No.

A330-57-3083

and

Before next

flight

No crack found None None

All A330 WV Do a Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH

Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 64

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found All A330 WV Oversize the

Hole Pre SB

No.

A330-57-3083

to First

Oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

All A330 WV Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 65

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

Fastener Pre

SB No.

A330-57-3083

in transition fit

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-007

015 for LH Side

and/or to

SUBTASK

573115-833-018

003 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No Crack found

after rototest

inspection

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection Pre

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 66

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No Crack found

after rototest

inspection

A330-300,

WV022

Repeat the

Rototest

Inspection Pre

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 67

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

SB

A330-57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A330-200,

WV020 Serie

FC optimized

set: 24,600

FC/86,200 FH

or

FH optimized

set: 18,900

FC/123,300 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 24,800

FC/81,300 FH

or

FH optimized

set: 19,500

FC/132,300 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 24,300

FC/79,400 FH

or

FH optimized

set: 19,100

FC/129,200 FH

See NOTE (*)

Config. 005

Post Service

Bulletin No.

A330-57-3083

A330-300,

WV022

Do a Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and to

SUBTASK

573115-832-005

001 for RH

Side

FC optimized

set: 23,700

FC/77,400 FH

or

FH optimized

set: 18,600

FC/126,100 FH

See NOTE (*)

2,400 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 68

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

SB

A330-57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

same Fastener

Post SB No.

A330-57-3083

in transition fit

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-002

015 for LH Side

and/or to

SUBTASK

573115-833-011

003 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No crack found

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 69

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

SB

A330-57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No crack found A330-300,

WV022

Repeat the

Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

Crack found All A330 WV Oversize the

Hole Post SB

No.

A330-57-3083

to First

Oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

All A330 WV Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 70

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

SB

A330-57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

Fastener Post

SB 57-3083 in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-008

015 for LH Side

and/or to

SUBTASK

573115-833-019

003 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No Crack found

after rototest

inspection

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 71

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

SB

A330-57-3083

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No Crack found

after rototest

inspection

A330-300,

WV022

Repeat the

Rototest

Inspection Post

SB No.

A330-57-3083

of the Hole on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 72

5

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@A330

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A330-200,

WV020 Serie

FC optimized

set: 16,100

FC/56,600 FH

or

FH optimized

set: 12,600 FC/

82,200 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 16,300

FC/53,200 FH

or

FH optimized

set: 12,900 FC/

87,300 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 15,900

FC/52,000 FH

or

FH optimized

set: 12,600 FC/

85,300 FH

See NOTE (*)

Config. 005

A330-300,

WV022

Do a Rototest

Inspection of

the Holes on

LH and RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to

SUBTASK

573115-832-011

005 for RH

Side

FC optimized

set: 15,500

FC/50,800 FH

or

FH optimized

set: 12,300 FC/

83,300 FH

See NOTE (*)

2,400 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 73

5

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@A330

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

same

Fasteners in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-022

005 for LH Side

and/or to

SUBTASK

573115-833-013

005 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No crack found

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 74

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No crack found A330-300,

WV022

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

Crack found All A330 WV Oversize the

Holes to First

Oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-023

005 for LH Side

and/or to

SUBTASK

573115-833-017

005 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

All A330 WV Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 75

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

Fasteners in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-024

005 for LH Side

and/or to

SUBTASK

573115-833-021

005 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 Serie

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV010 Serie

FC optimized

set: 10,000

FC/32,900 FH

or

FH optimized

set: 8,050

FC/54,700 FH

See NOTE (*)

No Crack found

after rototest

inspection

A330-300,

WV020 Serie

except WV022

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 76

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

No Crack found

after rototest

inspection

A330-300,

WV022

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 77

5

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@A330

SERVICE BULLETIN

**CONF 006

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

006 for LH Side

and to SUBTASK

573115-832-009

006 for RH Side

Refer to Table 3

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

Config. 006 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

Config. 006 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 78

5

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@A330

SERVICE BULLETIN

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 006 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to SUBTASK

573115-832-011

005 for RH Side

Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 006 Pre

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Pre SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-003

006 for LH Side

and to SUBTASK

573115-832-009

006 for RH Side

FC optimized set:

16,100 FC/56,600

FH

or

FH optimized set:

12,600 FC/82,200

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 79

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New same

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-001

007 for LH Side

and/or to

SUBTASK

573115-833-010

005 for RH Side

and

Before next flight None None

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

Or

Apply Service

Bulletin No.

A330-57-3083

and

Before next flight None None

No crack found

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

Refer to Table 4

Perform this rototest at the Threshold from SB

No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 80

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Pre SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-004

001 for LH Side

and/or to

SUBTASK

573115-833-014

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 81

5

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@A330

SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Pre SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-007

015 for LH Side

and/or to

SUBTASK

573115-833-018

003 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Pre SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-003

006 for LH Side

and/or to

SUBTASK

573115-832-009

006 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 82

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 006 Post

Service Bulletin

No. A330-57-3083

Do a Rototest

Inspection Post SB

No. A330-57-3083

of the Hole on LH

and RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and to SUBTASK

573115-832-005

001 for RH Side

FC optimized set:

24,600 FC/86,200

FH

or

FH optimized set:

18,900 FC/123,300

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fastener Post SB

No. A330-57-3083

in transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-002

015 for LH Side

and/or to

SUBTASK

573115-833-011

003 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 83

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Hole

Post SB No.

A330-57-3083 to

First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-005

001 for LH Side

and/or to

SUBTASK

573115-833-015

001 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 84

5

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@A330

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area

A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from SB

A330-57-3083

embodiment

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Install New

Fastener Post SB

57-3083 in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-008

015 for LH Side

and/or to

SUBTASK

573115-833-019

003 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

Post SB No.

A330-57-3083 of

the Hole on LH

and/or RH Sides,

refer to SUBTASK

573115-832-004

001 for LH Side

and/or to

SUBTASK

573115-832-005

001 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 85

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 006 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to SUBTASK

573115-832-011

005 for RH Side

FC optimized set:

16,100 FC/56,600

FH

or

FH optimized set:

12,600 FC/ 82,200

FH

See NOTE (*)

2,400 FC or 24

months from SB

issuance date

None

Install New same

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-022

005 for LH Side

and/or to

SUBTASK

573115-833-013

005 for RH Side

and

No crack found Before next flight None None

Repeat the

Rototest Inspection

of the Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 86

5

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

SERVICE BULLETIN

Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from first

flight (whichever

occurs first)

Grace period

(whichever occurs

first)

Repetitive Interval

Crack found Oversize the Holes

to First Oversize in

comparison with

the current hole

diameter on LH

and/or RH Sides,

refer to SUBTASK

573115-833-023

005 for LH Side

and/or to

SUBTASK

573115-833-017

005 for RH Side

and

do a rototest

inspection

Before next flight None None

Crack found after

rototest inspection

Contact Airbus Before next flight None None

Install New

Fasteners in

transition fit on LH

and/or RH Sides,

refer to SUBTASK

573115-833-024

005 for LH Side

and/or to

SUBTASK

573115-833-021

005 for RH Side

and

No Crack found Before next flight None None

after rototest

inspection

Repeat the

Rototest Inspection

of the Fastener

Holes on LH

and/or RH Sides,

refer to SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH Side

None None FC optimized set:

10,000 FC/35,100

FH

or

FH optimized set:

8,100 FC/52,700

FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 87

5

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

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF 007

Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 007 Do a Rototest

Inspection of the

Hole on LH and

RH Sides, refer to

SUBTASK

573115-832-006

001 for LH Side

and to SUBTASK

573115-832-012

001 for RH Side

Refer to Table 3

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 007 Do a Rototest

Inspection of the

Holes on LH and

RH Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to SUBTASK

573115-832-011

005 for RH Side

Refer to Table 4

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 88

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A330-200,

WV020 and

WV050 Series

FC optimized

set: 24,600

FC/86,200 FH

or

FH optimized

set: 18,900

FC/123,300 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 24,300

FC/79,400 FH

or

FH optimized

set: 19,100

FC/129,200 FH

See NOTE (*)

Config. 007

A330-300,

WV022 and

WV050 Series

Do a Rototest

Inspection of

the Hole on LH

and RH Sides,

refer to

SUBTASK

573115-832-006

001 for LH Side

and to

SUBTASK

573115-832-012

001 for RH

Side

FC optimized

set: 23,700

FC/77,400 FH

or

FH optimized

set: 18,600

FC/126,100 FH

See NOTE (*)

2,400 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 89

5

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

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

same Fastener

in transition fit

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-003

001 for LH Side

and/or to

SUBTASK

573115-833-012

001 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 and

WV050 Series

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

No crack found

A330-300,

WV022 and

WV050 Series

Repeat the

Rototest

Inspection of

the Hole on LH

and/or RH

Sides, refer to

SUBTASK

573115-832-006

001 for LH Side

and/or to

SUBTASK

573115-832-012

001 for RH

Side

None None

FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 90

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found All A330 WV Oversize the

Hole to First

Oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-006

001 for LH Side

and/or to

SUBTASK

573115-833-016

001 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

All A330 WV Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 91

5

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

SERVICE BULLETIN

Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

Fastener in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-009

001 for LH Side

and/or to

SUBTASK

573115-833-020

001 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 and

WV050 Series

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

No Crack found

after rototest

inspection

A330-300,

WV022 and

WV050 Series

Repeat the

Rototest

Inspection of

the Hole on LH

and/or RH

Sides, refer to

SUBTASK

573115-832-006

001 for LH Side

and/or to

SUBTASK

573115-832-012

001 for RH

Side

None None

FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 92

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A330-200,

WV020 and

WV050 Series

FC optimized

set: 16,100

FC/56,600 FH

or

FH optimized

set: 12,600 FC/

82,200 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 15,900

FC/52,000 FH

or

FH optimized

set: 12,600 FC/

85,300 FH

See NOTE (*)

Config. 007

A330-300,

WV022 and

WV050 Series

Do a Rototest

Inspection of

the Holes on

LH and RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and to

SUBTASK

573115-832-011

005 for RH

Side

FC optimized

set: 15,500

FC/50,800 FH

or

FH optimized

set: 12,300 FC/

83,300 FH

See NOTE (*)

2,400 FC or 24

months from

SB issuance

date

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 93

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

same

Fasteners in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-022

005 for LH Side

and/or to

SUBTASK

573115-833-013

005 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 and

WV050 Series

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

No crack found

A330-300,

WV022 and

WV050 Series

Repeat the

Rototest

Inspection of

the Holes on

LH and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None

FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 94

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found All A330 WV Oversize the

Holes to First

Oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

573115-833-023

005 for LH Side

and/or to

SUBTASK

573115-833-017

005 for RH

Side

and

do a rototest

inspection

Before next

flight

None None

Crack found

after rototest

inspection

All A330 WV Contact Airbus Before next

flight

None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 95

5

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

SERVICE BULLETIN

Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold to be

counted from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A330 WV Install New

Fasteners in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

573115-833-024

005 for LH Side

and/or to

SUBTASK

573115-833-021

005 for RH

Side

and

Before next

flight

None None

A330-200,

WV020 and

WV050 Series

FC optimized

set: 10,000

FC/35,100 FH

or

FH optimized

set: 8,100

FC/52,700 FH

See NOTE (*)

A330-300,

WV020 Serie

except WV022

FC optimized

set: 9,850

FC/32,200 FH

or

FH optimized

set: 7,900

FC/53,500 FH

See NOTE (*)

No Crack found

after rototest

inspection

A330-300,

WV022 and

WV050 Series

Repeat the

Rototest

Inspection of

the Fastener

Holes on LH

and/or RH

Sides, refer to

SUBTASK

573115-832-010

005 for LH Side

and/or to

SUBTASK

573115-832-011

005 for RH

Side

None None

FC optimized

set: 9,600

FC/31,400 FH

or

FH optimized

set: 7,700

FC/52,300 FH

See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that

better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 96

5

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

SERVICE BULLETIN

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the (thresholds

and/or intervals and/or date) given above but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

**CONF ALL

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 97

5

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@A330

SERVICE BULLETIN

Task 573115-832-801-001: Inspection

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 98

5

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SERVICE BULLETIN

Task 573115-833-801-001: Repair

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF 002

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 99

5

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

SERVICE BULLETIN

Task 573115-832-801-001: Inspection

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 100

5

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@A330

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF 003

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 101

5

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

SERVICE BULLETIN

Task 573115-832-801-001: Inspection

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 102

5

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

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF 004

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 103

5

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

SERVICE BULLETIN

Task 573115-832-801-001: Inspection

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 104

5

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

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF 005

Task 573115-832-801-001: Inspection

Get Access 12.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 105

5

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

SERVICE BULLETIN

Task 573115-832-801-001: Inspection

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 106

5

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

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 107

5

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

SERVICE BULLETIN

**CONF 006

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, LH Side

0.50

Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame

40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 108

5

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

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A Post Service Bulletin

No. A330-57-3083 to First Oversize in comparison with

the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

0.25

Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 109

5

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

SERVICE BULLETIN

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF 007

Task 573115-832-801-001: Inspection

Get Access 12.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Hole

of the Area A at FR 40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR 40, RH Side

0.25

Do a Rototest Inspection of the Hole of the Area A of

the Frame 40, LH Side

0.50

Do a Rototest Inspection of the Hole of the Area A of

the Frame 40, RH Side

0.50

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

5.00

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

5.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 573115-833-801-001: Repair

Get Access 12.00

On Aircraft

Install New same Fastener of the Area A in transition

fit, LH Side

0.25

Install New same Fastener of the Area A in transition

fit, RH Side

0.25

Install New same Fasteners of the Area B in transition

fit, LH Side

2.50

Install New same Fasteners of the Area B in transition

fit, RH Side

2.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 110

5

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

SERVICE BULLETIN

Task 573115-833-801-001: Repair

Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, LH Side

0.25

Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, RH Side

0.25

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

2.50

Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

2.50

Install New Fastener of the Area A in transition fit, LH

Side

0.25

Install New Fastener of the Area A in transition fit, RH

Side

0.25

Install New Fasteners of the Area B in transition fit, LH

Side

2.50

Install New Fasteners of the Area B in transition fit, RH

Side

2.50

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the

manhours stating post Service Bulletin No.A330-57-3083 apply.

For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the

manhours stating pre Service Bulletin No.A330-57-3083 apply.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 111

5

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

SERVICE BULLETIN

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 002

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 003

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 004

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 005

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 006

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 28-80-00 36-22-19

52-30-00 53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

**CONF 007

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24

20-21-11 21-20-00 21-52-41

24-41-00 25-52-00 25-80-00

27-84-41 36-22-19 52-30-00

53-35-13

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-57-3083

Standards Manual (SM)

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11

51-24-00 51-40-00 51-42-00

51-43-00 51-44-00 51-44-11

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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**CONF ALL

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Airworthiness Limitation Section

(ALS) Part 2

Maintenance Planning Document (MPD) 571102

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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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 573115A01R02

Kit 573115A02R02

Kit 573115A03R02

Kit 573115A04R03

Kit 573115A05R02

Kit 573115A06R03

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 573115A01R02

Cost 2,050.00 USD

Availability 120 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 573115A02R02

Cost 1,800.00 USD

Availability 120 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 573115A03R02

Cost 1,550.00 USD

Availability 120 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 573115A04R03

Cost 1,050.00 USD

Availability 120 calendar days from receipt of order

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The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 573115A05R02

Cost 2,250.00 USD

Availability 120 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

Kit 573115A06R03

Cost 2,950.00 USD

Availability 120 calendar days from receipt of order

The MH and parts required for ISB are not subject to any specific commercial policy.

However, in case of significant repair, Airbus may provide an industry support. A

dedicated sentence is included is next paragraph to refer to CSD in such a case.

B. INDUSTRY SUPPORT INFORMATION

This Service Bulletin is subject to a specific support provided by AIRBUS. For more details

regarding the applicable commercial policy, please contact your Customer Support Director.

C. LIST OF COMPONENTS

Kit 573115A01R02

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

NOTES

1 EN6115V6-16 3 SCREW

2 ASNA2531-6 8 NUT

3 EN6115V6X16 3 SCREW

4 EN6115V6-18 1 SCREW

5 EN6115V6X18 1 SCREW

6 EN6115V6-20 4 SCREW

7 EN6115V6X20 4 SCREW

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

94 EN6115V7-16 1 SCREW

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

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

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

to part number relationship.

Kit 573115A02R02

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

NOTES

9 ASNA2531-5 1 NUT

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

NOTES

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

91 EN6115-5X18 1 SCREW

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

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

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

to part number relationship.

Kit 573115A03R02

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

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

53 MS21250-07018 1 SCREW

54 NSA5399-6-16A 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

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

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

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

to part number relationship.

Kit 573115A04R03

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

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 2 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

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

NOTES

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

88 EN6115-5-19 1 SCREW

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

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

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

to part number relationship.

Kit 573115A05R02

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

NOTES

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

57 EN6115-5Y18 1 SCREW

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

85 MS21250-07023 1 SCREW

86 NSA5399-6-25A 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

91 EN6115-5X18 1 SCREW

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

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

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

to part number relationship.

Kit 573115A06R03

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

NOTES

1 EN6115V6-16 3 SCREW

2 ASNA2531-6 9 NUT

3 EN6115V6X16 3 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

65 NSA5398-6-18A 1 SCREW

73 EN6115V5-20 1 SCREW

74 EN6115V5X20 1 SCREW

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

NOTES

75 EN6115V6-24 4 SCREW

76 EN6115V6X24 4 SCREW

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

91 EN6115V6-19 1 SCREW

92 EN6115V6X19 1 SCREW

93 EN6115V6-22 1 SCREW

94 EN6115V7-16 1 SCREW

95 EN6115V6X22 1 SCREW

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

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

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

trichloroethane (methyl Chloroform) 11-004 As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

NOTE: To accomplish this Service Bulletin it is necessary to use the expendable

parts listed in the AMM Task 21-52-41-400-801 mentioned in paragraph

close-up.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed

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in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-up

and in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup.

(3) Special Tools

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 573115-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

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

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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**CONF 002

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 003

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 004

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 005

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 006

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 39.00

ELAPSED TIME (HOURS) 39.00

**CONF 007

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 38.00

ELAPSED TIME (HOURS) 38.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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**CONF ALL

A. GENERAL

CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft

under zero stress jacking. No zero stress jacking is required also in case of

concurrent accomplishment of maintenance tasks or SBs in frame 40 area.

However this is applicable only for the accomplishment of these tasks/SBs

without deviation. Indeed, in case of heavy repair, a temporary re-installation

of fasteners and/or zero stress jacking procedure could be anticipated.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

NOTE: The purpose of flow charts are for information only to show the various

Inspection/Repair phases described in this Service Bulletin.

**CONF 001

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

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(2) Subtask 573115-839-001-001 - 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 002

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 573115-839-001-001 - 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: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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**CONF 003

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 573115-839-001-001 - 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 004

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 573115-839-001-001 - 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 005

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

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(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 573115-839-001-001 - 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 006

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 127

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SERVICE BULLETIN

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

(2) Subtask 573115-839-001-001 - 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 007

(1) Subtask 573115-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) 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.

(g) Remove and install the fasteners in accordance with SRM 51-42-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 128

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@A330

SERVICE BULLETIN

(2) Subtask 573115-839-001-001 - 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

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 129

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SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE

NOTES

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 130

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@A330

SERVICE BULLETIN

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 131

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@A330

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

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

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 132

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@A330

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 002

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 133

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 134

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 135

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 136

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@A330

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 137

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@A330

SERVICE BULLETIN

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 003

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 138

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@A330

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 139

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@A330

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 140

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@A330

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

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

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 141

5

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@A330

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 004

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 142

5

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 143

5

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 144

5

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

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 145

5

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

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 146

5

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

SERVICE BULLETIN

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 005

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 147

5

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@A330

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 148

5

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@A330

SERVICE BULLETIN

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 149

5

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@A330

SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

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

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 150

5

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

SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 006

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 151

5

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

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 152

5

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

SERVICE BULLETIN

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 153

5

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

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 154

5

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

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 155

5

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

SERVICE BULLETIN

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

**CONF 007

(1) Subtask 573115-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-001-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 156

5

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@A330

SERVICE BULLETIN

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

(7) Subtask 573115-110-001-001 - Cleaning of the Structure

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

trichloroethane (methyl

Chloroform)

11-004

Lint-Free Cotton Cloth 19-003 As required

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 159

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SERVICE BULLETIN

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection surface with

trichloroethane

(methyl Chloroform)

11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(8) Subtask 573115-210-001-001 - Preparation of the Inspection Area

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damage or discontinuities.

(d) Make sure that there is no :

1 Corrosion damage :

- If you find corrosion damage, work In accordance with SRM 51-22-00,

Page Block 001 for types, inspection, removal and corrosion protection.

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) :

- If you find this type of damage, work In accordance with SRM 51-11-00,

Page Block 001 for damage classification and corrective action.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(3) Subtask 573115-832-002-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 002 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573115-832-008-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-011 002 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573115-832-003-001 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 163

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SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 004 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 001 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-001 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 165

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SERVICE BULLETIN

References

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 002 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 001 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 001 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 168

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SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-002 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 170

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SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (56) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (59) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 171

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SERVICE BULLETIN

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (50) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-022 002 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 002 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 002 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 002 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 002 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 172

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SERVICE BULLETIN

(b) For the inspection report, refer to Appendix 01.

(10) Subtask 573115-832-011-002 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 173

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SERVICE BULLETIN

1 Screw Item (56) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (59) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (50) Discard

1 Washer Item (58) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 002 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 002 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 002 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 002 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 174

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-011 002 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

**CONF 002

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 003 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 175

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SERVICE BULLETIN

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 003 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 176

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SERVICE BULLETIN

(3) Subtask 573115-832-002-009 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573115-832-008-002 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-011 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 177

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@A330

SERVICE BULLETIN

(5) Subtask 573115-832-003-003 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 001 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 178

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-003 003 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 003 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-003 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 179

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SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 001 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 003 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 180

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SERVICE BULLETIN

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 003 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 181

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SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 182

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SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 183

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SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 184

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SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 185

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@A330

SERVICE BULLETIN

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (8) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (50) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (54) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-022 001 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 186

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@A330

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-023 001 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 001 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(10) Subtask 573115-832-011-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 187

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SERVICE BULLETIN

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (8) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (50) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (54) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 188

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-013 001 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 001 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 001 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

**CONF 003

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 189

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@A330

SERVICE BULLETIN

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 004 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 190

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SERVICE BULLETIN

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 004 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(3) Subtask 573115-832-002-010 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 003 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 191

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SERVICE BULLETIN

(4) Subtask 573115-832-008-003 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) Do SUBTASK 573115-832-011 003 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573115-832-003-004 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 192

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@A330

SERVICE BULLETIN

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 005 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 004 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 193

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@A330

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 004 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-004 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 194

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@A330

SERVICE BULLETIN

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 003 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 004 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 195

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@A330

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-009 004 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 196

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 197

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 198

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@A330

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-003 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 199

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@A330

SERVICE BULLETIN

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (88) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (64) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 200

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-022 003 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 003 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 003 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 003 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 003 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(10) Subtask 573115-832-011-003 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 201

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@A330

SERVICE BULLETIN

References

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

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (88) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Remove fastener from hole H263, RH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 202

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SERVICE BULLETIN

1 Screw Item (64) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 003 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 003 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 003 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 003 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 003 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 203

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SERVICE BULLETIN

**CONF 004

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 005 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 204

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SERVICE BULLETIN

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 005 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(3) Subtask 573115-832-002-011 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 205

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

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 004 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573115-832-008-004 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-011 004 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573115-832-003-005 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 206

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 008 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 005 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 207

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SERVICE BULLETIN

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 005 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-005 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 208

5

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

SERVICE BULLETIN

References

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 004 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 005 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 209

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SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 005 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 210

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SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 211

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SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 212

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 001 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-004 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 213

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (91) Discard

1 Washer Item (67) Discard

1 Nut Item (83) Discard

- Remove fastener from hole H262, LH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 214

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@A330

SERVICE BULLETIN

1 Screw Item (84) Discard

1 Washer Item (88) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (86) Discard

1 Washer Item (58) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-022 004 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 004 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 004 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 004 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 215

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@A330

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-010 004 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(10) Subtask 573115-832-011-004 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (4) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 216

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SERVICE BULLETIN

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (6) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (91) Discard

1 Washer Item (67) Discard

1 Nut Item (83) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (84) Discard

1 Washer Item (88) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (86) Discard

1 Washer Item (58) Discard

1 Washer Item (51) Discard

1 Nut Item (52) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 004 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 217

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-011 004 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 004 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 004 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 004 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

**CONF 005

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 218

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SERVICE BULLETIN

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 219

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SERVICE BULLETIN

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(3) Subtask 573115-832-002-012 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 220

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SERVICE BULLETIN

(4) Subtask 573115-832-008-005 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573115-832-003-006 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 221

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SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 007 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 222

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SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 015 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-006 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 223

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SERVICE BULLETIN

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 005 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 003 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 224

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@A330

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-009 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 225

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SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-002 015 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 015 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 226

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-011 003 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 227

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SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 003 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 228

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@A330

SERVICE BULLETIN

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 229

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(10) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 230

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@A330

SERVICE BULLETIN

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (61) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 231

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SERVICE BULLETIN

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 232

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@A330

SERVICE BULLETIN

**CONF 006

(1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 233

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@A330

SERVICE BULLETIN

(2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) If Service Bulletin No. A330-57-3083 is accomplished:

1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 4 of the Planning Information Paragraph

E.(2).

(b) If Service Bulletin No. A330-57-3083 is not accomplished:

1 Do SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

at the threshold given in the table 3 of the Planning Information Paragraph

E.(2).

or

Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

threshold given in the table 4 of the Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

(3) Subtask 573115-832-002-012 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 234

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573115-832-008-005 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA Sheet 01 to Fig. A-FFAAA Sheet 03

(a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 573115-832-003-006 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 235

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove the fastener from hole H260, LH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-001 007 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 236

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SERVICE BULLETIN

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

2 If crack is found:

a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-007 015 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-003 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-009-006 - Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 237

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@A330

SERVICE BULLETIN

References

Service Bulletin (SB) A330-57-3083

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

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

(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove the fastener from hole H260, RH side:

1 Screw Item (6) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-010 005 Install New same Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 3 of the Planning Information Paragraph E.(2).

or

b Apply Service Bulletin No. A330-57-3083 before next flight and do

SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH

Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 238

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@A330

SERVICE BULLETIN

2 If crack is found:

a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A

Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-018 003 Install New Fastener Pre

Service Bulletin No. A330-57-3083 of the Area A in transition

fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-009 006 Do a Rototest Inspection Pre Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 3 of the

Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 239

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-002 015 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, LH Side and check if crack is found with a

rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-008 015 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-004 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 240

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@A330

SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

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

(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the

area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 241

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@A330

SERVICE BULLETIN

1 If no crack is found:

a Apply SUBTASK 573115-833-011 003 Install New same Fastener Post

Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side

before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No.

A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the

interval given in the table 4 of the Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A

Post Service Bulletin No. A330-57-3083 to First Oversize in comparison

with the current hole diameter, RH Side and check if crack is found with

a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-019 003 Install New Fastener

Post Service Bulletin No. A330-57-3083 of the Area A in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-005 001 Do a Rototest Inspection Post Service

Bulletin No. A330-57-3083 of the Hole of the Area A of the

Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(9) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 242

5

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (93) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 243

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@A330

SERVICE BULLETIN

1 Nut Item (2) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 244

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@A330

SERVICE BULLETIN

(10) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (73) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 245

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@A330

SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 246

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<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

**CONF 007

(1) Subtask 573115-832-001-008 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A330-57-3083

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 573115-832-006 001 Do a Rototest Inspection of the Hole of the

Area A of the Frame 40, LH Side at the threshold given in the table 3 of the

Planning Information Paragraph E.(2).

(2) Subtask 573115-832-007-002 - Do a Special Detailed Inspection of the Fastener

Hole of the Area A at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

(a) Do SUBTASK 573115-832-012 001 Do a Rototest Inspection of the Hole of the

Area A of the Frame 40, RH Side at the threshold given in the table 3 of the

Planning Information Paragraph E.(2).

(3) Subtask 573115-832-002-013 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 573115-832-008-006 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Refer to Fig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02

(a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

(5) Subtask 573115-832-006-001 - Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

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

(a) Do a rototest inspection of the hole of the area A of the frame 40, LH side.

- Remove fastener from hole H260, LH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, LH side.

Refer to Fig. A-FCBAA Sheet 01

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-003 001 Install New same Fastener of the

Area A in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-006 001 Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, LH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-006 001 Oversize the Hole of the Area A to

First Oversize in comparison with the current hole diameter, LH Side and

check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-009 001 Install New Fastener of

the Area A in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-006 001 Do a Rototest Inspection of the Hole of

the Area A of the Frame 40, LH Side at the interval given in the

table 4 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 573115-832-012-001 - Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

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

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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

(a) Do a rototest inspection of the hole of the area A of the frame 40, RH side.

- Remove fastener from hole H260, RH side:

1 Screw Item (77) Discard

1 Nut Item (78) Discard

- Do a rototest inspection at the hole H260, RH side.

Refer to Fig. A-FCBAA Sheet 01

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-012 001 Install New same Fastener of the

Area A in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-012 001 Do a Rototest Inspection of the Hole of the Area A

of the Frame 40, RH Side at the interval given in the table 4 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-016 001 Oversize the Hole of the Area A to

First Oversize in comparison with the current hole diameter, RH Side and

check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-020 001 Install New Fastener of

the Area A in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-012 001 Do a Rototest Inspection of the Hole of

the Area A of the Frame 40, RH Side at the interval given in

the table 4 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 251

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SERVICE BULLETIN

(7) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, LH side.

- Remove fasteners from hole H12 and H14, LH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, LH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, LH side:

4 Screw Item (75) Discard

4 Nut Item (2) Discard

- Remove fastener from hole H261, LH side:

1 Screw Item (73) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

1 Nut Item (9) Discard

- Remove fastener from hole H262, LH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, LH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the

Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, LH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-010 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 253

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SERVICE BULLETIN

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

References

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

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Fig. A-FCBAA

Rototest Inspection of the Fastener Hole

of the Area A and Area B of the Frame

40, LH and RH Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

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

(a) Do a rototest inspection of the holes of the area B of the frame 40, RH side.

- Remove fasteners from hole H12 and H14, RH side:

2 Screw Item (1) Discard

2 Nut Item (2) Discard

- Remove fastener from hole H13, RH side:

1 Screw Item (91) Discard

1 Nut Item (2) Discard

- Remove fasteners from holes H21, H22, H23 and H24, RH side:

4 Screw Item (75) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 254

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SERVICE BULLETIN

4 Nut Item (2) Discard

- Remove fastener from hole H261, RH side:

1 Screw Item (73) Discard

1 Nut Item (9) Discard

- Remove fastener from hole H262, RH side:

1 Screw Item (93) Discard

1 Nut Item (2) Discard

- Remove fastener from hole H263, RH side:

1 Screw Item (61) Discard

1 Washer Item (62) Discard

1 Nut Item (63) Discard

- Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261,

H262 and H263, LH side.

Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02

Refer to NTM 51-10-01

1 If no crack is found:

a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B

to First Oversize in comparison with the current hole diameter, RH Side

and check if crack is found with a rototest inspection before next flight.

<1> If no crack is found after the rototest inspection:

<a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of

the Area B in transition fit, RH Side before next flight

and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 255

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

573115-832-011 005 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

<2> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

(b) For the inspection report, refer to Appendix 01.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 573115-700-001-002 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 256

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SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 002

(1) Subtask 573115-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

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SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 003

(1) Subtask 573115-700-001-003 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 258

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SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 004

(1) Subtask 573115-700-001-004 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 259

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SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 005

(1) Subtask 573115-700-001-006 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 260

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SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 006

(1) Subtask 573115-700-001-007 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 261

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@A330

SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 007

(1) Subtask 573115-700-001-008 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-001

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 262

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@A330

SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF ALL

E. CLOSE-UP

NOTE: This paragraph is only applicable if no crack found after the inspection of the

holes.

**CONF 001

(1) Subtask 573115-410-001-002 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 263

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SERVICE BULLETIN

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-002-002 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 264

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@A330

SERVICE BULLETIN

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 265

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@A330

SERVICE BULLETIN

**CONF 002

(1) Subtask 573115-410-001-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 266

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@A330

SERVICE BULLETIN

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-002-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 267

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@A330

SERVICE BULLETIN

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 003

(1) Subtask 573115-410-001-003 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 268

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@A330

SERVICE BULLETIN

References

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-002-003 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 269

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: This paragraph is apply only if no crack found after result the holes

inspection.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 270

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@A330

SERVICE BULLETIN

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 004

(1) Subtask 573115-410-001-004 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 004 Testing .

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 271

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@A330

SERVICE BULLETIN

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-002-004 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 272

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@A330

SERVICE BULLETIN

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 005

(1) Subtask 573115-410-001-006 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 273

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 006 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 274

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SERVICE BULLETIN

(2) Subtask 573115-410-002-006 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 006 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 275

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SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 006

(1) Subtask 573115-410-001-007 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 276

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SERVICE BULLETIN

SUBTASK 573115-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-002-007 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 28-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 277

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SERVICE BULLETIN

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 28-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 007

(1) Subtask 573115-410-001-008 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 278

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SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 008 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 279

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@A330

SERVICE BULLETIN

(2) Subtask 573115-410-002-008 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 008 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 280

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SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 281

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@A330

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 282

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SERVICE BULLETIN

Task 573115-833-801-001 - Repair

**CONF ALL

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

INCLUDED IN THE REFERENCED PROCEDURES

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

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

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 283

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SERVICE BULLETIN

**CONF 002

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 003

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 004

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 005

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 006

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 44.00

ELAPSED TIME (HOURS) 44.00

**CONF 007

Zone

130 137 138 192

Manpower

TOTAL MANHOURS 42.50

ELAPSED TIME (HOURS) 42.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 284

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SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 285

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SERVICE BULLETIN

**CONF 002

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF 003

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 286

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF 004

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 287

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF 005

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 288

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF 006

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 289

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF 007

(1) Subtask 573115-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 290

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SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-23-11

51-24-00

51-40-00

51-42-00

51-43-00

51-44-11

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.

(c) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(d) Use a non-metallic spatula to remove the sealant and clean the surfaces.

(e) Remove and install the fasteners in accordance with SRM 51-42-00.

(f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.

(g) Apply the sealant In accordance with SRM 51-24-00.

(h) Drill and deburr the holes in accordance with SRM 51-44-11.

(i) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(j) 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.

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

**CONF ALL

B. PREPARATION

NOTE: This PREPARATION procedure is already done in the INSPECTION task.

**CONF 001

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 291

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 292

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 293

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 002

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 294

5

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 295

5

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 296

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 003

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 297

5

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 298

5

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 299

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 004

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 300

5

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 301

5

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 302

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 005

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 303

5

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 304

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 305

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 006

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 306

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 307

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 308

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

**CONF 007

(1) Subtask 573115-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 309

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@A330

SERVICE BULLETIN

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task

12-34-24-860-802).

(b) Put the access platform(s) in position at doors 821 and 822.

(2) Subtask 573115-861-002-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801

(a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).

(3) Subtask 573115-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC

(a) Open, safety and tag this (these) circuit breaker(s) :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

721 PACK 1 L1 115VAC 1HH1 02 F

721 PACK 1 L2 115VAC 3HH1 04 K

721 PACK 1 L2 28VDC 4HH1 07 R

721 PACK 1 L1 28VDC 2HH1 08 T

722 PACK 2 L2 115VAC 3HH2 44 E

722 PACK 2 L1 115VAC 1HH2 48 H

722 PACK 2 L2 28VDC 4HH2 41 U

722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU :

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbutton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 310

5

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@A330

SERVICE BULLETIN

(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1

and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet

01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 311

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SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 27-84-41-000-802

Task 53-35-13-000-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

(a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) On the RH side, remove and retain the universal joint between the slat angle

gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 312

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@A330

SERVICE BULLETIN

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 573115-833-001-004 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 313

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-002 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 314

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SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 315

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 316

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-022-002 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 317

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

Kit 573115A02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 318

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SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-22A Item 59

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-18A Item 50

1 Washer ASNA2394EW6 Item 58

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 319

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SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-002 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

Kit 573115A02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

59 NSA5399-6-22A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 320

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@A330

SERVICE BULLETIN

References

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Nut ASNA2531-5 Item 9

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 321

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-22A Item 59

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-18A Item 50

1 Washer ASNA2394EW6 Item 58

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 322

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 323

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@A330

SERVICE BULLETIN

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 324

5

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@A330

SERVICE BULLETIN

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-002 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 325

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-002 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 326

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@A330

SERVICE BULLETIN

(13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 327

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 328

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@A330

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 329

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 330

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@A330

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-002 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 331

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 332

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the next nominal fastener at hole H262:

1 Bolt MS21250-07022 Item 60

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07018 Item 53

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-002 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 333

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

53 MS21250-07018 1 SCREW

57 EN6115-5Y18 1 SCREW

60 MS21250-07022 1 BOLT

82 ASNA2394EW7 2 WASHER

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAB

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 334

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the next nominal fastener at hole H262:

1 Bolt MS21250-07022 Item 60

1 Washer ASNA2394EW7 Item 82

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07018 Item 53

1 Washer ASNA2394EW7 Item 82

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 335

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@A330

SERVICE BULLETIN

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 002

(1) Subtask 573115-833-001-001 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 336

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-001 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 337

5

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

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 338

5

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

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 339

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-022-001 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 340

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

Kit 573115A03R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

54 NSA5399-6-16A 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 341

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-18A Item 50

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-16A Item 54

1 Washer NSA5372EW616B Item 51

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 342

5

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@A330

SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-001 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 1 SCREW

Kit 573115A03R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

50 NSA5399-6-18A 1 SCREW

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

54 NSA5399-6-16A 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 343

5

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

SERVICE BULLETIN

References

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

1 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 344

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-18A Item 50

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-16A Item 54

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 345

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 346

5

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@A330

SERVICE BULLETIN

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 347

5

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

SERVICE BULLETIN

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-001 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 348

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-001 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 349

5

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@A330

SERVICE BULLETIN

(13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 350

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 351

5

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@A330

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 352

5

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

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 353

5

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@A330

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-001 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 6 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A03R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

53 MS21250-07018 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 354

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 355

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y19 Item 10

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07018 Item 53

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07016 Item 55

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-001 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 356

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 6 NUT

3 EN6115V6X16 1 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A03R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

10 EN6115-5Y19 1 SCREW

53 MS21250-07018 1 SCREW

55 MS21250-07016 1 SCREW

80 NSA5372EW716B 2 WASHER

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 357

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y19 Item 10

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the next nominal fastener at hole H262:

1 Screw MS21250-07018 Item 53

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the next nominal fastener at hole H263:

1 Screw MS21250-07016 Item 55

1 Washer NSA5372EW716B Item 80

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 358

5

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@A330

SERVICE BULLETIN

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 003

(1) Subtask 573115-833-001-005 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 359

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-003 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 360

5

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@A330

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 361

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 362

5

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

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-022-003 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 363

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

Kit 573115A04R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

88 EN6115-5-19 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 364

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5-19 Item 88

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw MS21250-06016 Item 64

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 365

5

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@A330

SERVICE BULLETIN

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-003 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 4 SCREW

Kit 573115A04R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 2 WASHER

63 NSA5057-6 2 NUT

64 MS21250-06016 1 SCREW

88 EN6115-5-19 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 366

5

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

SERVICE BULLETIN

References

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5-19 Item 88

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 367

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw MS21250-06016 Item 64

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 368

5

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 369

5

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@A330

SERVICE BULLETIN

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 370

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@A330

SERVICE BULLETIN

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-003 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 371

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SERVICE BULLETIN

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-003 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 372

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@A330

SERVICE BULLETIN

(13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 373

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 374

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SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 375

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SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 376

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@A330

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-003 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A04R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 2 NUT

62 MS20002C6 2 WASHER

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 377

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 378

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw NSA5398-6-16A Item 66

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-003 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 379

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A04R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 EN6115-5X19 1 SCREW

9 ASNA2531-5 1 NUT

62 MS20002C6 2 WASHER

65 NSA5398-6-18A 1 SCREW

66 NSA5398-6-16A 1 SCREW

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 ASNA0094-6 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAC

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 380

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@A330

SERVICE BULLETIN

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115-5X19 Item 8

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw NSA5398-6-16A Item 66

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 381

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@A330

SERVICE BULLETIN

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 004

(1) Subtask 573115-833-001-008 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 382

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-004 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 383

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 384

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 385

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-022-004 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 386

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 1 SCREW

Kit 573115A05R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

51 NSA5372EW616B 2 WASHER

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

86 NSA5399-6-25A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 387

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SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

1 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-23A Item 84

1 Washer ASNA2394EW6 Item 58

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 388

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@A330

SERVICE BULLETIN

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-25A Item 86

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-004 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 7 NUT

4 EN6115V6-18 1 SCREW

6 EN6115V6-20 1 SCREW

Kit 573115A05R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

51 NSA5372EW616B 2 WASHER

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 389

5

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@A330

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 ASNA0094-6 2 NUT

58 ASNA2394EW6 2 WASHER

67 NSA5368PD516B 1 WASHER

83 NSA5050-5 1 NUT

84 NSA5399-6-23A 1 SCREW

86 NSA5399-6-25A 1 SCREW

91 EN6115-5X18 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-18 Item 4

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 390

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

1 Screw EN6115V6-20 Item 6

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115-5X18 Item 91

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw NSA5399-6-23A Item 84

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw NSA5399-6-25A Item 86

1 Washer ASNA2394EW6 Item 58

1 Washer NSA5372EW616B Item 51

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 391

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 392

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 393

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 394

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@A330

SERVICE BULLETIN

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-004 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-004 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 395

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAD Sheet 01 to Fig. A-FCAAD Sheet 03.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 396

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 397

5

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

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 398

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 399

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@A330

SERVICE BULLETIN

(16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 400

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-004 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A05R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 EN6115-5Y18 1 SCREW

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

85 MS21250-07023 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 401

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 402

5

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@A330

SERVICE BULLETIN

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw MS21250-07023 Item 85

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw MS21250-07025 Item 87

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-004 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 403

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 7 NUT

3 EN6115V6X16 2 SCREW

5 EN6115V6X18 1 SCREW

7 EN6115V6X20 4 SCREW

Kit 573115A05R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

57 EN6115-5Y18 1 SCREW

67 NSA5368PD516B 1 WASHER

80 NSA5372EW716B 2 WASHER

82 ASNA2394EW7 2 WASHER

83 NSA5050-5 1 NUT

85 MS21250-07023 1 SCREW

87 MS21250-07025 1 SCREW

90 NSA5057-7 2 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAD

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 404

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SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X18 Item 5

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X20 Item 7

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the second oversize fastener at hole H261:

1 Screw EN6115-5Y18 Item 57

1 Washer NSA5368PD516B Item 67

1 Nut NSA5050-5 Item 83

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw MS21250-07023 Item 85

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 405

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@A330

SERVICE BULLETIN

6 Install the first oversize fastener at hole H263:

1 Screw MS21250-07025 Item 87

1 Washer ASNA2394EW7 Item 82

1 Washer NSA5372EW716B Item 80

1 Nut NSA5057-7 Item 90

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 005

(1) Subtask 573115-833-001-007 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 406

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@A330

SERVICE BULLETIN

References

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-005 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 407

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-015 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 408

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-003 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 409

5

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 410

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SERVICE BULLETIN

(5) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 411

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SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 412

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 413

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 414

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SERVICE BULLETIN

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 415

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 416

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@A330

SERVICE BULLETIN

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 417

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 418

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@A330

SERVICE BULLETIN

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 419

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@A330

SERVICE BULLETIN

(13) Subtask 573115-833-007-015 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 420

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 573115-833-018-003 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 421

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-015 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 422

5

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

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573115-833-019-003 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 423

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 424

5

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@A330

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 425

5

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@A330

SERVICE BULLETIN

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 426

5

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

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 427

5

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@A330

SERVICE BULLETIN

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 428

5

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@A330

SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 006

(1) Subtask 573115-833-001-007 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 429

5

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

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-010-005 - Install New same Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 430

5

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@A330

SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-002-015 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 431

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-011-003 - Install New same Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 432

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V7-16 Item 94

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 433

5

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 434

5

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@A330

SERVICE BULLETIN

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 435

5

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 436

5

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@A330

SERVICE BULLETIN

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 437

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SERVICE BULLETIN

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 438

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SERVICE BULLETIN

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin

No. A330-57-3083 to First Oversize in comparison with the current hole diameter,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCCAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 439

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service

Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole

diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 440

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SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCDAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(11) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 441

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SERVICE BULLETIN

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(12) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(13) Subtask 573115-833-007-015 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 442

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SERVICE BULLETIN

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 443

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SERVICE BULLETIN

(14) Subtask 573115-833-018-003 - Install New Fastener Pre Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Removal/Installation of the Fastener Pre

Service Bulletin A330-57-3083 of the

Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCCAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 444

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SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 573115-833-008-015 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 445

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SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 573115-833-019-003 - Install New Fastener Post Service Bulletin No.

A330-57-3083 of the Area A in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

78 ASNA2531-7 1 NUT

79 EN6115V7X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 446

5

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@A330

SERVICE BULLETIN

References

Fig. A-FCDAA

Removal/Installation of the Fastener

Post Service Bulletin A330-57-3083 of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCDAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V7X16 Item 79

1 Nut ASNA2531-7 Item 78

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 447

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 448

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SERVICE BULLETIN

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(18) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 449

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@A330

SERVICE BULLETIN

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 450

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SERVICE BULLETIN

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 451

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SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF 007

(1) Subtask 573115-833-003-001 - Install New same Fastener of the Area A in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 452

5

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@A330

SERVICE BULLETIN

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(2) Subtask 573115-833-012-001 - Install New same Fastener of the Area A in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 1 SCREW

2 ASNA2531-6 1 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 453

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SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found, install the

fastener.

1 Install the fastener at hole H260:

1 Screw EN6115V6-16 Item 1

1 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 454

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 455

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 456

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@A330

SERVICE BULLETIN

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V6-16 2 SCREW

2 ASNA2531-6 8 NUT

9 ASNA2531-5 1 NUT

61 MS21250-06018 1 SCREW

62 MS20002C6 1 WASHER

63 NSA5057-6 1 NUT

73 EN6115V5-20 1 SCREW

75 EN6115V6-24 4 SCREW

91 EN6115V6-19 1 SCREW

93 EN6115V6-22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 Install the fasteners at holes H12 and H14:

2 Screw EN6115V6-16 Item 1

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 457

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@A330

SERVICE BULLETIN

2 Install the fastener at hole H13:

1 Screw EN6115V6-19 Item 91

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6-24 Item 75

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the fastener at hole H261:

1 Screw EN6115V5-20 Item 73

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the fastener at hole H262:

1 Screw EN6115V6-22 Item 93

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the fastener at hole H263:

1 Screw MS21250-06018 Item 61

1 Washer MS20002C6 Item 62

1 Nut NSA5057-6 Item 63

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 458

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(5) Subtask 573115-833-006-001 - Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCEAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(6) Subtask 573115-833-016-001 - Oversize the Hole of the Area A to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 459

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@A330

SERVICE BULLETIN

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area A, if crack is found, oversize the hole.

a Drill to the first oversize diameter in comparison with the hole H260 to the

dimension given in Fig. A-FCEAA Sheet 01.

b Do a rototest inspection of the drilled hole to check if the crack is still present.

Refer to NTM 51-10-01

(7) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 460

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SERVICE BULLETIN

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

(8) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in

comparison with the current hole diameter, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

References

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

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas B, if crack is found, oversize the

holes.

a Drill to the first oversize diameter in comparison with the current hole diameter

the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the

dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02.

b Do a rototest inspection of the drilled holes to check if the crack is still

present.

Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 461

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SERVICE BULLETIN

(9) Subtask 573115-833-009-001 - Install New Fastener of the Area A in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 462

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

(10) Subtask 573115-833-020-001 - Install New Fastener of the Area A in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 1 NUT

3 EN6115V6X16 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCEAA

Removal/Installation of the Fastener of

the Area A of the Frame 40, LH and RH

Sides

Sheet 01

Refer to Fig. A-FCEAA Sheet 01

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area A, if no crack is found:

1 Install the fastener at hole H260:

1 Screw EN6115V6X16 Item 3

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 463

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SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(11) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 464

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@A330

SERVICE BULLETIN

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 465

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SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(12) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 573115A06R03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2531-6 8 NUT

3 EN6115V6X16 2 SCREW

9 ASNA2531-5 1 NUT

52 ASNA0094-6 1 NUT

62 MS20002C6 1 WASHER

65 NSA5398-6-18A 1 SCREW

74 EN6115V5X20 1 SCREW

76 EN6115V6X24 4 SCREW

92 EN6115V6X19 1 SCREW

95 EN6115V6X22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 466

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAF

Removal/Installation of the Fasteners of

the Area B of the Frame 40, LH and RH

Sides

Sheet 01

Sheet 02

Refer to Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

Refer to AMM Task 20-21-11-911-801

In accordance with SRM 51-42-00, SRM 51-43-00

(a) Depending on inspection results of the area B, if no crack is found:

1 Install the first oversize fasteners at holes H12 and H14:

2 Screw EN6115V6X16 Item 3

2 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 Install the first oversize fastener at hole H13:

1 Screw EN6115V6X19 Item 92

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24:

4 Screw EN6115V6X24 Item 76

4 Nut ASNA2531-6 Item 2

Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 467

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@A330

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

4 Install the first oversize fastener at hole H261:

1 Screw EN6115V5X20 Item 74

1 Nut ASNA2531-5 Item 9

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

5 Install the first oversize fastener at hole H262:

1 Screw EN6115V6X22 Item 95

1 Nut ASNA2531-6 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

6 Install the first oversize fastener at hole H263:

1 Screw NSA5398-6-18A Item 65

1 Washer MS20002C6 Item 62

1 Nut ASNA0094-6 Item 52

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 573115-700-002-002 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 468

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 002

(1) Subtask 573115-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 469

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 003

(1) Subtask 573115-700-002-003 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 470

5

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 004

(1) Subtask 573115-700-002-004 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 471

5

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 005

(1) Subtask 573115-700-002-006 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 472

5

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 006

(1) Subtask 573115-700-002-007 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 473

5

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

**CONF 007

(1) Subtask 573115-700-002-008 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 474

5

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

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation

of the parts removed for the access SUBTASK 573115-010-003

001 Remove/Open for Access in the FWD Cargo-Compartment and

SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly

Fairing Area .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of Air Conditioning Pack

(Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 475

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@A330

SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 573115-410-003-002 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 476

5

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@A330

SERVICE BULLETIN

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-004-002 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 002 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 477

5

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@A330

SERVICE BULLETIN

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 002

(1) Subtask 573115-410-003-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 478

5

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@A330

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: This paragraph is apply only if no crack found after the result of the

inspection.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer toAMM Task

21-20-00-410-001 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-001 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 479

5

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@A330

SERVICE BULLETIN

(2) Subtask 573115-410-004-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 001 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 480

5

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@A330

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 003

(1) Subtask 573115-410-003-003 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 481

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@A330

SERVICE BULLETIN

SUBTASK 573115-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-004-003 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 482

5

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@A330

SERVICE BULLETIN

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 003 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 004

(1) Subtask 573115-410-003-004 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 483

5

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@A330

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 484

5

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

SERVICE BULLETIN

(2) Subtask 573115-410-004-004 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 004 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 485

5

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

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 005

(1) Subtask 573115-410-003-006 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 486

5

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@A330

SERVICE BULLETIN

SUBTASK 573115-700-001 006 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-004-006 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 487

5

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@A330

SERVICE BULLETIN

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 006 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 006

(1) Subtask 573115-410-003-007 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 488

5

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

SERVICE BULLETIN

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 489

5

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

SERVICE BULLETIN

(2) Subtask 573115-410-004-007 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 007 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 490

5

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@A330

SERVICE BULLETIN

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

**CONF 007

(1) Subtask 573115-410-003-008 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area

Work Zones and Access Panels

Zone Access/Work location

192 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 27-84-41-400-802

Task 53-35-13-400-802

Fig. A-FBBAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (Belly Fairing Area)

Sheet 01

Fig. A-FBCAA

Removal/Installation of the Ventilation

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 491

5

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@A330

SERVICE BULLETIN

SUBTASK 573115-700-001 008 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) On the RH side, install the retained universal joint between the slat angle gearbox

and the torque shaft (Refer to AMM Task 27-84-41-400-802).

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FBCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 573115-410-004-008 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Work Zones and Access Panels

Zone Access/Work location

130 Work location from Frame 39.1 to Frame 40

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 (FWD Cargo-Compartment)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 492

5

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@A330

SERVICE BULLETIN

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 573115-700-001 008 Testing .

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(e) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(3) Subtask 573115-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

(c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 493

5

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@A330

SERVICE BULLETIN

**CONF ALL

RH SIDE SHOWN

LH SIDE SYMMETRICAL

Z130

FR39.1

FR40

(11) (12)

(14)

(13)

B

B

B

A

A

G_SB_573115_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD CargoCompartment)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 494

5

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@A330

SERVICE BULLETIN

**CONF ALL

A

B

FR39.2

FR40.2

A

B

(26)

Z192

G_SB_573115_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 495

5

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@A330

SERVICE BULLETIN

**CONF ALL

FR39.2

FR40.2

B

(41)

A

B

A Z192

G_SB_573115_5_BCAA_01_01

Figure A-FBCAA - Sheet 01

Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 496

5

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@A330

SERVICE BULLETIN

**CONF 001

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAB_01_02

Figure A-FCAAB - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 497

5

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@A330

SERVICE BULLETIN

**CONF 001

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

01

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) 01

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

01

01

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

01

01

EN6115−5X18 SCREW

ASNA2531−5 NUT

EN6115−5Y18 SCREW

NUT

N

ASNA2531−5

91

9

57

9

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−18A SCREW

ASNA2394EW6 WASHER

ASNA0094−6 NUT

N MS21250−07018

50

58

52

53

N

82

90

02

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

ASNA2394EW7

NSA5057−7

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−22A SCREW

ASNA2394EW6 WASHER

ASNA0094−6 NUT

MS21250−07022

59

58

52

60

82

90

SCREW

WASHER

NUT

ASNA2394EW7

NSA5057−7

02

02

02

02

02

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(91)

(9)

(56)

(9)

(50)

(58)

(52)

(50)

(51)

(52)

(59)

(58)

(52)

(59)

(58)

(52)

ITEM REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

01

02

01

02

01

02

01

02

01

02

01

02

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.692 mm

(0.342 in)

8.732 mm

(0.343 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

G_SB_573115_5_CAAB_02_06

Figure A-FCAAB - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 498

5

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@A330

SERVICE BULLETIN

**CONF 002

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAA_01_03

Figure A-FCAAA - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 499

5

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

SERVICE BULLETIN

**CONF 002

HOLE

SYMBOL PN DESCRIPTION REMARKS

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

STANDARD FASTENER

IN TRANSITION FIT

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

IN TRANSITION FIT

(1)

(2)

(1)

(2)

01

N

HEAD ON THE VISIBLE SIDE

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) FIRST OVERSIZE 01

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

(4)

(2)

(1)

(2)

01

01

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

(6)

(2)

(6)

(2)

01

01

8.692 mm

(0.342 in)

8.732 mm

(0.343 in)

EN6115−5X19 SCREW

ASNA2531−5 NUT

EN6115−5Y19 SCREW

NUT

N

ASNA2531−5

(8)

(9)

(8)

(9)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−18A SCREW

NSA5372EW616B WASHER

ASNA0094−6 NUT

N MS21250−07018

(50)

(51)

(52)

(50)

N

(51)

(52)

NEXT NOMINAL

02

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

8.296 mm

(0.326 in)

8.335 mm

(0.328 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

NSA5372EW716B

NSA5057−7

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5399−6−16A SCREW

NSA5372EW616B WASHER

ASNA0094−6 NUT

MS21250−07016

(54)

(51)

(52)

(54)

(51)

(52)

SCREW

WASHER

NUT

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

NSA5372EW716B

NSA5057−7

02

02

02

02

02

NOTE:

01 DEPENDING ON INSPECTION RESULT

02

1

2

3

2

4

2

5

2

6

2

7

2

8

9

10

9

50

51

52

53

80

90

54

51

52

55

80

90

ITEM

INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

01

02

01

02

01

02

01

02

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

G_SB_573115_5_CAAA_02_06

Figure A-FCAAA - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 500

5

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

SERVICE BULLETIN

**CONF 003

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAC_01_02

Figure A-FCAAC - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 501

5

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

SERVICE BULLETIN

**CONF 003

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

EN6115−5−19 SCREW

ASNA2531−5 NUT

EN6115−5X19 SCREW

NUT

N

ASNA2531−5

88

9

8

9

MS21250−06018 SCREW

WASHER

NSA5057−6 NUT

N NSA5398−6−18A

61

62

63

65

N

62

52

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

SCREW

WASHER

NUT

SCREW

WASHER

NUT

64

62

63

66

62

52

SCREW

WASHER

NUT

MS20002C6

ASNA0094−6

MS20002C6

MS21250−06016

NSA5057−6

NSA5398−6−16A

MS20002C6

ASNA0094−6

MS20002C6

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(88)

(9)

(88)

(9)

(61)

(62)

(63)

(61)

(62)

(63)

(64)

(62)

(63)

(64)

(62)

(63)

ITEM

01

9.387 mm

(0.369 in)

9.427 mm

(0.370 in) 01

01

01

01

01

02

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

7.815 mm

(0.307 in)

7.849 mm

(0.309 in)

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

01

02

01

02

01

02

01

02

01

02

01

02

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

8.211 mm

(0.323 in)

8.245 mm

(0.324 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

STANDARD FASTENER

IN TRANSITION FIT

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

STANDARD FASTENER

IN TRANSITION FIT

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

IN TRANSITION FIT

9.886 mm FIRST OVERSIZE

(0.389 in)

9.925 mm

(0.390 in)

IN TRANSITION FIT

9.886 mm FIRST OVERSIZE

(0.389 in)

9.925 mm

(0.390 in)

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

G_SB_573115_5_CAAC_02_08

Figure A-FCAAC - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 502

5

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

SERVICE BULLETIN

**CONF 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAD_01_03

Figure A-FCAAD - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 503

5

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

SERVICE BULLETIN

**CONF 004

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

EN6115V6−18 SCREW

NUT

EN6115V6X18 SCREW

NUT

N

4

2

5

2

EN6115V6−20 SCREW

NUT

EN6115V6X20 SCREW

NUT

N

6

2

7

2

NSA5399−6−23A SCREW

ASNA2394EW6 WASHER

NSA5372EW616B

N

ASNA0094−6

84

58

51

52

85

82

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

EN6115−5X18 SCREW

NSA5368PD516B WASHER

NSA5050−5 NUT

N EN6115−5Y18

91

67

83

57

67

83

SCREW

WASHER

NUT

NSA5368PD516B

NSA5050−5

8.692mm

(0.342 in)

8.732 mm

(0.343 in)

8.211 mm

(0.323 in)

8.245 mm

(0.328 in)

8.296 mm

(0.326 in)

8.335 mm

(0.324 in)

80

90

WASHER

NUT

SCREW

WASHER

WASHER

NUT

MS21250−07023

ASNA2394EW7

NSA5372EW716B

NSA5057−7

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

(1)

(2)

(1)

(2)

(4)

(2)

(1)

(2)

(6)

(2)

(6)

(2)

(91)

(67)

(83)

(91)

(67)

(83)

(84)

(58)

(51)

(52)

(84)

(58)

(51)

(52)

ITEM

01

01

01

01

01

01

02

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

01

02

01

02

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

9.490 mm

(0.374 in)

9.530 mm

(0.375 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

10.282 mm

(0.404 in)

10.321 mm

(0.443 in)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

G_SB_573115_5_CAAD_02_06

Figure A-FCAAD - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 504

5

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

SERVICE BULLETIN

**CONF 004

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EXISTING HOLE DIAMETER

MIN MAX

N

SCREW

ASNA2394EW6 WASHER

86

58

51

87

82

80

SCREW

ASNA2394EW7 WASHER

MS21250−07025

(86) NSA5399−6−25A

(58)

ITEM

(51)

(86)

(58)

(51)

REMARKS

NEXT NOMINAL

IN TRANSITION FIT

SECOND OVERSIZE

IN TRANSITION FIT

01

02

01

02

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

10.282 mm

(0.404 in)

10.321 mm

(0.406 in)

52 ASNA0094−6 NUT

90 NSA5057−7 NUT

(52)

(52)

NSA5372EW616B WASHER

NSA5372EW716B WASHER

G_SB_573115_5_CAAD_03_01

Figure A-FCAAD - Sheet 03

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 505

5

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

SERVICE BULLETIN

**CONF 005 thru 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAF_01_03

Figure A-FCAAF - Sheet 01

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 506

5

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

SERVICE BULLETIN

**CONF 005 thru 007

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

EN6115V6−19 SCREW

NUT

EN6115V6X19 SCREW

NUT

N

91

2

92

2

EN6115V6−22 SCREW

NUT

EN6115V6X22 SCREW

NUT

N

93

2

94

2

EN6115V6−24 SCREW

ASNA2531−6 NUT

EN6115V6X24 SCREW

NUT

N

ASNA2531−6

75

2

76

2

N

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

ASNA2531−6

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

SCREW

WASHER

NUT

61

62

63

65

62

52

SCREW

WASHER

NUT

MS21250−06018

NSA5057−6

NSA5398−6−18A

MS20002C6

ASNA0094−6

MS20002C6

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

EN6115V5−20 SCREW

ASNA2531−5 NUT

EN6115V5X20 SCREW

NUT

N

ASNA2531−5

73

9

74

9

7.815 mm

(0.308 in)

7.849 mm

(0.309 in)

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

(1)

(2)

(1)

(2)

(91)

(2)

(92)

(2)

(93)

(2)

(93)

(2)

(75)

(2)

(75)

(2)

(73)

(9)

(73)

(9)

(61)

(62)

(63)

(61)

ITEM

(62)

(63)

01

01

01

01

01

01

02

02

02

02

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

NOTE:

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

01

02

01

02

01

02

01

02

01

02

01

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

G_SB_573115_5_CAAF_02_06

Figure A-FCAAF - Sheet 02

Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 507

5

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

SERVICE BULLETIN

**CONF ALL

A Z141 Z142 − 

FR47

FR40

B

B

A

G_SB_573115_5_CBAA_01_01

Figure A-FCBAA - Sheet 01

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 508

5

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

SERVICE BULLETIN

**CONF ALL

FR40

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H14

H22 H21 H13 H12

VIEW LOOKING AFT

NOTE:

DO A ROTOTEST

INSPECTION OF THE HOLE OF THE AREA A AS PER NTM TASK 51−10−01

DO A ROTOTEST

INSPECTION OF THE HOLES OF THE AREA B AS PER NTM TASK 51−10−01

H24 H23

CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER

B 12, 13, 14, 21, 22, 23, 24, 261, 262, 263

A 260

G_SB_573115_5_CBAA_02_05

Figure A-FCBAA - Sheet 02

Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 509

5

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

SERVICE BULLETIN

**CONF 001 thru 006

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H260

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

(1)

(2)

(1)

(2)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

A 260

G_SB_573115_5_CCAA_01_05

Figure A-FCCAA - Sheet 01

Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 510

5

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@A330

SERVICE BULLETIN

**CONF 001 thru 006

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H260

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

EN6115V7−16 SCREW

ASNA2531−7 NUT

EN6115V7X16 SCREW

NUT

N

94

78

79

78

EXISTING HOLE DIAMETER

MIN MAX

10.972 mm

(0.432 in)

11.007 mm

(0.433in)

ASNA2531−7

(94)

(78)

(94)

(78)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

11.080 mm

(0.436 in)

11.120 mm

(0.437 in)

CENTER WING BOX LOWER PANEL REFERENCE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

NOTE:

AREA HOLE NUMBER

A 260

G_SB_573115_5_CDAA_01_05

Figure A-FCDAA - Sheet 01

Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the

Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 511

5

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@A330

SERVICE BULLETIN

**CONF 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H260

VIEW LOOKING AFT

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

EN6115V6−16 SCREW

ASNA2531−6 NUT

EN6115V6X16 SCREW

NUT

N

1

2

3

2

EXISTING HOLE DIAMETER

MIN MAX

9.387 mm

(0.369 in)

9.427 mm

(0.370 in)

ASNA2531−6

(1)

(2)

(1)

(2)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FIRST OVERSIZE

N

HEAD ON THE VISIBLE SIDE

01 DEPENDING ON INSPECTION RESULT

02 INSTALL THE FASTENERS WITH MAT. No 09−013

(WET ASSEMBLY)

9.490 mm

(0.373 in)

9.530 mm

(0.377 in)

CENTER WING BOX LOWER PANEL REFERENCE

NOTE:

AREA HOLE NUMBER

A 260

G_SB_573115_5_CEAA_01_03

Figure A-FCEAA - Sheet 01

Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 512

5

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

SERVICE BULLETIN

**CONF 001 thru 006

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

AND

(REFER TO SUBTASKS 573115−832−002 AND 573115−832−008 FOR AREA B)

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE

(REFER TO SUBTASKS 573115−832−010 AND 573115−832−011)

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

(REFER TO SUBTASK 573115−832−010

OF THE FASTENER HOLES OF THE

AREA B OF THE FRAME 40, LH AND RH SIDES

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 02

AREA B IN TRANSITION FIT, LH AND

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASKS 573115−832−001 AND 573115−832−007 FOR AREA A)

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER

HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

AND/OR 573115−832−011)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−022

AND/OR 573115−833−013)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

G_SB_573115_5_FAAA_01_04

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 513

5

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

SERVICE BULLETIN

**CONF 001 thru 006

QUESTION

ACTION

FINDING

CRACKS

OR

(REFER TO SUBTASKS 573115−832−003 AND 573115−832−009)

SB No. A330−57−3083 OF THE FASTENER HOLE

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

A330−57−3083 NO YES ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 01

SB No.

CRACKS YES NO

(REFER TO SUBTASK 573115−832−004 AND/OR 573115−832−005)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA SHEET 03

OR

(REFER TO SUBTASK 573115−832−003 AND/OR 573115−832−009)

SB No. A330−57−3083 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

APPLY SB No. A330−57−3083

YES NO

SEE FIG. A−FFAAA

SHEET 03

(SB No. A330−57−3083

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 03

(SB No. A330−57−3083

NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENER PRE SB No. A330−57−3083

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

DO A ROTOTEST INSPECTION PRE

SB No. A330−57−3083 OF THE FASTENER HOLE

DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573115−832−004 AND/OR 573115−832−005)

SB No. A330−57−3083 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

INSTALL NEW SAME FASTENER POST SB No. A330−57−3083

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION POST

BEFORE NEXT FLIGHT

NOTE:

01 THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT

01

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−001 AND/OR 573115−833−010)

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−002 AND/OR 573115−833−011)

G_SB_573115_5_FAAA_02_04

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 514

5

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

SERVICE BULLETIN

**CONF 001 thru 006

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

NO YES

SEE FIG. A−FFAAA

SHEET 01 AND SHEET 02

INSTALL NEW FASTENER PRE OR POST

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−004 AND/OR 573115−833−014) OR

SEE FIG. A−FFAAA SHEET 02 

(SB No. A330−57−3083

NOT ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 02

(SB No. A330−57−3083

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 01

CONTACT AIRBUS

A330−57−3083

ACCOMPLISHED

SB No.

SB No. A330−57−3083 OF THE AREA A

(REFER TO SUBTASK 573115−833−005 AND/OR 573115−833−015)

(REFER TO SUBTASK 573115−832−003

SB No. A330−57−3083 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION PRE

(REFER TO SUBTASK 573115−832−004

SB No. A330−57−3083 OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION POST

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−007 AND/OR 573115−833−018) OR

(REFER TO SUBTASK 573115−833−008 AND/OR 573115−833−019)

CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE AREA B

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−023 AND/OR 573115−833−017)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−024

(REFER TO SUBTASK 573115−832−010

OF THE FASTENER HOLES OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

BEFORE NEXT FLIGHT

AND/OR 573115−832−009)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

AND/OR 573115−832−005)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

CONTACT AIRBUS

BEFORE NEXT FLIGHT

 AND/OR 573115−833−021)

AND/OR 573115−832−011)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLE OF THE AREA A PRE OR POST

SB No. A330−57−3083 TO FIRST OVERSIZE IN COMPARISON WITH

CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREA B TO

FIRST OVERSIZE IN COMPARISON WITH THE

G_SB_573115_5_FAAA_03_06

Figure A-FFAAA - Sheet 03

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 515

5

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@A330

SERVICE BULLETIN

**CONF 007

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER

HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE AREA B

(REFER TO SUBTASKS 573115−832−010 AND 573115−832−011)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAB

SHEET 02

SEE FIG. A−FFAAB

SHEET 02 (AREA B)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−022 AND/OR 573115−833−013)

CRACKS NO YES FOUND

SEE FIG. A−FFAAB

SHEET 02

SEE FIG. A−FFAAB

SHEET 02 (AREA A)

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

(REFER TO SUBTASKS 573115−832−006 AND 573115−832−012)

OF THE FASTENER HOLE

OF THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573115−832−006 AND/OR 573115−832−012)

OF THE FASTENER HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

INSTALL NEW SAME FASTENER OF THE AREA A

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−003 AND/OR 573115−833−012)

DO A ROTOTEST INSPECTION

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASK 573115−832−010 AND/OR 573115−832−011)

OF THE FASTENER HOLES OF THE

AREA B OF THE FRAME 40, LH AND RH SIDES

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

REPEAT THE ROTOTEST INSPECTION

(REFER TO SUBTASKS 573115−832−001 AND 573115−832−007 FOR AREA A) AND 

(REFER TO SUBTASKS 573115−832−002 AND 573115−832−008 FOR AREA B)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

G_SB_573115_5_FAAB_01_04

Figure A-FFAAB - Sheet 01

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 516

5

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@A330

SERVICE BULLETIN

**CONF 007

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

SEE FIG. A−FFAAB

SHEET 01

INSTALL NEW FASTENER

HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLE OF THE AREA A

TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT

SEE FIG. A−FFAAB SHEET 01

SEE FIG. A−FFAAB SHEET 01

CONTACT AIRBUS

OF THE AREA A IN TRANSITION FIT,

(REFER TO SUBTASK 573115−832−006

OF THE FASTENERS HOLE OF

THE AREA A OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−009

CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE

HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREA B

TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT

LH AND RH SIDES BEFORE NEXT FLIGHT

AREA B IN TRANSITION FIT, LH AND RH SIDES

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−832−010

OF THE FASTENER HOLES OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

BEFORE NEXT FLIGHT

AND/OR 573115−833−020)

AND/OR 573115−832−012)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

CONTACT AIRBUS

BEFORE NEXT FLIGHT

AND/OR 573115−832−011)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573115−833−024

AND/OR 573115−833−021)

AREA A

HOLE 260

AREA B

HOLES 12, 13, 14, 21, 22,

23, 24, 261, 262 AND 263

LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−006 AND/OR 573115−833−016) (REFER TO SUBTASK 573115−833−023 AND/OR 573115−833−017)

G_SB_573115_5_FAAB_02_05

Figure A-FFAAB - Sheet 02

Flow Chart

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 517

5

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@A330

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 518

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF ALL

(1) Inspection report

(a) The results of the inspection, including no findings, replacement or actions to be done, must

be forwarded to AIRBUS SEES1, on the attached inspection report sheet.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 1

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 004

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3115

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CRACKS AFTER

OVERSIZE

H12 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H13 YES NO YES NO YES NO YES NO

H14 YES NO YES NO YES NO YES NO

H21 YES NO YES NO YES NO YES NO

H22 YES NO YES NO YES NO YES NO

H23 YES NO YES NO YES NO YES NO

H24 YES NO YES NO YES NO YES NO

H260 YES NO YES NO YES NO YES NO

H261 YES NO YES NO YES NO YES NO

H262 YES NO YES NO YES NO YES NO

H263 YES NO YES NO YES NO YES NO

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573115_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 2

5

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 004

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3115

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

INSPECTION

H12

RH SIDE

H13

H14

H21

H22

H23

H24

H260

H261

H262

H263

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

mm

FINAL

DIAMETER

in

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

G_SB_573115_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 3

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 004

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H23 H14 H24

H22 H21 H13 H12

VIEW LOOKING AFT

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573115_5_RAAA_03_00

Figure A-FRAAA - Sheet 03

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 4

5

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 004

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 260

HOLE 13

FR40 FRONT

FITTING

(8 mm)

(0.315 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 12 & 14

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

G_SB_573115_5_RAAA_04_01

Figure A-FRAAA - Sheet 04

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 5

5

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@A330

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 001 thru 004

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 21, 22, 23 & 24

HOLE 262 HOLE 263

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB

GUSSET

(5 mm)

(0.197 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in) CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

CWB

GUSSET

(8 mm TO

8.5 mm)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

HOLE 261

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(6 mm)

(0.236 in)

FWD

FWD

(0.315 in to

0.334 in)

CWB

GUSSET

(11 mm TO

11.5 mm)

(0.433 in to

0.453 in)

SHIM

(6.5 mm)

(0.256 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

G_SB_573115_5_RAAA_05_01

Figure A-FRAAA - Sheet 05

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 6

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3115

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CRACKS AFTER

OVERSIZE

H12 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H13 YES NO YES NO YES NO YES NO

H14 YES NO YES NO YES NO YES NO

H21 YES NO YES NO YES NO YES NO

H22 YES NO YES NO YES NO YES NO

H23 YES NO YES NO YES NO YES NO

H24 YES NO YES NO YES NO YES NO

H260 YES NO YES NO YES NO YES NO

H261 YES NO YES NO YES NO YES NO

H262 YES NO YES NO YES NO YES NO

H263 YES NO YES NO YES NO YES NO

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573115_5_RAAB_01_00

Figure A-FRAAB - Sheet 01

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 7

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A330−57−3115

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

INSPECTION

H12

RH SIDE

H13

H14

H21

H22

H23

H24

H260

H261

H262

H263

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

mm

FINAL

DIAMETER

in

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

G_SB_573115_5_RAAB_02_00

Figure A-FRAAB - Sheet 02

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 8

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

FR47

FR40

FR40

B

B A

B LH SIDE SHOWN

RH SIDE SYMMETRICAL

A Z141 Z142 − 

STGR38

STGR39

STGR40

STGR37

H260 H263

H262

H261

H23 H14

H21 H13 H12

VIEW LOOKING AFT

H24

H22

CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573115_5_RAAB_03_01

Figure A-FRAAB - Sheet 03

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 9

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 260

HOLE 13

FR40 FRONT

FITTING

(8 mm)

(0.315 in) FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 12 & 14

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

G_SB_573115_5_RAAB_04_01

Figure A-FRAAB - Sheet 04

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 10

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

HOLE 21, 23 & 24

NOTE:

THESE THICKNESSES ARE THEORETICAL

HOLE 22

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(12 mm)

(0.472 in)

FWD

CWB LOWER

ANGLE

(6 mm)

(0.236 in)

CWB RIB

Y1959

(10 mm)

(0.394 in)

FR40

SPAR

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40 POST

Y1959

(6 mm)

(0.236 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FWD

G_SB_573115_5_RAAB_05_01

Figure A-FRAAB - Sheet 05

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 11

5

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

SERVICE BULLETIN

Appendix 01 : Inspection Report

**CONF 005 thru 007

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 262

HOLE 263

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in) CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

CWB

GUSSET

(8 mm TO

9 mm)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

CWB LOWER

ANGLE

(6.5 mm)

(0.256 in)

HOLE 261

FWD

(0.315 in to

0.354 in)

CWB

GUSSET

(11 mm TO

12 mm)

(0.433 in to

0.472 in)

CWB

GUSSET

(12.5 mm TO

13.5 mm)

(0.492 in to

0.531 in)

G_SB_573115_5_RAAB_06_01

Figure A-FRAAB - Sheet 06

Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 12

5

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER

PANEL

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 1

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@A330

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115

REVISION No.: 00 - Apr 04/13 Page: 1

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