@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL

CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO

SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND

COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A

AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH

MODIFICATION No.: 53222D44560

This page transmits Revision No.03 of Service Bulletin No.A330-53-3160

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 03 issued to update the Flight Cycles (FC) and Flight Hours (FH).

CHANGES

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 1

6

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

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

APPENDICES Minor editorial or document structure change N

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

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

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

CONF 002 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Threshold are revised. N

Accomplishment Timescale Threshold are revised. N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 2

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@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

MATERIAL INFORMATION

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

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 533160D01R04 Minor editorial or document structure change N

Kit 533160D02R05 Minor editorial or document structure change N

Kit 533160D03R01 Minor editorial or document structure change N

Kit 533160D04R01 Minor editorial or document structure change N

Kit 533160D05R01 Minor editorial or document structure change N

Kit 533160D06R01 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

Consumable CMLD01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

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

Tools Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 533160- 831-848-001-

MODIFICATION

Minor editorial or document structure change N

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

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

Subtask 533160-910-203-001 Minor editorial or document structure change N

Subtask 533160-839-201-001 Minor editorial or document structure change N

Subtask 533160-910-203-001 Minor editorial or document structure change N

Subtask 533160-839-201-001 Minor editorial or document structure change N

Subtask 533160-941-201-001 Minor editorial or document structure change N

Subtask 533160-941-201-001 Minor editorial or document structure change N

Subtask 533160-831-204-001 Minor editorial or document structure change N

Subtask 533160-831-205-001 Minor editorial or document structure change N

Subtask 533160-831-206-001 Minor editorial or document structure change N

Subtask 533160-831-207-001 Minor editorial or document structure change N

Subtask 533160-831-208-001 Minor editorial or document structure change N

Subtask 533160-831-209-001 Minor editorial or document structure change N

Subtask 533160-831-210-001 Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 533160-831-211-001 Minor editorial or document structure change N

Subtask 533160-831-212-001 Minor editorial or document structure change N

Subtask 533160-400-201-001 Minor editorial or document structure change N

Subtask 533160-400-202-001 Minor editorial or document structure change N

Subtask 533160-831-204-002 Minor editorial or document structure change N

Subtask 533160-831-205-002 Minor editorial or document structure change N

Subtask 533160-831-206-002 Minor editorial or document structure change N

Subtask 533160-831-207-002 Minor editorial or document structure change N

Subtask 533160-831-208-002 Minor editorial or document structure change N

Subtask 533160-831-209-002 Minor editorial or document structure change N

Subtask 533160-831-210-002 Minor editorial or document structure change N

Subtask 533160-831-211-002 Minor editorial or document structure change N

Subtask 533160-831-212-002 Minor editorial or document structure change N

Subtask 533160-400-201-002 Minor editorial or document structure change N

Subtask 533160-400-202-002 Minor editorial or document structure change N

Subtask 533160-831-223-001 Minor editorial or document structure change N

Subtask 533160-831-223-001 Minor editorial or document structure change N

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Fig. A-GBBAA Sheet 06 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 07 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 08 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 09 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 10 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 11 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 12 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 13 Minor editorial or document structure change N

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 4

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

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-GBBAA Sheet 14 Minor editorial or document structure change N

Fig. A-GBBAA Sheet 15 Minor editorial or document structure change N

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

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

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

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

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

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

Fig. A-GBBAB Sheet 06 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 07 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 08 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 09 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 10 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 11 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 12 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 13 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 14 Minor editorial or document structure change N

Fig. A-GBBAB Sheet 15 Minor editorial or document structure change N

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

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

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

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

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

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

Fig. A-GBCAA Sheet 06 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 07 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 08 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 09 Minor editorial or document structure change N

Fig. A-GBCAA Sheet 10 Minor editorial or document structure change N

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

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

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

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

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

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

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

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

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

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 5

6

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

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

This Service Bulletin was updated with rev. 01 to include all new information from the validation on the

A330 MSN 229.

Revision No. 02

This Service Bulletin has been updated to correct the quantity of the fastener, item 19 and item 20 for

configuration 02.

REVISION SEQUENCE

ORIGINAL: Jul 09/07

REVISION No.: 02 - Mar 29/10

REVISION No. : 03 - Jan 06/12

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 6

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

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL

CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO

SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND

COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A

AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 53222D44560

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

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

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

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During long life structure tests on the A340-600, damage was found in the upper shell structure

between FR84 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles

(FC). Under consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no

action is required.

Nevertheless, due to the higher DSG of 33000 FC / 40000 FC and different design (e.g. skin thickness)

for A330-200 aircraft, this damage is considered relevant for these models.

Structure improvements have to be embodied.

This Service Bulletin has been validated on A330 aircraft MSN 0229.

A booklet including photographs taken during the validation of this Service Bulletin is available on

AIRBUS World, Maintenance and Engineering, Service Bulletin Information.

This Service Bulletin has been issued to inform the operator to improve the upper shell structure

between FR84 and FR87 as follows :

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 1

6

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

SERVICE BULLETIN

SUMMARY

- removal/installation of the vertical stabilizer for access reason.

- do a rototest inspection of fastener holes and a eddy current high frequency inspection between

the fastener rows in the upper shell area of FR80, FR84 and FR86.

- install new reinforcement T-doublers on the upper shell fuselage skin in the area of FR84 and

FR86 between STGR5A LH and STGR5A RH,

- do a cold working with interference fit at FR80, FR84, FR85 and FR86,

- replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4 LH/RH,

- install a system angle between FR85 and FR86 and between STGR2 and STGR3 LH/RH.

- replace a system angle between FR83 and FR84, at STGR3 LH/RH.

The accomplishment of this Service Bulletin will ensure the structural integrity of the upper shell

structure between FR84 to FR87 up the DSG of 40000 FC for A330-200 aircraft.

This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft delivery

configuration and modified by the reported incorporation of Airbus SBs). Prior to Service Bulletin

embodiment, the operator is reminded to pay specific attention to structural damage which may exist

and to repairs which were performed on the aircraft because they may be affected by the Service

Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in

accordance with the SRM and outside of the SRM) are still applicable and effective to the new

Service Bulletin configuration. There may be additional or modified maintenance requirements, such as

temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration.

Airbus disclaims any liability for the effect which the Service Bulletin may have on repairs performed on

the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no

more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by Airbus, the

operator should contact Airbus Customer Services Repair Engineering Support (SER1). Repair review

will be done by Airbus at conditions of the Customer Services Catalogue.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533160D01R04 1 14,240.00 Attachment Parts, Reinforcement Part

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 2

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

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533160D02R05 1 9,270.00 Attachment Parts

Kit 533160D03R01 1 4,030.00 Attachment Parts

TOTAL 27,540.00

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533160D04R01 1 14,990.00 Attachment Parts, Reinforcement Part

Kit 533160D05R01 1 9,310.00 Attachment Parts

Kit 533160D06R01 1 4,060.00 Attachment Parts

TOTAL 28,360.00

EFFECTIVITY

**CONF ALL

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

ACI AEA AFR ALK AZA BER BMA BTV CRL CSN CYP DAH DAL

DGA EDW EIN ETD EVA FWI GFA GRL HVN I2L IAC ISS IYE

JST KAL KKK MAS MON MSR QAF QTR STZ SWR TAM TAP TCX

THY TSC UAE VKG VOZ XLF

CONCURRENT REQUIREMENTS

Due to the access requirements, AIRBUS recommends the simultaneous accomplishment of:

Service Bulletin No. A330-53-3152 Mod. No. 53222D44902

A330-53-3157 54622D46095

NOTE: Service Bulletin A330-53-3152 is applicable for MSN 0205 thru 0667.

NOTE: Service Bulletin A330-53-3157 is applicable for MSN 0181 and 0195.

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT Yes

OTHERS OIT SE999.0124/06

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 3

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

SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 533160-831-848-001: MODIFICATION

TOTAL MANHOURS 190.50

ELAPSED TIME (HOURS) 97.50

**CONF 002

Task 533160-831-848-001: MODIFICATION

TOTAL MANHOURS 192.50

ELAPSED TIME (HOURS) 99.50

APPENDICES

**CONF ALL

None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 4

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

SERVICE BULLETIN

SUMMARY

**CONF ALL

Z310

A

AD

REPAIR AREA

Z270

A

G_SB_533160_6_SAAA_01_00

STGR8

STGR8

FR91

FR87

FR79

Figure A-GSAAA - Sheet 01

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 5

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

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 6

6

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: 53

TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL

CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO

SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND

COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A

AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH

MODIFICATION No.: 53222D44560

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin is applicable for A330-200 aircraft on which MOD

44205D40465 has already been embodied, and MOD 52974D44611 and

MOD 53223D44586 have NOT been embodied in production.

(1) Models

330-202 330-203 330-223 330-243

(2) Effectivity by MSN

0181 0195 0205 0211 0222-0223 0226 0229-0230 0232 0238 0240 0247-0251

0253-0255 0258-0259 0261-0262 0265-0266 0269 0271-0272 0275-0276 0281 0283

0285-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0314

0316-0317 0320 0322 0324 0326 0328 0330 0334 0339-0340 0343 0345 0348 0353

0358 0361-0362 0364-0366 0369 0372 0382 0384 0392 0396-0398 0401 0403-0404

0409 0422 0427 0432 0437 0441 0443-0444 0448 0451-0452 0454-0456 0458

0461-0463 0465-0466 0469 0472-0473 0476-0477 0480-0481 0486-0487 0489 0491

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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@A330

SERVICE BULLETIN

0493-0494 0498 0500-0511 0513 0516 0518-0519 0521-0522 0525-0527 0529-0530

0532 0535-0536 0551 0555 0567 0571 0573 0584 0587 0597 0600 0605 0609-0610

0612 0614 0616 0618 0620-0621 0625 0627 0631-0635 0638 0644 0647 0649-0650

0652-0653 0655-0658 0661 0664-0667

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

ACI 0507 0510

AEA 0461 0597

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

0567 0584 0657

ALK 0303 0306 0311 0313 0404

AZA 0272 0339

BER 0403 0432 0444 0454 0469 0476 0493

BMA 0398 0401

BTV 0205 0330

CRL 0285 0320

CSN 0649 0652 0656 0664

CYP 0505 0526

DAH 0644 0647 0650 0653 0667

DAL 0609 0614 0618 0620 0621 0631 0633

DGA 0240

EDW 0291

EIN 0269 0397

ETD 0658

EVA 0530 0535 0555 0573 0587 0634 0655 0661

FWI 0253

GFA 0276 0281 0286 0287 0334 0340 0527 0529 0532

GRL 0230

HVN 0255 0262 0275 0294 0299 0366

I2L 0211 0551

IAC 0353 0362

ISS 0665

IYE 0625 0627 0632

JST 0506 0508 0513 0522

KAL 0222 0226 0258

KKK 0343 0358 0364

MAS 0290 0296 0300

MON 0261 0265

MSR 0600 0610 0666

QAF 0487 0605

QTR 0441 0473 0489 0511 0521 0571 0612 0616 0638

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 2

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@A330

SERVICE BULLETIN

OPERATOR MSN

STZ 0324

SWR 0229 0249 0288 0322

TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486

TAP 0181 0195 0223 0305 0308 0312 0317

TCX 0254 0266 0301 0427 0456

THY 0463 0504

TSC 0250 0271 0369 0480

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

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

0518 0525 0536

VKG 0309

VOZ 0365 0372

XLF 0501 0635

(4) Configuration by MSN

MSN CONFIGURATION

0181 0195 0205 0211 0222 0223 0226 0229 0230 0232 0238

0240 0247 0248 0249 0250 0251 0253 0254 0255 0258 0259

0261 0262 0265 0266 0269 0271 0272 0275 0276 0281 0283

0285 0286 0287 0288 0290 0291 0293 0294 0295 0296 0299

0300 0301 0303 0305 0306 0308 0309 0311 0312 0313 0314

0316 0317 0320 0322 0324 0326 0328 0330 0334 0339 0340

0343 0345 0348 0353 0358 0361 0362 0364 0365 0366 0369

0372 0382 0384 0392 0396 0397 0398 0401 0403 0404 0409

0422 0427 0432 0437 0441 0443 0444 0448 0451 0452 0454

0455 0456 0458 0461 0462 0463 0465 0466 0469 0472 0473

0476 0477 0480 0481 0486 0487 0489 0491 0493 0494 0498

0500 0501 0502 0503 0504 0505 0506 0507 0508 0509 0510

0511 0513 0516 0518 0519 0521 0522 0525 0526 0527 0529

0530 0532 0535 0536 0551 0567 0584 0597 0627 0635 0657

001

0555 0571 0573 0587 0600 0605 0609 0610 0612 0614 0616

0618 0620 0621 0625 0631 0632 0633 0634 0638 0644 0647

0649 0650 0652 0653 0655 0656 0658 0661 0664 0665 0666

0667

002

(5) Configuration definition

**CONF 001

Config. 001 is applicable to aircraft that have weight variant (WV) 20 thru WV 29.

**CONF 002

Config. 002 is applicable to aircraft which have weight variant (WV) 50 thru VW 55.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 533160D01R04 1 (1)

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MATERIAL QTY PER A/C SEE NOTES

Kit 533160D02R05 1 (2)

Kit 533160D03R01 1 (3)

Consumable CMLD01 1

NOTE (1): Kit 533160D01 should be used for the standard fastener installation.

NOTE (2): Kit 533160D02 should be used for the installation of the first oversize

fasteners, if the fasteners of kit 533160D01 do not fit.

NOTE (3): Kit 533160D03 should be used for the installation of smaller fastener, if

the fastener edge clearance of the standard fastener installation of kit

533160D01 does not match the minimum distance.

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 533160D04R01 1 (1)

Kit 533160D05R01 1 (2)

Kit 533160D06R01 1 (3)

Consumable CMLD01 1

NOTE (1): Kit 533160D04 should be used for the standard fastener installation.

NOTE (2): Kit 533160D05 should be used for the installation of the first oversize

fasteners, if the fasteners of kit 533160D04 do not fit.

NOTE (3): Kit 533160D06 should be used for the installation of smaller fastener, if

the fastener edge clearance of the standard fastener installation of kit

533160D04 does not match the minimum distance.

**CONF ALL

B. CONCURRENT REQUIREMENTS

Due to the access requirements, AIRBUS recommends the simultaneous accomplishment of:

Service Bulletin No. A330-53-3152 Mod. No. 53222D44902

A330-53-3157 54622D46095

NOTE: Service Bulletin A330-53-3152 is applicable for MSN 0205 thru 0667.

NOTE: Service Bulletin A330-53-3157 is applicable for MSN 0181 and 0195.

C. REASON

(1) History

During long life structure tests on the A340-600, damage was found in the upper shell

structure between FR84 and FR86. This damage occurred between 58341 and 72891

simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of

16600 FC for A340-600 aircraft, no action is required.

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Nevertheless, due to the higher DSG of 33000 FC / 40000 FC and different design

(e.g. skin thickness) for A330-200 aircraft, this damage is considered relevant for these

models.

Structure improvements have to be embodied.

This Service Bulletin has been validated on A330 aircraft MSN 0229.

A booklet including photographs taken during the validation of this Service Bulletin is

available on AIRBUS World, Maintenance and Engineering, Service Bulletin Information.

(2) Objective/Action

This Service Bulletin has been issued to inform the operator to improve the upper shell

structure between FR84 and FR87 as follows :

- removal/installation of the vertical stabilizer for access reason.

- do a rototest inspection of fastener holes and a eddy current high frequency

inspection between the fastener rows in the upper shell area of FR80, FR84 and

FR86.

- install new reinforcement T-doublers on the upper shell fuselage skin in the area of

FR84 and FR86 between STGR5A LH and STGR5A RH,

- do a cold working with interference fit at FR80, FR84, FR85 and FR86,

- replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4

LH/RH,

- install a system angle between FR85 and FR86 and between STGR2 and STGR3

LH/RH.

- replace a system angle between FR83 and FR84, at STGR3 LH/RH.

(3) Advantages

The accomplishment of this Service Bulletin will ensure the structural integrity of the

upper shell structure between FR84 to FR87 up the DSG of 40000 FC for A330-200

aircraft.

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SERVICE BULLETIN

(4) Operational/Maintenance Consequences

This Service Bulletin is based on the aircraft configuration as known by Airbus (first

aircraft delivery configuration and modified by the reported incorporation of Airbus SBs).

Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention

to structural damage which may exist and to repairs which were performed on the

aircraft because they may be affected by the Service Bulletin. Operators must verify that

all allowable damage limits and repairs performed (both in accordance with the SRM

and outside of the SRM) are still applicable and effective to the new Service Bulletin

configuration. There may be additional or modified maintenance requirements, such as

temporary limits or additional inspections, that apply with respect to the Service Bulletin

configuration. Airbus disclaims any liability for the effect which the Service Bulletin may

have on repairs performed on the aircraft before embodiment of the Service Bulletin. If

the post Service Bulletin repair status is no more covered by the SRM and for repairs

outside of the SRM covered by a RAS issued by Airbus, the operator should contact

Airbus Customer Services Repair Engineering Support (SER1). Repair review will be

done by Airbus at conditions of the Customer Services Catalogue.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 533160-831-848-001: MODIFICATION

(1) Remove the fasteners in the upper fuselage shell between FR80 and FR87.

(2) Do the Eddy Current Rotating Probe Testing FR80, FR84 and FR86 to find cracks

around the holes of the previous removed fasteners.

(3) Do the eddy current high frequency inspection of FR84 and FR86 to find cracks

between the fastener rows.

(4) Do a check of the fastener position to make sure that the edge clearance of all

existing fastener holes is correct.

(5) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between

STGR2A LH/RH and STGR5A LH/RH.

(6) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR86.

(7) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR84.

(8) Install fasteners with cold working in the upper fuselage skin at FR85

(9) Apply surface protection to the modification area.

(10) Installation of undersize fasteners of kit 533160D03R01

(11) Oversize fasteners of kit 533160D02R01

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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**CONF 002

Task 533160-831-848-001: MODIFICATION

(1) Remove the fasteners in the upper fuselage shell between FR80 and FR87.

(2) Do the Eddy Current Rotating Probe Testing of FR80, FR84 and FR86 to find cracks

around the holes of the previous removed fasteners.

(3) Do the eddy current high frequency inspection of FR84 and FR86 to find cracks

between the fastener rows.

(4) Do a check of the fastener position to make sure that the edge clearance of all

existing fastener holes is correct.

(5) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between

STGR2A LH/RH and STGR5A LH/RH.

(6) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR86.

(7) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR84.

(8) Install fasteners with cold working in the upper fuselage skin at FR85

(9) Apply surface protection to the modification area.

(10) Installation of undersize fasteners of kit 533160D06R01

(11) Oversize fasteners of kit 533160D05R01

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

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(2) Accomplishment Timescale

**CONF 001

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach is an

equivalent damage approach corresponding to trade of between FC/FH to better suit

fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness

and could be used any type of utilization, for 1st inspection and repetitive ones,

operators may select either SR (Threshold or Interval) or LR (Threshold or Interval)

(depending of the A/C utilization evolution). If a non optimal set of threshold/interval

is selected, airworthiness will be ensured, but will penalize the operator because the

inspection will be performed sooner than necessary as a consequence, the selection of

SR or LR threshold and subsequent intervals can be change whenever. Threshold

and Interval are whichever occurs first between FC and FH for selected set of

threshold/interval between SR and LR. This means that the set FC/FH must be

considered jointly (ie FCSR cannot be used with FHLR and vice versa).

NOTE: The Service Bulletin must be performed at whichever limit (FC or FH)

occurs first.

Type Threshold SR Threshold LR

Threshold 12900 FC or 45300 FH 9600 FC or 62600 FH

NOTE: A grace period of 20 months from Service Bulletin revision 03 issuance

is allowed but without exceeding 13500 FC.

**CONF 002

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach is an

equivalent damage approach corresponding to trade of between FC/FH to better suit

fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness

and could be used any type of utilization, for 1st inspection and repetitive ones,

operators may select either SR (Threshold or Interval) or LR (Threshold or Interval)

(depending of the A/C utilization evolution). If a non optimal set of threshold/interval

is selected, airworthiness will be ensured, but will penalize the operator because the

inspection will be performed sooner than necessary as a consequence, the selection of

SR or LR threshold and subsequent intervals can be change whenever. Threshold

and Interval are whichever occurs first between FC and FH for selected set of

threshold/interval between SR and LR. This means that the set FC/FH must be

considered jointly (ie FCSR cannot be used with FHLR and vice versa).

NOTE: The Service Bulletin must be performed at whichever limit (FC or FH)

occurs first.

Type Threshold SR Threshold LR

Threshold 9800 FC or 34500 FH 7300 FC or 47600 FH

NOTE: A grace period of 20 months from Service Bulletin revision 03 issuance

is allowed but without exceeding 10700 FC or 59300 FH, whichever

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SERVICE BULLETIN

occurs first.

**CONF ALL

F. APPROVAL

The technical content of this Service Bulletin is approved under the authority of Design

Organisation Approval No.EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 533160-831-848-001: MODIFICATION

Get Access 48.00

On Aircraft

Remove the fasteners in the upper fuselage shell

between FR80 and FR87.

2.25

Do the Eddy Current Rotating Probe Testing FR80,

FR84 and FR86 to find cracks around the holes of the

previous removed fasteners.

3.00

Do the eddy current high frequency inspection of FR84

and FR86 to find cracks between the fastener rows.

2.50

Do a check of the fastener position to make sure that

the edge clearance of all existing fastener holes is

correct.

1.50

Install 6 fasteners with cold working in the upper

fuselage shell at FR80 between STGR2A LH/RH and

STGR5A LH/RH.

2.00

Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR86.

35.00

Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR84.

33.50

Install fasteners with cold working in the upper

fuselage skin at FR85

2.25

Apply surface protection to the modification area. 1.50

Installation of undersize fasteners of kit 533160D03R01 0.00

Oversize fasteners of kit 533160D02R01 0.00

Tests 9.00

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SERVICE BULLETIN

Task 533160-831-848-001: MODIFICATION

Close-Up 50.00

TOTAL MANHOURS 190.50

ELAPSED TIME (HOURS) 97.50

**CONF 002

Task 533160-831-848-001: MODIFICATION

Get Access 48.00

On Aircraft

Remove the fasteners in the upper fuselage shell

between FR80 and FR87.

2.25

Do the Eddy Current Rotating Probe Testing of FR80,

FR84 and FR86 to find cracks around the holes of the

previous removed fasteners.

3.00

Do the eddy current high frequency inspection of FR84

and FR86 to find cracks between the fastener rows.

2.50

Do a check of the fastener position to make sure that

the edge clearance of all existing fastener holes is

correct.

1.50

Install 6 fasteners with cold working in the upper

fuselage shell at FR80 between STGR2A LH/RH and

STGR5A LH/RH.

1.50

Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR86.

38.00

Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR84.

33.00

Install fasteners with cold working in the upper

fuselage skin at FR85

2.25

Apply surface protection to the modification area. 1.50

Installation of undersize fasteners of kit 533160D06R01 0.00

Oversize fasteners of kit 533160D05R01 0.00

Tests 9.00

Close-Up 50.00

TOTAL MANHOURS 192.50

ELAPSED TIME (HOURS) 99.50

**CONF ALL

H. WEIGHT AND BALANCE

**CONF 001

Manufacturers Empty Weight +5.81 KG (+12.8087 LB)

Effect on Balance +330.54 KGM (+2390.795 LB.FT )

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**CONF 002

Manufacturers Empty Weight +6.56 KG (+14.46 LB)

Effect on Balance +373.58 KGM (+2702.10 LB.FT )

**CONF ALL

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29

12-34-24 20-28-00 25-33-48

25-33-52 25-33-53 25-33-54

27-51-18 29-00-00 29-14-00

36-12-14 36-12-41 36-22-17

51-31-11 52-10-00 55-31-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-08

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11

51-43-00 51-44-11 51-46-11

51-46-12 51-47-00 51-48-00

**CONF 002

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29

12-34-24 20-28-00 25-33-48

25-33-52 25-33-53 25-33-54

27-51-18 29-00-00 29-14-00

36-12-14 36-12-41 36-22-17

51-31-11 52-10-00 55-31-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-51-20 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-08

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00 51-24-00 51-42-11

51-43-00 51-44-11 51-46-11

51-46-12 51-47-00 51-48-00

**CONF ALL

K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 53-51-11

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L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 533160D01R04

Kit 533160D02R05

Kit 533160D03R01

Kit 533160D04R01

Kit 533160D05R01

Kit 533160D06R01

Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is :

AIRBUS Material, Logistic and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http//spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

For ordering by E-mail: airbus.kit@airbus.com

Operators interested in obtaining the FTI tool

kits should contact:

Fatigue Technology Inc.

401 ANDOVER PARK EAST

SEATTLE, WA 98188-7605

USA

E-Mail: www.fatiguetech.com

Phone: +(1) 206 2462010

Fax: +(1) 206 2449886

(2) Price and Availability

Kit 533160D01R04

Cost 14,240.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 533160D02R05

Cost 9,270.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 533160D03R01

Cost 4,030.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 533160D04R01

Cost 14,990.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 533160D05R01

Cost 9,310.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

Kit 533160D06R01

Cost 4,060.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

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

policy.

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C. LIST OF COMPONENTS

Kit 533160D01R04

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

NOTES

1 F5357716920000 1 DOUBLER

2 F5357716920100 1 DOUBLER

3 F5357716920200 1 DOUBLER

4 F5357716920300 1 DOUBLER

5 F5357798920000 1 SHIM

6 F5357798920100 1 SHIM

7 F5357798920200 1 SHIM

8 F5357798920300 1 SHIM

9 A5398525620600 1 ANGLE

10 F5357716921800 1 DOUBLER

11 F5357716921900 1 DOUBLER

12 F5357716922100 1 DOUBLER

13 F5357716922000 1 DOUBLER

14 F5357798921200 1 SHIM

15 F5357798921400 1 SHIM

16 F5357798921700 1 SHIM

17 F5357798921600 1 SHIM

18 DAN5-5-4 2 PIN

19 DAN5-6-3 14 PIN

20 DAN5-6-4 2 PIN

21 DAN5-6-5 10 PIN

22 DAN5-6-6 20 PIN

23 DAN5-6-7 8 PIN

24 DAN5-6-8 16 PIN

25 DAN5-6-10 8 PIN

26 DAN7-8-9 4 PIN

27 DAN7-8-10 4 PIN

28 DAN7-8-11 12 PIN

29 DAN7-10-11 8 PIN

30 DAN7-10-12 6 PIN

31 DAN7-10-17 4 PIN

32 DAN5-6-7X 4 PIN

33 DAN5-6-10X 4 PIN

34 DAN7-6-11Y 2 PIN

35 DAN7-8-13Y 6 PIN

36 DAN7-8-15Y 6 PIN

37 DAN7-8-16Y 6 PIN

38 EN6115K4Y7 20 BOLT

39 EN6115K4Y8 6 BOLT

40 EN6115K4Y10 8 BOLT

41 EN6115K4Y11 8 BOLT

42 EN6115K4Y12 14 BOLT

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

NOTES

43 EN6115K4Y15 2 BOLT

44 EN6115K4Y16 2 BOLT

45 NSA5075-5 2 COLLAR

46 NSA5075-6 78 COLLAR

47 DAN12-6Y 2 COLLAR

48 DAN12-8 20 COLLAR

49 DAN12-10 18 COLLAR

50 ASNA2528-3 60 NUT

51 ASNA2528-4 54 NUT

52 ASNA2528-5 40 NUT

53 NSA5330-6 6 COLLAR

54 DAN12-8Y 72 COLLAR

55 DAN12-8X 2 COLLAR

56 DAN11-6X 8 COLLAR

57 DAN5-6-7Y 2 PIN

58 DAN5-6-8Y 4 PIN

59 DAN7-8-12X 2 PIN

60 DAN7-8-10Y 20 PIN

61 DAN7-8-11Y 20 PIN

62 DAN7-8-12Y 14 PIN

63 EN6115K3-3 10 BOLT

64 EN6115K3-4 10 BOLT

65 EN6115K3-5 22 BOLT

66 EN6115K3-7 10 BOLT

67 EN6115K3-8 8 BOLT

68 EN6115K5-10 8 BOLT

69 EN6115K5-11 8 BOLT

70 EN6115K5-12 8 BOLT

71 EN6115K5-17 8 BOLT

72 EN6115K5-19 8 BOLT

73 LN9198-4012CF 1 RIVET

74 LN9198-4014CF 1 RIVET

75 EN6080D5-06 1 RIVET

76 LN9198-4812CF 2 RIVET

77 LN9198-4814CF 8 RIVET

124 EN6115K3A7 2 BOLT

125 EN6115K3A8 2 BOLT

126 ASNA2528-3A 4 NUT

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

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

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

to part number relationship.

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Kit 533160D02R05

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

NOTES

20 DAN5-6-4 2 PIN

28 DAN7-8-11 PIN

29 DAN7-10-11 5 PIN

30 DAN7-10-12 5 PIN

32 DAN5-6-7X 5 PIN

33 DAN5-6-10X 5 PIN

46 NSA5075-6 2 COLLAR

48 DAN12-8 2 COLLAR

49 DAN12-10 5 COLLAR

50 ASNA2528-3 5 NUT

51 ASNA2528-4 4 NUT

52 ASNA2528-5 6 NUT

53 NSA5330-6 5 COLLAR

54 DAN12-8Y 2 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

57 DAN5-6-7Y 4 PIN

62 DAN7-8-12Y 2 PIN

68 EN6115K5-10 5 BOLT

69 EN6115K5-11 5 BOLT

70 EN6115K5-12 5 BOLT

78 DAN5-6-3X 5 PIN

79 DAN5-6-4X 2 PIN

80 DAN5-6-5X 5 PIN

81 DAN5-6-6X 5 PIN

82 DAN5-6-8X 5 PIN

83 DAN7-8-9X 4 PIN

84 DAN7-8-10X 4 PIN

85 DAN7-8-11X 5 PIN

86 DAN7-10-11X 5 PIN

87 DAN7-10-12X 5 PIN

88 DAN7-10-17X 4 PIN

89 DAN5-6-10Y 4 PIN

90 DAN7-10-13 5 PIN

91 DAN7-10-15 5 PIN

92 DAN7-10-16 5 PIN

93 EN6115K5-7 5 BOLT

94 EN6115K5-8 6 BOLT

95 EN6115K5-15 2 BOLT

96 EN6115K5-16 2 BOLT

97 DAN12-10X 5 COLLAR

98 NSA5075-8 5 COLLAR

99 DAN5-8-7 2 PIN

100 DAN5-8-8 4 PIN

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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

NOTES

101 DAN7-10-10 5 PIN

102 EN6115K3X3 5 BOLT

103 EN6115K3X4 5 BOLT

104 EN6115K3X5 5 BOLT

105 EN6115K4-7 2 BOLT

106 EN6115K3X7 5 BOLT

107 EN6115K3X8 5 BOLT

108 EN6115K4-8 2 BOLT

109 EN6115K5X10 5 BOLT

110 EN6115K5X11 5 BOLT

111 EN6115K5X12 5 BOLT

112 EN6115K5X17 5 BOLT

113 EN6115K5X19 5 BOLT

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

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

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

to part number relationship.

Kit 533160D03R01

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

NOTES

32 DAN5-6-7X 2 PIN

34 DAN7-6-11Y 5 PIN

40 EN6115K4Y10 5 BOLT

41 EN6115K4Y11 5 BOLT

42 EN6115K4Y12 5 BOLT

47 DAN12-6Y 5 COLLAR

51 ASNA2528-4 5 NUT

54 DAN12-8Y 5 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

59 DAN7-8-12X 5 PIN

61 DAN7-8-11Y 5 PIN

62 DAN7-8-12Y 5 PIN

82 DAN5-6-8X 4 PIN

84 DAN7-8-10X 5 PIN

85 DAN7-8-11X 5 PIN

114 DAN7-6-9Y 4 PIN

115 DAN7-6-10Y 2 PIN

116 DAN7-8-17Y 4 PIN

117 DAN7-6-11X 2 PIN

118 DAN7-8-13X 5 PIN

119 DAN7-8-15X 5 PIN

120 DAN7-8-16X 5 PIN

121 DAN12-6X 2 COLLAR

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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

NOTES

122 EN6115K4Y17 5 BOLT

123 EN6115K4Y19 5 BOLT

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

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

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

to part number relationship.

Kit 533160D04R01

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

NOTES

1 F5357716920000 1 DOUBLER

2 F5357716920100 1 DOUBLER

3 F5357716920400 1 DOUBLER

4 F5357716920500 1 DOUBLER

5 F5357798920400 1 SHIM

6 F5357798920500 1 SHIM

7 F5357798920600 1 SHIM

8 F5357798920700 1 SHIM

9 A5398525620600 1 ANGLE

10 F5357716921800 1 DOUBLER

11 F5357716921900 1 DOUBLER

12 F5357716922100 1 DOUBLER

13 F5357716922000 1 DOUBLER

14 F5357798921200 1 SHIM

15 F5357798921400 1 SHIM

16 F5357798921700 1 SHIM

17 F5357798921600 1 SHIM

18 DAN5-5-4 2 PIN

19 DAN5-6-3 12 PIN

20 DAN5-6-4 6 PIN

21 DAN5-6-5 12 PIN

22 DAN5-6-6 22 PIN

23 DAN5-6-7 8 PIN

24 DAN5-6-8 16 PIN

25 DAN5-6-10 8 PIN

26 DAN7-8-9 8 PIN

27 DAN7-8-10 4 PIN

28 DAN7-8-11 14 PIN

29 DAN7-10-11 8 PIN

30 DAN7-10-12 6 PIN

31 DAN7-10-17 4 PIN

32 DAN5-6-7X 4 PIN

33 DAN5-6-10X 4 PIN

34 DAN7-6-11Y 2 PIN

35 DAN7-8-13Y 6 PIN

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

NOTES

36 DAN7-8-15Y 6 PIN

37 DAN7-8-16Y 6 PIN

38 EN6115K4Y7 20 BOLT

39 EN6115K4Y8 6 BOLT

40 EN6115K4Y10 8 BOLT

41 EN6115K4Y11 8 BOLT

42 EN6115K4Y12 14 BOLT

43 EN6115K4Y15 2 BOLT

44 EN6115K4Y16 2 BOLT

45 NSA5075-5 2 COLLAR

46 NSA5075-6 84 COLLAR

47 DAN12-6Y 2 COLLAR

48 DAN12-8 24 COLLAR

49 DAN12-10 18 COLLAR

50 ASNA2528-3 66 NUT

51 ASNA2528-4 60 NUT

52 ASNA2528-5 40 NUT

53 NSA5330-6 6 COLLAR

54 DAN12-8Y 72 COLLAR

55 DAN12-8X 2 COLLAR

56 DAN11-6X 8 COLLAR

57 DAN5-6-7Y 2 PIN

58 DAN5-6-8Y 4 PIN

59 DAN7-8-12X 2 PIN

60 DAN7-8-10Y 20 PIN

61 DAN7-8-11Y 20 PIN

62 DAN7-8-12Y 14 PIN

63 EN6115K3-3 12 BOLT

64 EN6115K3-4 14 BOLT

65 EN6115K3-5 22 BOLT

66 EN6115K3-7 10 BOLT

67 EN6115K3-8 8 BOLT

68 EN6115K5-10 8 BOLT

69 EN6115K5-11 8 BOLT

70 EN6115K5-12 8 BOLT

71 EN6115K5-17 8 BOLT

72 EN6115K5-19 8 BOLT

73 LN9198-4012CF 1 RIVET

74 LN9198-4014CF 1 RIVET

75 EN6080D5-06 1 RIVET

76 LN9198-4812CF 2 RIVET

77 EN6081D6-08 6 RIVET

124 EN6115K3A7 2 BOLT

125 EN6115K3A8 2 BOLT

126 ASNA2528-3A 4 NUT

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

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

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

to part number relationship.

Kit 533160D05R01

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

NOTES

20 DAN5-6-4 2 PIN

28 DAN7-8-11 2 PIN

29 DAN7-10-11 5 PIN

30 DAN7-10-12 5 PIN

32 DAN5-6-7X 5 PIN

33 DAN5-6-10X 5 PIN

46 NSA5075-6 2 COLLAR

48 DAN12-8 2 COLLAR

49 DAN12-10 5 COLLAR

50 ASNA2528-3 5 NUT

51 ASNA2528-4 4 NUT

52 ASNA2528-5 10 NUT

53 NSA5330-6 5 COLLAR

54 DAN12-8Y 2 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

57 DAN5-6-7Y 4 PIN

62 DAN7-8-12Y 2 PIN

68 EN6115K5-10 5 BOLT

69 EN6115K5-11 5 BOLT

70 EN6115K5-12 5 BOLT

78 DAN5-6-3X 5 PIN

79 DAN5-6-4X 4 PIN

80 DAN5-6-5X 5 PIN

81 DAN5-6-6X 5 PIN

82 DAN5-6-8X 5 PIN

83 DAN7-8-9X 5 PIN

84 DAN7-8-10X 4 PIN

85 DAN7-8-11X 5 PIN

86 DAN7-10-11X 5 PIN

87 DAN7-10-12X 5 PIN

88 DAN7-10-17X 4 PIN

89 DAN5-6-10Y 4 PIN

90 DAN7-10-13 5 PIN

91 DAN7-10-15 5 PIN

92 DAN7-10-16 5 PIN

93 EN6115K5-7 5 BOLT

94 EN6115K5-8 6 BOLT

95 EN6115K5-15 2 BOLT

96 EN6115K5-16 2 BOLT

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

NOTES

97 DAN12-10X 5 COLLAR

98 NSA5075-8 5 COLLAR

99 DAN5-8-7 2 PIN

100 DAN5-8-8 4 PIN

101 DAN7-10-10 5 PIN

102 EN6115K3X3 5 BOLT

103 EN6115K3X4 5 BOLT

104 EN6115K3X5 5 BOLT

105 EN6115K4-7 2 BOLT

106 EN6115K3X7 5 BOLT

107 EN6115K3X8 5 BOLT

108 EN6115K4-8 2 BOLT

109 EN6115K5X10 5 BOLT

110 EN6115K5X11 5 BOLT

111 EN6115K5X12 5 BOLT

112 EN6115K5X17 5 BOLT

113 EN6115K5X19 5 BOLT

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

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

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

to part number relationship.

Kit 533160D06R01

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

NOTES

32 DAN5-6-7X 2 PIN

34 DAN7-6-11Y 5 PIN

40 EN6115K4Y10 5 BOLT

41 EN6115K4Y11 5 BOLT

42 EN6115K4Y12 5 BOLT

47 DAN12-6Y 5 COLLAR

51 ASNA2528-4 5 NUT

54 DAN12-8Y 5 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 4 COLLAR

59 DAN7-8-12X 5 PIN

61 DAN7-8-11Y 5 PIN

62 DAN7-8-12Y 5 PIN

82 DAN5-6-8X 4 PIN

84 DAN7-8-10X 5 PIN

85 DAN7-8-11X 5 PIN

114 DAN7-6-9Y 5 PIN

115 DAN7-6-10Y 2 PIN

116 DAN7-8-17Y 4 PIN

117 DAN7-6-11X 2 PIN

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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

NOTES

118 DAN7-8-13X 5 PIN

119 DAN7-8-15X 5 PIN

120 DAN7-8-16X 5 PIN

121 DAN12-6X 2 COLLAR

122 EN6115K4Y17 5 BOLT

123 EN6115K4Y19 5 BOLT

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

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

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

sealant 09-013 As required

sealant 09-016 As required

cleaning agent 11-026 As required

corrosion preventive 15-005 As required

polyurethane primer 16-001 As required

polyurethane top coat 16-018 As required

wash primer 16-020 As required

lint-free cloth 19-003 As required

(2) Components

To accomplish this Service Bulletin, it is necessary to use parts and tools listed in AMM

51-31-11.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(2) Tools

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

cold working:

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

51-012.

- Capital tool kit FTI-A330-53-3160-1No.:

The capital tools provided in this kit are not specific to this Service Bulletin and are

normally already available in operators’ stock as a long term investment or can be

loaned from FTI.

- Durable tool kit No.: DK-A330-53-3160-1

The durable tool kit contains the minimum quantity of durable tools necessary to

accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be

accomplished on more than one aircraft, the number of durable kits required can be

established by SIL 51-012.

- Expendable tool kit No.: EK-A330-53-3160-1

The expendable tool kit contains the quantity of expendable tools necessary to

accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for

every aircraft on which this Service Bulletin is to be accomplished.

(3) Special Tools

None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 24

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 533160-831-848-001 - MODIFICATION

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 190.50

ELAPSED TIME (HOURS) 97.50

**CONF 002

Manpower

TOTAL MANHOURS 192.50

ELAPSED TIME (HOURS) 99.50

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 533160-910-203-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

sealant 09-013 As required

sealant 09-016 As required

polyurethane primer 16-001 As required

polyurethane top coat 16-018 As required

wash primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00

51-24-00

51-42-11

51-43-00

51-44-11

51-46-11, Page Block 001

51-46-12

(a) Refer to the Standards Manual (SM) if you find part numbers for the hardware

components in the related kit(s) which you can not identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part

number to part number relationship.

(b) For the specification of the consumable materials (Refer to Consumable Material

List (CML)).

(c) For the identification of access panels (Refer to AMM 06-41-53, Page Block 001).

(d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(e) Remove old sealant with non-metallic scraper and a stiff brush.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(f) For fastener removal/installation (Rlefer to SRM 51-42-11).

(g) For fastener hole and drill data (Refer to SRM 51-44-11).

(h) To transfer drill holes, use a pilot drill and a drill bush.

(i) Make sure you have the correct edge clearance before you drill the holes.

(j) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(k) For spot facing of fastener holes (Refer to SRM 51-46-12).

(l) For countersinking of fastener holes (Refer to SRM 51-46-11, Page Block 001).

(m) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(n) Before the installation of structural items, apply

sealant 09-005 As required

on the mating surfaces.

(o) Wet install rivets, pins and collars with

sealant 09-005 As required

(p) After installation of structural items, apply fillet seal around the edges with

sealant 09-013 As required

or

sealant 09-016 As required

(q) For the procedure to use sealant (Refer to SRM 51-24-00).

(r) After rework, apply

wash primer 16-020 As required

polyurethane primer 16-001 As required

and

polyurethane top

coat

16-018 As required

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

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(2) Subtask 533160-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 533160-910-203-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

sealant 09-013 As required

sealant 09-016 As required

polyurethane primer 16-001 As required

polyurethane top coat 16-018 As required

wash primer 16-020 As required

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-00

51-24-00

51-42-11

51-43-00

51-44-11

51-46-11, Page Block 001

51-46-12

(a) Refer to the Standards Manual (SM) if you find part numbers for the hardware

components in the related kit(s) which you can not identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part

number to part number relationship.

(b) For the specification of the consumable materials (Refer to Consumable Material

List (CML)).

(c) For the identification of access panels (Refer to AMM 06-41-53, Page Block 001).

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(d) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(e) Remove old sealant with non-metallic scraper and a stiff brush.

(f) For fastener removal/installation (Rlefer to SRM 51-42-11).

(g) For fastener hole and drill data (Refer to SRM 51-44-11).

(h) To transfer drill holes, use a pilot drill and a drill bush.

(i) Make sure you have the correct edge clearance before you drill the holes.

(j) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(k) For spot facing of fastener holes (Refer to SRM 51-46-12).

(l) For countersinking of fastener holes (Refer to SRM 51-46-11, Page Block 001).

(m) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(n) Before the installation of structural items, apply

sealant 09-005 As required

on the mating surfaces.

(o) Wet install rivets, pins and collars with

sealant 09-005 As required

(p) After installation of structural items, apply fillet seal around the edges with

sealant 09-013 As required

or

sealant 09-016 As required

(q) For the procedure to use sealant (Refer to SRM 51-24-00).

(r) After rework, apply

wash primer 16-020 As required

polyurethane primer 16-001 As required

and

polyurethane top

coat

16-018 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

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

(2) Subtask 533160-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 533160-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

25-33-48, Page Block 401

25-33-52, Page Block 401

25-33-53, Page Block 401

25-33-54, Page Block 401

27-51-18, Page Block 401

29-00-00, Page Block 201

29-14-00, Page Block 201

36-12-41, Page Block 401

36-22-17, Page Block 401

52-10-00, Page Block 201

55-31-11, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page

Block 201).

(b) Put the access platform(s) in position in the rear fuselage area and at the FWD

passenger/crew doors.

(c) Open the access door 312AR in the rear fuselage area.

(d) Open the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block

201).

(e) Depressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM

29-00-00, Page Block 201).

(f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to

AMM 29-14-00, Page Block 201).

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(g) Put warning notices in position to tell persons not to pressurize the hydraulic

systems

1 in the cockpit on the hydraulic section 40VU of the overhead panel,

2 on the ground service panel of each hydraulic system.

(h) Open, safety and tag the circuit breaker(s) which are listed in

1 AMM 27-51-18, Page Block 401.

(i) Remove the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401).

(j) Remove the Bleed Air pipe sense line between FR85 and FR87, (Refer to AMM

36-22-17, Page Block 401).

(k) Remove the Bleed Air pipe between FR85 and FR87, (Refer to AMM 36-12-41,

Page Block 401).

(l) Remove the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the

AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401).

(m) Remove the AFT galley (Refer to AMM 25-33-52, Page Block 401 and AMM

25-33-53, Page Block 401).

**CONF 002

(1) Subtask 533160-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

25-33-48, Page Block 401

25-33-52, Page Block 401

25-33-53, Page Block 401

25-33-54, Page Block 401

27-51-18, Page Block 401

29-00-00, Page Block 201

29-14-00, Page Block 201

36-12-41, Page Block 401

36-22-17, Page Block 401

52-10-00, Page Block 201

55-31-11, Page Block 401

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24, Page

Block 201).

(b) Put the access platform(s) in position in the rear fuselage area and at the FWD

passenger/crew doors.

(c) Open the access door 312AR in the rear fuselage area.

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(d) Open the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page Block

201).

(e) Depressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM

29-00-00, Page Block 201).

(f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to

AMM 29-14-00, Page Block 201).

(g) Put warning notices in position to tell persons not to pressurize the hydraulic

systems

1 in the cockpit on the hydraulic section 40VU of the overhead panel,

2 on the ground service panel of each hydraulic system.

(h) Open, safety and tag the circuit breaker(s) which are listed in

1 AMM 27-51-18, Page Block 401.

(i) Remove the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401).

(j) Remove the Bleed Air pipe sense line between FR85 and FR87, (Refer to AMM

36-22-17, Page Block 401).

(k) Remove the Bleed Air pipe between FR85 and FR87, (Refer to AMM 36-12-41,

Page Block 401).

(l) Remove the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the

AFT galley pelmet (Refer to AMM 25-33-48, Page Block 401).

(m) Remove the AFT galley (Refer to AMM 25-33-52, Page Block 401 and AMM

25-33-53, Page Block 401).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 533160-831-204-001 - Remove the fasteners in the upper fuselage shell

between FR80 and FR87.

Manpower Resources

Manhours 2.25

Minimum number of person 2

Subtask elapsed time 1.75

Skills AIRFRAME

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References

Fig. A-GBAAA

Removal of Fastener from the upper

fuselage shell between FR80 and FR86

Sheet 01

Sheet 02

Sheet 03

Sheet 04

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) At FR80 between STGR2 LH/RH and STGR5 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 03, View C:

6 pin DAN5-8-8 Item (39) Discard

6 collar NAS5075-8 Item (51) Discard

(b) At FR84 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B:

12 pin DAN5-6-5 Item (36) Discard

8 pin DAN5-8-10 Item (40) Discard

2 pin DAN5-6-7 Item (37) Discard

8 pin DAN5-8-11 Item (41) Discard

52 pin DAN5-8-7 Item (38) Discard

4 rivet LN9198-4800CF Item (44) Discard

2 rivet LN9198-4000CF Item (43) Discard

14 collar NSA5075-6 Item (54) Discard

68 collar NSA5075-8 Item (51) Discard

1 angle A53985256206 Item (130) Retain

2 angle F53577990000 Item (131) Retain

(c) At FR85 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B:

4 pin DAN5-8-10 Item (40) Discard

4 pin DAN5-8-11 Item (41) Discard

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4 pin DAN5-8-7 Item (38) Discard

12 collar NSA5075-8 Item (51) Discard

(d) At FR86 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, View B:

16 pin DAN5-6-5 Item (36) Discard

12 pin DAN5-8-11 Item (41) Discard

8 pin DAN5-8-14 Item (42) Discard

82 pin DAN5-8-7 Item (38) Discard

4 pin DAN5-8-10 Item (40) Discard

4 rivet LN9198-4800CF Item (44) Discard

2 rivet LN9198-4000CF Item (43) Discard

16 collar NSA5075-6 Item (54) Discard

106 collar NSA5075-8 Item (51) Discard

2 angle F53577990000 Item (131) Retain

1 angle A53985256206 Item (132) Discard

(2) Subtask 533160-831-205-001 - Do the Eddy Current Rotating Probe Testing FR80,

FR84 and FR86 to find cracks around the holes of the previous removed fasteners.

Manpower Resources

Manhours 3.00

Minimum number of person 3

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 , Procedure A

Fig. A-GBDAA

Inspection Areas of Fastener Hole

Rototest and for HFEC Inspection

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

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CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Do the Eddy Current Rotating Probe Testing , as shown on Fig. A-GBDAA Sheet

01, Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 and

Fig. A-GBDAA Sheet 05 (Refer to NTM 51-10-01, Page Block 601, Procedure A).

NOTE: Check only the fastener holes for the fasteners which have been

removed to accomplish this modification.

1 In case of no crack finding, continue with the accomplishment of the

modification.

2 In case of crack finding, contact AIRBUS for repair.

(3) Subtask 533160-831-206-001 - Do the eddy current high frequency inspection of

FR84 and FR86 to find cracks between the fastener rows.

Manpower Resources

Manhours 2.50

Minimum number of person 2

Subtask elapsed time 1.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GBDAA

Inspection Areas of Fastener Hole

Rototest and for HFEC Inspection

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Do a eddy current high frequency inspection from the fuselage outside, as shown

on Fig. A-GBDAA Sheet 01, Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig.

A-GBDAA Sheet 04 andFig. A-GBDAA Sheet 05 (Refer to NTM 51-10-08, Page

Block 601).

1 In case of no crack finding, continue with the accomplishment of the

modification.

2 In case of crack finding, contact AIRBUS for repair.

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(4) Subtask 533160-831-207-001 - Do a check of the fastener position to make sure

that the edge clearance of all existing fastener holes is correct.

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

References

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

Fig. A-GBAAA

Removal of Fastener from the upper

fuselage shell between FR80 and FR86

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBEAA

Flow Chart of Fastener Installation

Process and Example of Fastener Hole

Reworking

Sheet 01

Sheet 02

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Check the edge clearance of all fastener holes from the outside and from the inside

of the fuselage shell as shown on Fig. A-GBAAA Sheet 01, Fig. A-GBAAA Sheet

02 and Fig. A-GBAAA Sheet 04. If the edge clearance is very close for the current

fasteners, try to rework the fastener holes to keep the minimum distance to the

structure edge after re-drilling to the final fastener hole diameter as shown on Fig.

A-GBEAA Sheet 01 and Fig. A-GBEAA Sheet 02. For the correct edge clearance,

refer to SRM 51-47-00. Only in the case that the fastener hole can not be moved to

keep the correct edge clearance, an undersize fastener of Kit 533160D03R01

should be installed, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA

Sheet 10.

NOTE: In accordance with SRM 51-47-00, Edge Distance for Milling Steps,

the additional distance of 1.0 mm (0.039 in) to the edge margin for

higher milling steps than 1.0 mm is not applicable for these fastener

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holes.

NOTE: The installation of undersize fastener is limited by five fastener per

reinforcement bracket with a maximum of two fastener adjacent to

each other.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

(5) Subtask 533160-831-208-001 - Install 6 fasteners with cold working in the upper

fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH.

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Kit 533160D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

39 EN6115K4Y8 6 BOLT

51 ASNA2528-4 6 NUT

Kit 533160D02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 ASNA2528-5 6 NUT

94 EN6115K5-8 6 BOLT

References

Structural Repair Manual (SRM) 51-48-00

51-48-00, Page Block 001

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References

Fig. A-GBBAA

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page Block 001 and Fig. AGBCAA Sheet 06.

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

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

Sheet 07.

(d) Expand the fastener holes (Refer to SRM 51-48-00, Page Block 001.

(e) Ream the fastener holes with the correct gage finish reamer, as shown on Fig. AGBCAA Sheet 07.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01 .

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin

with the associated nut or collar which is part of Kit 533160D02R05.

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(f) At the FR80 in the upper fuselage install as given in Figure Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02, View C and Fig. A-GBCAA Sheet 07:

6 Bolt EN6115K4Y8 Item 39

6 Nut ASNA2528-4 Item 51

or next oversize (part of Kit 533160D02R05)

6 Bolt EN6115K5-8 Item 94

6 Nut ASNA2528-5 Item 52

(6) Subtask 533160-831-209-001 - Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR86.

Manpower Resources

Manhours 35.00

Minimum number of person 3

Subtask elapsed time 11.50

Skills AIRFRAME

Material necessary to do the job

Kit 533160D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 F5357716920000 1 DOUBLER

2 F5357716920100 1 DOUBLER

3 F5357716920200 1 DOUBLER

4 F5357716920300 1 DOUBLER

5 F5357798920000 1 SHIM

6 F5357798920100 1 SHIM

7 F5357798920200 1 SHIM

8 F5357798920300 1 SHIM

9 A5398525620600 1 ANGLE

18 DAN5-5-4 2 PIN

19 DAN5-6-3 14 PIN

20 DAN5-6-4 2 PIN

21 DAN5-6-5 10 PIN

22 DAN5-6-6 20 PIN

24 DAN5-6-8 10 PIN

26 DAN7-8-9 4 PIN

27 DAN7-8-10 4 PIN

28 DAN7-8-11 6 PIN

29 DAN7-10-11 8 PIN

30 DAN7-10-12 6 PIN

31 DAN7-10-17 4 PIN

38 EN6115K4Y7 16 BOLT

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

40 EN6115K4Y10 4 BOLT

41 EN6115K4Y11 4 BOLT

42 EN6115K4Y12 14 BOLT

45 NSA5075-5 2 COLLAR

46 NSA5075-6 56 COLLAR

48 DAN12-8 14 COLLAR

49 DAN12-10 18 COLLAR

50 ASNA2528-3 26 NUT

51 ASNA2528-4 38 NUT

52 ASNA2528-5 40 NUT

53 NSA5330-6 6 COLLAR

54 DAN12-8Y 10 COLLAR

57 DAN5-6-7Y 2 PIN

58 DAN5-6-8Y 4 PIN

60 DAN7-8-10Y 4 PIN

61 DAN7-8-11Y 4 PIN

62 DAN7-8-12Y 2 PIN

63 EN6115K3-3 10 BOLT

64 EN6115K3-4 6 BOLT

65 EN6115K3-5 10 BOLT

68 EN6115K5-10 8 BOLT

69 EN6115K5-11 8 BOLT

70 EN6115K5-12 8 BOLT

71 EN6115K5-17 8 BOLT

72 EN6115K5-19 8 BOLT

75 EN6080D5-06 1 RIVET

76 LN9198-4812CF 2 RIVET

77 LN9198-4814CF 4 RIVET

124 EN6115K3A7 2 BOLT

126 ASNA2528-3A 2 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

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References

Fig. A-GBBAA

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 5 and the doubler, item 1 to the fuselage structure.

2 Countersink (100 DEG) the rivet hole, previously used to fit the angle, item

(132), as shown on Fig. A-GBBAA Sheet 03.

3 Close one rivet hole, previously used to fit the angle, item (132), as shown on

Fig. A-GBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet

06 with

1 Rivet EN6080D5-06 Item 75

NOTE: Install the rivet, item 75, with 09-005 sealant.

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4 Put the shim, item 5 and the doubler, item 1 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 03.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

5 Transfer drill the pilot holes from the shim, item 5 and from the doubler, item 1

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

6 Transfer drill the existing fastener holes from the fuselage structure to the

doubler, item 1, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

7 Mark the fastener holes with a soft felt pen which have to be expand by cold

working, as shown on Fig. A-GBBAA Sheet 04.

8 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

9 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

10 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

11 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

13 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

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

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15 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

16 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

05.

17 Remove the angle, item 9, from the fuselage skin.

18 Remove the doubler, item 1 and the shim, item 5 from the fuselage structure.

19 Deburr the fastener holes.

20 Clean the shim, item 5, the doubler, item 1 and the fuselage structure with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

21 Install with screw pins, as shown on Fig. A-GBCAA Sheet 03:

1 Doubler F5357716920000 Item 1

1 Shim F5357798920000 Item 5

with:

sealant 09-005 As required

22 Put in position, with

sealant 09-005 As required

and secure with screw pins, as shown on Fig. A-GBCAA Sheet 03:

1 Angle A5398525620600 Item 9

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23 To the fuselage skin, the doubler, item 1 and the shim, item 5, install with

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables on Fig. A-GBCAA Sheet

01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or

pin with the associated nut or collar which is part of Kit

533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

2 Pin DAN5-5-4 Item 18

3 Pin DAN5-6-3 Item 19

2 Pin DAN5-6-5 Item 21

4 Pin DAN5-6-6 Item 22

2 Pin DAN5-6-8 Item 24

b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

2 Pin DAN7-8-11 Item 28

4 Pin DAN7-10-11 Item 29

c For the following fasteners, as shown on Fig. A-GBCAA Sheet 03.

3 Pin DAN7-10-12 Item 30

2 Pin DAN7-10-17 Item 31

d For the following fasteners, as shown on Fig. A-GBCAA Sheet 05.

1 Pin DAN5-6-7Y Item 57

2 Pin DAN5-6-8Y Item 58

2 Pin DAN7-8-10Y Item 60

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2 Pin DAN7-8-11Y Item 61

e For the following fasteners, as shown on Fig. A-GBCAA Sheet 06.

1 Pin DAN7-8-12Y Item 62

f For the following fasteners, as shown on Fig. A-GBCAA Sheet 07.

3 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Bolt EN6115K4Y12 Item 42

g For the following fasteners, as shown on Fig. A-GBCAA Sheet 08.

2 Bolt EN6115K3-3 Item 63

2 Bolt EN6115K3-4 Item 64

2 Bolt EN6115K3-5 Item 65

1 Bolt EN6115K3A7 Item 124

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

4 Bolt EN6115K5-17 Item 71

with

4 Nut ASNA2528-5 Item 52

13 Nut ASNA2528-4 Item 51

6 Nut ASNA2528-3 Item 50

5 Collar DAN12-8Y Item 54

11 Collar NSA5075-6 Item 46

3 Collar NSA5330-6 Item 53

2 Collar NSA5075-5 Item 45

4 Collar DAN12-8 Item 48

9 Collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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24 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 6 and the doubler, item 2 to the fuselage structure.

2 Put the shim, item 6 and the doubler, item 2 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 05.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 6 and from the doubler, item 2

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 2, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

5 Mark the fastener holes with a soft felt pen which have to be expand by cold

working, as shown on Fig. A-GBCAA Sheet 06.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 for all

fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

14 Remove the doubler, item 2 and the shim, item 6 from the fuselage structure.

15 Deburr the fastener holes.

16 Clean the shim, item 6, the doubler, item 2 and the fuselage structure with

cleaning agent 11-026 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 47

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SERVICE BULLETIN

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 05:

1 Doubler F5357716920100 Item 2

1 Shim F5357798920100 Item 6

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 2 and the shim, item 6, install with:

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables on Fig. A-GBCAA Sheet

01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or

pin with the associated nut or collar which is part of Kit

533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

5 Pin DAN5-6-3 Item 19

2 Pin DAN5-6-5 Item 21

4 Pin DAN5-6-6 Item 22

2 Pin DAN5-6-8 Item 24

b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

2 Pin DAN7-8-11 Item 28

c For the following fasteners, as shown on Fig. A-GBCAA Sheet 03.

4 Pin DAN7-10-11 Item 29

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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3 Pin DAN7-10-12 Item 30

2 Pin DAN7-10-17 Item 31

d For the following fasteners, as shown on Fig. A-GBCAA Sheet 05.

1 Pin DAN5-6-7Y Item 57

2 Pin DAN5-6-8Y Item 58

2 Pin DAN7-8-10Y Item 60

2 Pin DAN7-8-11Y Item 61

e For the following fasteners, as shown on Fig. A-GBCAA Sheet 06.

1 Pin DAN7-8-12Y Item 62

f For the following fasteners, as shown on Fig. A-GBCAA Sheet 07.

3 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Bolt EN6115K4Y12 Item 42

g For the following fasteners, as shown on Fig. A-GBCAA Sheet 08.

2 Bolt EN6115K3-3 Item 63

2 Bolt EN6115K3-4 Item 64

2 Bolt EN6115K3-5 Item 65

1 Bolt EN6115K3A7 Item 124

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

4 Bolt EN6115K5-17 Item 71

with:

4 Nut ASNA2528-5 Item 52

13 Nut ASNA2528-4 Item 51

6 Nut ASNA2528-3 Item 50

5 Collar DAN12-8Y Item 54

13 Collar NSA5075-6 Item 46

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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3 Collar NSA5330-6 Item 53

4 Collar DAN12-8 Item 48

9 Collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

19 Clean the repair area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(c) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A

L/H.

1 Clean the working area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 7 and the doubler, item 3 to the fuselage structure.

2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAA

Sheet 07, View J.

3 Drill with a 4.8 mm (0.19 in.) DIA drill the new hole with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole.

5 Remove the surface protection around the rivet holes of angle, item (131), for

electrical bonding.

6 Install, as shown on Fig. A-GBBAA Sheet 07, Fig. A-GBBAA Sheet 08 and

Fig. A-GBCAA Sheet 06:

1 angle F53577990000 Item (131)

1 Rivet LN9198-4812CF Item 76

2 Rivet LN9198-4814CF Item 77

with:

sealant 09-005 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

NOTE: Install the angle, item (131), as electrical bonding point, refer to

ESPM 20-51-20 and refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 7 and the doubler, item 3 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 07.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Transfer drill the pilot holes from the shim, item 7 and from the doubler, item 3

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 3, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 08.

11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to

maximum of 16 mm (0.63 in) on the doubler, item 3 located at FR86, as

shown on Fig. A-GBBAA Sheet 08.

20 Remove the doubler, item 3 and the shim, item 7 from the fuselage structure.

21 Deburr the fastener holes.

22 Clean the shim, item 7, the doubler, item 3 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 07:

1 Doubler F5357716920200 Item 3

1 Shim F5357798920200 Item 7

with:

sealant 09-005 As required

24 To the fuselage skin, the doubler, item 3 and the shim, item 7, install with

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 52

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NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

3 Pin DAN5-6-3 Item 19

1 Pin DAN5-6-4 Item 20

3 Pin DAN5-6-5 Item 21

6 Pin DAN5-6-6 Item 22

3 Pin DAN5-6-8 Item 24

b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

1 Pin DAN7-8-11 Item 28

c For the following fasteners, as shown on Fig. A-GBCAA Sheet 07.

5 Bolt EN6115K4Y7 Item 38

1 Bolt EN6115K4Y12 Item 42

d For the following fasteners, as shown on Fig. A-GBCAA Sheet 08.

3 Bolt EN6115K3-3 Item 63

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

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

4 Bolt EN6115K5-10 Item 68

4 Bolt EN6115K5-11 Item 69

4 Bolt EN6115K5-12 Item 70

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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f For the following fasteners, as shown on Fig. A-GBCAA Sheet 10.

4 Bolt EN6115K5-19 Item 72

with

3 Collar DAN12-8 Item 48

6 Nut ASNA2528-4 Item 51

7 Nut ASNA2528-3 Item 50

16 Nut ASNA2528-5 Item 52

16 Collar NSA5075-6 Item 46

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(d) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 8 and the doubler, item 4 to the fuselage structure.

2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAA

Sheet 07, View J.

3 Drill with a 4.8 (0.19 in.) mm DIA drill the new hole with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole.

5 Remove the surface protection around the rivet holes of the angle, item (131)

for electrical bonding.

6 Install, as shown on Fig. A-GBBAA Sheet 07, Fig. A-GBBAA Sheet 08 and

Fig. A-GBCAA Sheet 06:

1 Angle F53577990000 Item (131)

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

1 Rivet LN9198-4812CF Item 76

2 Rivet LN9198-4814CF Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131) as electrical bonding point, refer to

ESPM 20-51-20 refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 8 and the doubler, item 4 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 07.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Transfer drill the pilot holes from the shim, item 8 and from the doubler, item 4

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 4, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 08.

11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to

maximum of 16 mm (0.63 in) on the doubler, item 4 located at FR86, as

shown on Fig. A-GBBAA Sheet 08.

20 Remove the doubler, item 4 and the shim, item 8 from the fuselage structure.

21 Deburr the fastener holes.

22 Clean the shim, item 8, the doubler, item 4 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 07:

1 Doubler F5357716920300 Item 4

1 Shim F5357798920300 Item 8

with:

sealant 09-005 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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24 To the fuselage skin, the doubler, item 4 and the shim, item 8, install with

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

3 Pin DAN5-6-3 Item 19

1 Pin DAN5-6-4 Item 20

3 Pin DAN5-6-5 Item 21

6 Pin DAN5-6-6 Item 22

3 Pin DAN5-6-8 Item 24

b For the following fasteners, as shown on Fig. A-GBCAA Sheet 02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

1 Pin DAN7-8-11 Item 28

c For the following fasteners, as shown on Fig. A-GBCAA Sheet 07.

5 Bolt EN6115K4Y7 Item 38

1 Bolt EN6115K4Y12 Item 42

d For the following fasteners, as shown on Fig. A-GBCAA Sheet 08.

3 Bolt EN6115K3-3 Item 63

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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

4 Bolt EN6115K5-10 Item 68

4 Bolt EN6115K5-11 Item 69

4 Bolt EN6115K5-12 Item 70

f For the following fasteners, as shown on Fig. A-GBCAA Sheet 10.

4 Bolt EN6115K5-19 Item 72

with

6 Nut ASNA2528-4 Item 51

3 Collar DAN12-8 Item 48

16 Nut ASNA2528-5 Item 52

7 Nut ASNA2528-3 Item 50

16 Collar NSA5075-6 Item 46

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(7) Subtask 533160-831-210-001 - Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR84.

Manpower Resources

Manhours 33.50

Minimum number of person 3

Subtask elapsed time 10.50

Skills AIRFRAME

Material necessary to do the job

Kit 533160D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 F5357716921800 1 DOUBLER

11 F5357716921900 1 DOUBLER

12 F5357716922100 1 DOUBLER

13 F5357716922000 1 DOUBLER

14 F5357798921200 1 SHIM

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 F5357798921400 1 SHIM

16 F5357798921700 1 SHIM

17 F5357798921600 1 SHIM

23 DAN5-6-7 8 PIN

24 DAN5-6-8 6 PIN

25 DAN5-6-10 8 PIN

28 DAN7-8-11 6 PIN

32 DAN5-6-7X 4 PIN

33 DAN5-6-10X 4 PIN

34 DAN7-6-11Y 2 PIN

35 DAN7-8-13Y 6 PIN

36 DAN7-8-15Y 6 PIN

37 DAN7-8-16Y 6 PIN

43 EN6115K4Y15 2 BOLT

44 EN6115K4Y16 2 BOLT

46 NSA5075-6 22 COLLAR

47 DAN12-6Y 2 COLLAR

48 DAN12-8 6 COLLAR

50 ASNA2528-3 34 NUT

51 ASNA2528-4 4 NUT

54 DAN12-8Y 62 COLLAR

55 DAN12-8X 2 COLLAR

56 DAN11-6X 8 COLLAR

59 DAN7-8-12X 2 PIN

60 DAN7-8-10Y 16 PIN

61 DAN7-8-11Y 16 PIN

62 DAN7-8-12Y 12 PIN

64 EN6115K3-4 4 BOLT

65 EN6115K3-5 12 BOLT

66 EN6115K3-7 10 BOLT

67 EN6115K3-8 8 BOLT

73 LN9198-4012CF 1 RIVET

74 LN9198-4014CF 1 RIVET

77 LN9198-4814CF 4 RIVET

125 EN6115K3A8 2 BOLT

126 ASNA2528-3A 2 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 59

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

Fig. A-GBBAA

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 10 and the doubler, item 14 to the fuselage structure.

2 Mark the new holes for the angles, item (130) and (131), as shown on Fig. AGBBAA Sheet 09, View N.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

3 Drill with a 4.1 mm (0.16 in.) DIA drill the new holes with the angle, item (130).

4 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131).

5 Remove the angles, item (130) and (131) from the fuselage skin and deburr

the rivet holes.

6 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

7 Install, as shown on Fig. A-GBBAA Sheet 09, Fig. A-GBBAA Sheet 10 and

Fig. A-GBCAA Sheet 06:

1 angle A5398525620600 Item (130)

1 angle F5357799000000 Item (131)

1 Rivet LN9198-4012CF Item 73

1 Rivet LN9198-4014CF Item 74

2 Rivet LN9198-4814CF Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131) as electrical bonding point, refer to

ESPM 20-51-20 refer to AMM Task 20-28-00-912-801.

8 Put the shim, item 14 and the doubler, item 10 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 09.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the pilot holes from the shim, item 14 and from the doubler, item

10 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

10 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 10 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

11 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 10.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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12 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

13 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

14 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

16 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

17 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

18 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

19 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

20 Remove the doubler, item 10 and the shim, item 14 from the fuselage

structure.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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21 Deburr the fastener holes.

22 Clean the shim, item 14, the doubler, item 10 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins, as shown on Fig. A-GBBAA Sheet 09:

1 Doubler F5357716921800 Item 10

1 Shim F5357798921200 Item 14

with:

sealant 09-005 As required

24 To the fuselage skin, the doubler, item 10 and the shim, item 14, install with

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

01.

1 Pin DAN5-6-7 Item 23

2 Pin DAN5-6-8 Item 24

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

02.

2 Pin DAN5-6-10 Item 25

1 Pin DAN7-8-11 Item 28

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

03.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

2 Pin DAN5-6-7X Item 32

1 Pin DAN5-6-10X Item 33

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

04.

1 Pin DAN7-6-11Y Item 34

3 Pin DAN7-8-15Y Item 36

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

05.

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

5 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y15 Item 43

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

3 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

with

5 Collar NSA5075-6 Item 46

1 Collar DAN12-6Y Item 47

1 Collar DAN12-8 Item 48

9 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

16 Collar DAN12-8Y Item 54

3 Collar DAN11-6X Item 56

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 11 and the doubler, item 15 to the fuselage structure.

2 Mark the new holes for the angle, item (131), as shown on Fig. A-GBBAA

Sheet 11, View R.

3 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet

holes.

5 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

6 Install, as shown on Fig. A-GBBAA Sheet 11, Fig. A-GBBAA Sheet 12 and

Fig. A-GBCAA Sheet 06:

1 angle F5357799000000 Item (131)

2 Rivet LN9198-4814CF Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131), as bonding point, refer to ESPM

20-51-20 refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 15 and the doubler, item 11 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 11.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

8 Transfer drill the pilot holes from the shim, item 15 and from the doubler, item

11 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 11 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 12.

11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04Kit 533160D03R01, use a smaller

fastener (part of Kit 533160D03R01) as given in the fastener table, as shown

on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 66

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SERVICE BULLETIN

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Remove the doubler, item 11 and the shim, item 15 from the fuselage

structure.

20 Deburr the fastener holes.

21 Clean the shim, item 15, the doubler, item 11 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

22 Install with screw pins, as shown on Fig. A-GBBAA Sheet 11:

1 Doubler F5357716921900 Item 11

1 Shim F5357798921400 Item 15

with:

sealant 09-005 As required

23 To the fuselage skin, the doubler, item 11 and the shim, item 15, install with

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

01.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

1 Pin DAN5-6-7 Item 23

2 Pin DAN5-6-8 Item 24

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

02.

2 Pin DAN5-6-10 Item 25

1 Pin DAN7-8-11 Item 28

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

03.

1 Pin DAN5-6-10X Item 33

2 Pin DAN5-6-7X Item 32

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

04.

1 Pin DAN7-6-11Y Item 34

3 Pin DAN7-8-15Y Item 36

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

05.

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

5 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y15 Item 43

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

3 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

with

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

5 Collar NSA5075-6 Item 46

1 Collar DAN12-6Y Item 47

1 Collar DAN12-8 Item 48

9 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

16 Collar DAN12-8Y Item 54

3 Collar DAN11-6X Item 56

24 Clean the repair area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(c) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A

L/H.

1 Clean the working area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 13 and the doubler, item 17 to the fuselage structure.

2 Put the shim, item 17 and the doubler, item 13 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 13.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 17 and from the doubler, item

13 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 13 with a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

5 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 14.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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14 Remove the doubler, item 13 and the shim, item 17 from the fuselage

structure.

15 Deburr the fastener holes.

16 Clean the shim, item 17, the doubler, item 13 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 13:

1 Doubler F5357716922000 Item 13

1 Shim F5357798921600 Item 17

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 13 and the shim, item 17, install with:

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

01.

1 Pin DAN5-6-8 Item 24

3 Pin DAN5-6-7 Item 23

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

02.

2 Pin DAN5-6-10 Item 25

2 Pin DAN7-8-11 Item 28

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 71

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

03.

1 Pin DAN5-6-10X Item 33

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

04.

3 Pin DAN7-8-13Y Item 35

3 Pin DAN7-8-16Y Item 37

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

05.

1 Pin DAN7-8-12X Item 59

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

NOTE: For the following fasteners, as shown Fig. A-GBCAA Sheet 06.

1 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y16 Item 44

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

2 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

1 Bolt EN6115K3A8 Item 125

with

6 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

8 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

15 Collar DAN12-8Y Item 54

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1 Collar DAN12-8X Item 55

1 Collar DAN11-6X Item 56

1 nut ASNA2528-3A Item 126

19 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(d) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 12 and the doubler, item 16 to the fuselage structure.

2 Put the shim, item 16 and the doubler, item 12 in the final position on the

fuselage structure, as shown on Fig. A-GBBAA Sheet 13.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 16 and from the doubler, item

12 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 12 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

5 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAA Sheet 14.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and, as shown on Fig. A-GBCAA Sheet 01Fig. A-GBCAA Sheet 10 for

all fastener holes.

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7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-001, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D01R04, use a smaller fastener (part of Kit

533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-001, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D01R04, use a smaller fastener (part of

Kit 533160D03R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 001 Installation of undersize fasteners of kit

533160D03R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

14 Remove the doubler, item 12 and the shim, item 16 from the fuselage

structure.

15 Deburr the fastener holes.

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16 Clean the shim, item 16, the doubler, item 12 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAA Sheet 13:

1 Doubler F5357716922100 Item 12

1 Shim F5357798921700 Item 16

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 12 and the shim, item 16, install with:

sealant 09-005 As required

as shown on Fig. A-GBBAA Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

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

01.

1 Pin DAN5-6-8 Item 24

3 Pin DAN5-6-7 Item 23

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

02.

2 Pin DAN5-6-10 Item 25

2 Pin DAN7-8-11 Item 28

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

03.

1 Pin DAN5-6-10X Item 33

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

04.

3 Pin DAN7-8-13Y Item 35

3 Pin DAN7-8-16Y Item 37

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

05.

1 Pin DAN7-8-12X Item 59

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

1 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y16 Item 44

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

2 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

1 Bolt EN6115K3A8 Item 125

with

6 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

8 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

15 Collar DAN12-8Y Item 54

1 Collar DAN12-8X Item 55

1 Collar DAN11-6X Item 56

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

1 nut ASNA2528-3A Item 126

19 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(8) Subtask 533160-831-211-001 - Install fasteners with cold working in the upper

fuselage skin at FR85

Manpower Resources

Manhours 2.25

Minimum number of person 2

Subtask elapsed time 1.25

Skills AIRFRAME

Material necessary to do the job

Kit 533160D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

38 EN6115K4Y7 4 BOLT

40 EN6115K4Y10 4 BOLT

41 EN6115K4Y11 4 BOLT

51 ASNA2528-4 12 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

References

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBBAA

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the fasteners with cold working at FR85 between STGR2B L/H and STGR5A

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

2 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Drill the marked fastener holes for cold working with the correct start drill, as

shown onFig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

4 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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5 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

6 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

7 Deburr the fastener holes.

8 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

9 Install the fastener with

sealant 09-005 As required

, as shown on Fig. A-GBBAA Sheet 15 and Fig. A-GBCAA Sheet 07:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

2 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Nut ASNA2528-4 Item 51

10 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the fasteners with cold working at FR85 between STGR2B R/H and STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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and

lint-free cloth 19-003 As required

2 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

4 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

5 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

6 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

7 Deburr the fastener holes.

8 Clean the repair area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

9 Install the fastener with:

sealant 09-005 As required

, as shown on Fig. A-GBBAA Sheet 15 and Fig. A-GBCAA Sheet 07:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D02R05.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 001 Oversize fasteners of kit 533160D02R01

.

2 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

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SERVICE BULLETIN

2 Bolt EN6115K4Y11 Item 41

6 Nut ASNA2528-4 Item 51

10 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

lint-free cloth 19-003 As required

(9) Subtask 533160-831-212-001 - Apply surface protection to the modification area.

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-013 As required

sealant 09-016 As required

corrosion preventive 15-005 As required

polyurethane primer 16-001 As required

polyurethane top coat 16-018 As required

wash primer 16-020 As required

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

Apply surface protection to the modification area.

(a) Apply

sealant 09-013 As required

or

sealant 09-016 As required

to form a bead around the new doubler and reinstalled angles.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(b) Apply

wash primer 16-020 As required

to all reworked edges and heads of fasteners.

(c) Apply

polyurethane primer 16-001 As required

to all reworked edges and heads of fasteners.

(d) Apply

polyurethane top

coat

16-018 As required

to all reworked edges and heads of fasteners.

(e) Apply

corrosion preventive 15-005 As required

to the modification area inside the fuselage.

(10) Subtask 533160-400-201-001 - Installation of undersize fasteners of kit

533160D03R01

Manpower Resources

Manhours 0.00

Minimum number of person 0

Subtask elapsed time 0.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533160D03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

32 DAN5-6-7X 2 PIN

34 DAN7-6-11Y 5 PIN

40 EN6115K4Y10 5 BOLT

41 EN6115K4Y11 5 BOLT

42 EN6115K4Y12 5 BOLT

47 DAN12-6Y 5 COLLAR

51 ASNA2528-4 5 NUT

54 DAN12-8Y 5 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

59 DAN7-8-12X 5 PIN

61 DAN7-8-11Y 5 PIN

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

62 DAN7-8-12Y 5 PIN

82 DAN5-6-8X 4 PIN

84 DAN7-8-10X 5 PIN

85 DAN7-8-11X 5 PIN

114 DAN7-6-9Y 4 PIN

115 DAN7-6-10Y 2 PIN

116 DAN7-8-17Y 4 PIN

117 DAN7-6-11X 2 PIN

118 DAN7-8-13X 5 PIN

119 DAN7-8-15X 5 PIN

120 DAN7-8-16X 5 PIN

121 DAN12-6X 2 COLLAR

122 EN6115K4Y17 5 BOLT

123 EN6115K4Y19 5 BOLT

References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

(a) The subsequent undersize fasteners are parts of Kit 533160D03R01.

NOTE: Depending of the edge margin measurement requested with

subtask 533160-831-207-001 undersize fasteners can be installed.

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

NOTE: The installation of undersize fasteners is limited by five fasteners

per reinforcement bracket with a maximum of two fasteners

adjacent to each other.

If it is not the case, contact AIRBUS.

2 Pin DAN5-6-7X Item 32

5 Pin DAN7-6-11Y Item 34

5 Bolt EN6115K4Y10 Item 40

5 Bolt EN6115K4Y11 Item 41

5 Bolt EN6115K4Y12 Item 42

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5 Collar DAN12-6Y Item 47

5 Nut ASNA2528-4 Item 51

5 Collar DAN12-8Y Item 54

5 Collar DAN12-8X Item 55

5 Collar DAN11-6X Item 56

5 Pin DAN7-8-12X Item 59

5 Pin DAN7-8-11Y Item 61

5 Pin DAN7-8-12Y Item 62

4 Pin DAN5-6-8X Item 82

5 Pin DAN7-8-10X Item 84

5 Pin DAN7-8-11X Item 85

4 Pin DAN7-6-9Y Item 114

2 Pin DAN7-6-10Y Item 115

4 Pin DAN7-8-17Y Item 116

2 Pin DAN7-6-11X Item 117

5 Pin DAN7-8-13X Item 118

5 Pin DAN7-8-15X Item 119

5 Pin DAN7-8-16X Item 120

2 Collar DAN12-6X Item 121

5 Bolt EN6115K4Y17 Item 122

5 Bolt EN6115K4Y19 Item 123

(11) Subtask 533160-400-202-001 - Oversize fasteners of kit 533160D02R01

Manpower Resources

Manhours 0.00

Minimum number of person 0

Subtask elapsed time 0.00

Skills NON SPECIFIC

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Material necessary to do the job

Kit 533160D02R05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

20 DAN5-6-4 2 PIN

28 DAN7-8-11 PIN

29 DAN7-10-11 5 PIN

30 DAN7-10-12 5 PIN

32 DAN5-6-7X 5 PIN

33 DAN5-6-10X 5 PIN

46 NSA5075-6 2 COLLAR

48 DAN12-8 2 COLLAR

49 DAN12-10 5 COLLAR

50 ASNA2528-3 5 NUT

51 ASNA2528-4 4 NUT

52 ASNA2528-5 NUT

53 NSA5330-6 5 COLLAR

54 DAN12-8Y 2 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

57 DAN5-6-7Y 4 PIN

62 DAN7-8-12Y 2 PIN

68 EN6115K5-10 5 BOLT

69 EN6115K5-11 5 BOLT

70 EN6115K5-12 5 BOLT

78 DAN5-6-3X 5 PIN

79 DAN5-6-4X 2 PIN

80 DAN5-6-5X 5 PIN

81 DAN5-6-6X 5 PIN

82 DAN5-6-8X 5 PIN

83 DAN7-8-9X 4 PIN

84 DAN7-8-10X 4 PIN

85 DAN7-8-11X 5 PIN

86 DAN7-10-11X 5 PIN

87 DAN7-10-12X 5 PIN

88 DAN7-10-17X 4 PIN

89 DAN5-6-10Y 4 PIN

90 DAN7-10-13 5 PIN

91 DAN7-10-15 5 PIN

92 DAN7-10-16 5 PIN

93 EN6115K5-7 5 BOLT

94 EN6115K5-8 BOLT

95 EN6115K5-15 2 BOLT

96 EN6115K5-16 2 BOLT

97 DAN12-10X 5 COLLAR

98 NSA5075-8 5 COLLAR

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

99 DAN5-8-7 2 PIN

100 DAN5-8-8 4 PIN

101 DAN7-10-10 5 PIN

102 EN6115K3X3 5 BOLT

103 EN6115K3X4 5 BOLT

104 EN6115K3X5 5 BOLT

105 EN6115K4-7 2 BOLT

106 EN6115K3X7 5 BOLT

107 EN6115K3X8 5 BOLT

108 EN6115K4-8 2 BOLT

109 EN6115K5X10 5 BOLT

110 EN6115K5X11 5 BOLT

111 EN6115K5X12 5 BOLT

112 EN6115K5X17 5 BOLT

113 EN6115K5X19 5 BOLT

References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

(a) If fasteners of Kit 533160D01R04 do not fit because oversize fasteners are

necessary, then refer to the fastener tables, as shown on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut

or collar which is part of kit Kit 533160D02R05 and listed below:

2 Pin DAN5-6-4 Item 20

2 Pin DAN7-8-11 Item 28

5 Pin DAN7-10-11 Item 29

5 Pin DAN7-10-12 Item 30

5 Pin DAN5-6-7X Item 32

5 Pin DAN5-6-10X Item 33

2 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

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SERVICE BULLETIN

5 Collar DAN12-10 Item 49

5 Nut ASNA2528-3 Item 50

4 Nut ASNA2528-4 Item 51

10 Nut ASNA2528-5 Item 52

5 Collar NSA5330-6 Item 53

2 Collar DAN12-8Y Item 54

5 Collar DAN12-8X Item 55

5 Collar DAN11-6X Item 56

4 Pin DAN5-6-7Y Item 57

2 Pin DAN7-8-12Y Item 62

5 Bolt EN6115K5-10 Item 68

5 Bolt EN6115K5-11 Item 69

5 Bolt EN6115K5-12 Item 70

5 Pin DAN5-6-3X Item 78

2 Pin DAN5-6-4X Item 79

5 Pin DAN5-6-5X Item 80

5 Pin DAN5-6-6X Item 81

5 Pin DAN5-6-8X Item 82

4 Pin DAN7-8-9X Item 83

4 Pin DAN7-8-10X Item 84

5 Pin DAN7-8-11X Item 85

5 Pin DAN7-10-11X Item 86

5 Pin DAN7-10-12X Item 87

4 Pin DAN7-10-17X Item 88

4 Pin DAN5-6-10Y Item 89

5 Pin DAN5-6-10Y Item 89

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5 Pin DAN7-10-13 Item 90

5 Pin DAN7-10-15 Item 91

5 Pin DAN7-10-16 Item 92

5 Bolt EN6115K5-7 Item 93

5 Bolt EN6115K5-8 Item 94

2 Bolt EN6115K5-15 Item 95

2 Bolt EN6115K5-16 Item 96

5 Collar DAN12-10X Item 97

5 Collar NSA5075-8 Item 98

2 Pin DAN5-8-7 Item 99

4 Pin DAN5-8-8 Item 100

5 Pin DAN7-10-10 Item 101

5 Bolt EN6115K3X3 Item 102

5 Bolt EN6115K3X4 Item 103

5 Bolt EN6115K3X5 Item 104

2 Bolt EN6115K4-7 Item 105

5 Bolt EN6115K3X7 Item 106

5 Bolt EN6115K3X8 Item 107

2 Bolt EN6115K4-8 Item 108

5 Bolt EN6115K5X10 Item 109

5 Bolt EN6115K5X11 Item 110

5 Bolt EN6115K5X12 Item 111

5 Bolt EN6115K5X17 Item 112

5 Bolt EN6115K5X19 Item 113

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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**CONF 002

(1) Subtask 533160-831-204-002 - Remove the fasteners in the upper fuselage shell

between FR80 and FR87.

Manpower Resources

Manhours 2.25

Minimum number of person 2

Subtask elapsed time 1.75

Skills AIRFRAME

References

Fig. A-GBAAB

Removal of Fastener from the upper

fuselage shell between FR80 and FR86

Sheet 01

Sheet 02

Sheet 03

Sheet 04

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) At FR80 between STGR2 LH/RH and STGR5 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View C:

6 pin DAN5-8-8 Item (39) Discard

6 collar NAS5075-8 Item (51) Discard

(b) At FR84 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View B :

12 pin DAN5-6-5 Item (36) Discard

8 pin DAN5-8-10 Item (40) Discard

2 pin DAN5-6-7 Item (37) Discard

8 pin DAN5-8-11 Item (41) Discard

52 pin DAN5-8-7 Item (38) Discard

4 rivet LN9198-4800CF Item (44) Discard

2 rivet LN9198-4000CF Item (43) Discard

14 collar NSA5075-6 Item (54) Discard

68 collar NSA5075-8 Item (51) Discard

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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1 angle A53985256206 Item (130) Retain

2 angle F53577990000 Item (131) Retain

(c) At FR85 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown on Fig. AGBAAB Sheet 01 and Fig. A-GBAAB Sheet 02, View B :

4 pin DAN5-8-10 Item (40) Discard

4 pin DAN5-8-11 Item (41) Discard

4 pin DAN5-8-7 Item (38) Discard

12 collar NSA5075-8 Item (51) Discard

(d) At FR86 at STGR3 LH/RH and at STGR6 LH/RH remove, as shown Fig. A-GBAAB

Sheet 01 and Fig. A-GBAAB Sheet 02, View B :

18 pin DAN5-6-5 Item (36) Discard

12 pin DAN5-8-11 Item (41) Discard

8 pin DAN5-8-14 Item (42) Discard

82 pin DAN5-8-7 Item (38) Discard

4 pin DAN5-8-10 Item (40) Discard

4 rivet LN9198-4800CF Item (44) Discard

2 rivet LN9198-4000CF Item (43) Discard

18 collar NSA5075-6 Item (54) Discard

106 collar NSA5075-8 Item (51) Discard

2 angle F53577990000 Item (131) Retain

1 angle A53985256206 Item (132) Discard

(2) Subtask 533160-831-205-002 - Do the Eddy Current Rotating Probe Testing of

FR80, FR84 and FR86 to find cracks around the holes of the previous removed

fasteners.

Manpower Resources

Manhours 3.00

Minimum number of person 3

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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References

Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 , Procedure A

Fig. A-GBDAA

Inspection Areas of Fastener Hole

Rototest and for HFEC Inspection

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Do the Eddy Current Rotating Probe Testing as shown on Fig. A-GBDAA Sheet 01,

Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig. A-GBDAA Sheet 04 and

Fig. A-GBDAA Sheet 05.(Refer to NTM 51-10-01, Page Block 601 , Procedure A).

NOTE: Check only the fastener holes for the fasteners which have been

removed to accomplish this modification

1 In case of no crack finding, continue with the accomplishment of the

modification.

2 In case of crack finding, contact AIRBUS for repair.

(3) Subtask 533160-831-206-002 - Do the eddy current high frequency inspection of

FR84 and FR86 to find cracks between the fastener rows.

Manpower Resources

Manhours 2.50

Minimum number of person 2

Subtask elapsed time 1.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-08, Page Block 601

Fig. A-GBDAA

Inspection Areas of Fastener Hole

Rototest and for HFEC Inspection

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(a) Do a eddy current high frequency inspection from the fuselage outside, as shown

on Fig. A-GBDAA Sheet 01, Fig. A-GBDAA Sheet 02, Fig. A-GBDAA Sheet 03, Fig.

A-GBDAA Sheet 04 and Fig. A-GBDAA Sheet 05 (Refer to NTM 51-10-08, Page

Block 601).

1 In case of no crack finding, continue with the accomplishment of the

modification.

2 In case of crack finding, contact AIRBUS for repair.

(4) Subtask 533160-831-207-002 - Do a check of the fastener position to make sure

that the edge clearance of all existing fastener holes is correct.

Manpower Resources

Manhours 1.50

Minimum number of person 2

Subtask elapsed time 0.75

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-47-00

Fig. A-GBAAB

Removal of Fastener from the upper

fuselage shell between FR80 and FR86

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBEAA

Flow Chart of Fastener Installation

Process and Example of Fastener Hole

Reworking

Sheet 01

Sheet 02

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

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(a) Check the edge clearance of all existing fastener holes from the outside and from

the inside of the fuselage shell, as shown on Fig. A-GBAAB Sheet 01, Fig. AGBAAB Sheet 02 and Fig. A-GBAAB Sheet 04. If the edge clearance is very close

for the current fasteners, try to rework the fastener holes to keep the minimum

distance to the structure edge after re-drilling to the final fastener hole diameter as

shown on Fig. A-GBEAA Sheet 01 and Fig. A-GBEAA Sheet 02. For the correct

edge clearance, refer to SRM 51-47-00. Only in the case that the fastener hole can

not be moved to keep the correct edge clearance, an undersize fastener of Kit

533160D06R01 should be installed, as shown on Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10.

NOTE: In accordance with SRM 51-47-00, Edge Distance for Milling Steps,

the additional distance of 1.0 mm (0.039 in) to the edge margin for

higher milling steps than 1.0 mm is not applicable for these fastener

holes.

NOTE: The installation of undersize fastener is limited by five fastener per

reinforcement bracket with a maximum of two fastener adjacent to

each other.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

(5) Subtask 533160-831-208-002 - Install 6 fasteners with cold working in the upper

fuselage shell at FR80 between STGR2A LH/RH and STGR5A LH/RH.

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Kit 533160D04R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

39 EN6115K4Y8 6 BOLT

51 ASNA2528-4 6 NUT

Kit 533160D05R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 ASNA2528-5 6 NUT

94 EN6115K5-8 6 BOLT

References

Structural Repair Manual (SRM) 51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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References

Fig. A-GBBAB

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page Block 001 and Fig. AGBCAA Sheet 06.

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

07.

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

Sheet 07.

(d) Expand the fastener holes, refer to SRM 51-48-00, Page Block 001).

(e) Ream the fastener holes with the correct gage finish reamer, as shown on Fig. AGBCAA Sheet 07.

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin

with the associated nut or collar which is part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

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533160-400-202 002 Oversize fasteners of kit 533160D05R01 .

(f) At the FR80 in the upper fuselage install as shown on Fig. A-GBBAB Sheet 01 and

Fig. A-GBBAB Sheet 02, View C and Fig. A-GBCAA Sheet 07:

6 Bolt EN6115K4Y8 Item 39

6 Nut ASNA2528-4 Item 51

or next oversize (part of Kit 533160D05R01)

6 Bolt EN6115K5-8 Item 94

6 Nut ASNA2528-5 Item 52

(6) Subtask 533160-831-209-002 - Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR86.

Manpower Resources

Manhours 38.00

Minimum number of person 3

Subtask elapsed time 12.50

Skills AIRFRAME

Material necessary to do the job

Kit 533160D04R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 F5357716920000 1 DOUBLER

2 F5357716920100 1 DOUBLER

3 F5357716920400 1 DOUBLER

4 F5357716920500 1 DOUBLER

5 F5357798920400 1 SHIM

6 F5357798920500 1 SHIM

7 F5357798920600 1 SHIM

8 F5357798920700 1 SHIM

9 A5398525620600 1 ANGLE

18 DAN5-5-4 2 PIN

19 DAN5-6-3 12 PIN

20 DAN5-6-4 6 PIN

21 DAN5-6-5 12 PIN

22 DAN5-6-6 22 PIN

24 DAN5-6-8 10 PIN

26 DAN7-8-9 8 PIN

27 DAN7-8-10 4 PIN

28 DAN7-8-11 8 PIN

29 DAN7-10-11 8 PIN

30 DAN7-10-12 6 PIN

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

31 DAN7-10-17 4 PIN

38 EN6115K4Y7 16 BOLT

40 EN6115K4Y10 4 BOLT

41 EN6115K4Y11 4 BOLT

42 EN6115K4Y12 14 BOLT

45 NSA5075-5 2 COLLAR

46 NSA5075-6 62 COLLAR

48 DAN12-8 18 COLLAR

49 DAN12-10 18 COLLAR

50 ASNA2528-3 32 NUT

51 ASNA2528-4 38 NUT

52 ASNA2528-5 40 NUT

53 NSA5330-6 6 COLLAR

54 DAN12-8Y 10 COLLAR

57 DAN5-6-7Y 2 PIN

58 DAN5-6-8Y 4 PIN

60 DAN7-8-10Y 4 PIN

61 DAN7-8-11Y 4 PIN

62 DAN7-8-12Y 2 PIN

63 EN6115K3-3 12 BOLT

64 EN6115K3-4 10 BOLT

65 EN6115K3-5 10 BOLT

68 EN6115K5-10 8 BOLT

69 EN6115K5-11 8 BOLT

70 EN6115K5-12 8 BOLT

71 EN6115K5-17 8 BOLT

72 EN6115K5-19 8 BOLT

75 EN6080D5-06 1 RIVET

76 LN9198-4812CF 2 RIVET

77 EN6081D6-08 2 RIVET

124 EN6115K3A7 2 BOLT

126 ASNA2528-3A 2 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801

Elec. Std. Practices Manual (ESPM) 20-51-20

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References

Structural Repair Manual (SRM) 51-47-00

51-48-00

51-48-00, Page Block 001

Fig. A-GBBAB

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 5 and the doubler, item 1 to the fuselage structure.

2 Countersink (100 DEG) the rivet hole, previously used to fit the angle, item

(132), as shown on Fig. A-GBBAB Sheet 03.

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3 Close one rivet hole, previously used to fit the angle, item (132), as shown on

Fig. A-GBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet

06 with

1 Rivet EN6080D5-06 Item 75

NOTE: Install the rivet, item 75, with 09-005 sealant.

4 Put the shim, item 5 and the doubler, item 1 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 03.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

5 Transfer drill the pilot holes from the shim, item 5 and from the doubler, item 1

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

6 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 1 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

7 Mark the fastener holes with a soft felt pen which have to be expand by cold

working, as shown on Fig. A-GBBAB Sheet 04.

8 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

9 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

10 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

11 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

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12 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

13 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thruFig. A-GBCAA Sheet 10.

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

15 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thruFig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

16 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

17 Remove the angle, item 9, from the fuselage skin.

18 Remove the doubler, item 1 and the shim, item 5 from the fuselage structure.

19 Deburr the fastener holes.

20 Clean the shim, item 5, the doubler, item 1 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

21

sealant 09-005 As required

1 Doubler F5357716920000 Item 1

1 Shim F5357798920400 Item 5

with:

sealant 09-005 As required

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22 Put in position, with

sealant 09-005 As required

and secure with screw pins, as shown on Fig. A-GBBAB Sheet 03:

1 Angle A5398525620600 Item 9

23 To the fuselage skin, the doubler, item 1 and the shim, item 5, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 04 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

2 Pin DAN5-5-4 Item 18

1 Pin DAN5-6-3 Item 19

2 Pin DAN5-6-4 Item 20

2 Pin DAN5-6-5 Item 21

4 Pin DAN5-6-6 Item 22

2 Pin DAN5-6-8 Item 24

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

02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

2 Pin DAN7-8-11 Item 28

2 Pin DAN7-8-11 Item 28

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

03.

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4 Pin DAN7-10-11 Item 29

3 Pin DAN7-10-12 Item 30

2 Pin DAN7-10-17 Item 31

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

05.

1 Pin DAN5-6-7Y Item 57

2 Pin DAN5-6-8Y Item 58

2 Pin DAN7-8-10Y Item 60

2 Pin DAN7-8-11Y Item 61

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

06.

1 Pin DAN7-8-12Y Item 62

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

07.

3 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Bolt EN6115K4Y12 Item 42

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

08.

2 Bolt EN6115K3-3 Item 63

2 Bolt EN6115K3-4 Item 64

2 Bolt EN6115K3-5 Item 65

1 Bolt EN6115K3A7 Item 124

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

09.

4 Bolt EN6115K5-17 Item 71

with

4 Nut ASNA2528-5 Item 52

13 Nut ASNA2528-4 Item 51

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6 Nut ASNA2528-3 Item 50

5 Collar DAN12-8Y Item 54

11 Collar NSA5075-6 Item 46

3 Collar NSA5330-6 Item 53

2 Collar NSA5075-5 Item 45

4 Collar DAN12-8 Item 48

9 Collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

24 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the reinforcement doublers and shims with cold working at FR86 at STGR2B

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 6 and the doubler, item 2 to the fuselage structure.

2 Put the shim, item 6 and the doubler, item 2 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 05.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 6 and from the doubler, item 2

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 2 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

5 Mark the fastener holes with a soft felt pen which have to be expand by cold

working, as shown on Fig. A-GBBAB Sheet 06.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10.

14 Remove the doubler, item 2 and the shim, item 6 from the fuselage structure.

15 Deburr the fastener holes.

16 Clean the shim, item 6, the doubler, item 2 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 05:

1 Doubler F5357716920100 Item 2

1 Shim F5357798920500 Item 6

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 2 and the shim, item 6, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 06 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

3 Pin DAN5-6-3 Item 19

2 Pin DAN5-6-4 Item 20

2 Pin DAN5-6-5 Item 21

4 Pin DAN5-6-6 Item 22

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

2 Pin DAN5-6-8 Item 24

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

02.

1 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

2 Pin DAN7-8-11 Item 28

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

03.

4 Pin DAN7-10-11 Item 29

3 Pin DAN7-10-12 Item 30

2 Pin DAN7-10-17 Item 31

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

05.

1 Pin DAN5-6-7Y Item 57

2 Pin DAN5-6-8Y Item 58

2 Pin DAN7-8-10Y Item 60

2 Pin DAN7-8-11Y Item 61

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

06.

1 Pin DAN7-8-12Y Item 62

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

07.

3 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Bolt EN6115K4Y12 Item 42

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

08.

2 Bolt EN6115K3-3 Item 63

2 Bolt EN6115K3-4 Item 64

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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2 Bolt EN6115K3-5 Item 65

1 Bolt EN6115K3A7 Item 124

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

09.

4 Bolt EN6115K5-17 Item 71

with

4 Nut ASNA2528-5 Item 52

13 Nut ASNA2528-4 Item 51

6 Nut ASNA2528-3 Item 50

5 Collar DAN12-8Y Item 54

13 Collar NSA5075-6 Item 46

3 Collar NSA5330-6 Item 53

4 Collar DAN12-8 Item 48

9 Collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

19 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(c) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 7 and the doubler, item 3 to the fuselage structure.

2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAB

Sheet 07, View J.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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3 Drill with a 4.8 mm (0.19 in.) DIA drill the new hole with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole.

5 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

6 Install to the mating surfaces install, as shown on Fig. A-GBBAB Sheet 07,

Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 06:

1 angle F53577990000 Item (131)

1 Rivet LN9198-4812CF Item 76

1 Rivet EN6081D6-08 Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131), as electrical bonding point, refer to

ESPM 20-51-20 refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 7 and the doubler, item 3 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 07.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Transfer drill the pilot holes from the shim, item 7 and from the doubler, item 3

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 3 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 08.

11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 107

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12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002 to define the correct fastener dimension, refer to

SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to

maximum of 16 mm (0.63 in) on the doubler, item 3 located at FR86, as

shown on Fig. A-GBBAB Sheet 08.

20 Remove the doubler, item 3 and the shim, item 7 from the fuselage structure.

21 Deburr the fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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22 Clean the shim, item 7, the doubler, item 3 and the fuselage structure with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins, as shown on Fig. A-GBBAB Sheet 07:

1 Doubler F5357716920400 Item 3

1 Shim F5357798920600 Item 7

with:

sealant 09-005 As required

24 To the fuselage skin, the doubler, item 3 and the shim, item 7, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

4 Pin DAN5-6-3 Item 19

1 Pin DAN5-6-4 Item 20

4 Pin DAN5-6-5 Item 21

7 Pin DAN5-6-6 Item 22

3 Pin DAN5-6-8 Item 24

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

02.

3 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 109

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SERVICE BULLETIN

1 Pin DAN7-8-11 Item 28

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

07.

5 Bolt EN6115K4Y7 Item 38

1 Bolt EN6115K4Y12 Item 42

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

08.

4 Bolt EN6115K3-3 Item 63

3 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

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

09.

4 Bolt EN6115K5-10 Item 68

4 Bolt EN6115K5-11 Item 69

4 Bolt EN6115K5-12 Item 70

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

10.

4 Bolt EN6115K5-19 Item 72

with

19 Collar NSA5075-6 Item 46

5 Collar DAN12-8 Item 48

10 Nut ASNA2528-3 Item 50

6 Nut ASNA2528-4 Item 51

16 Nut ASNA2528-5 Item 52

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 110

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(d) Install the reinforcement doublers and shims with cold working at FR86 at STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 8 and the doubler, item 4 to the fuselage structure.

2 Mark the new hole for the angle, item (131), as shown on Fig. A-GBBAB

Sheet 07, View J.

3 Drill with a 4.8 (0.19 in.) mm DIA drill the new hole with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet hole.

5 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

6 Install to the mating surfaces, as shown on Fig. A-GBBAB Sheet 07, Fig. AGBBAB Sheet 08 and Fig. A-GBCAA Sheet 06:

1 angle F53577990000 Item (131)

1 Rivet LN9198-4812CF Item 76

1 Rivet EN6081D6-08 Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131) as electrical bonding point, refer to

ESPM 20-51-20 refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 8 and the doubler, item 4 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 07.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Transfer drill the pilot holes from the shim, item 8 and from the doubler, item 4

to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 111

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9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 4 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 08.

11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in) to

maximum of 16 mm (0.63 in) on the doubler, item 4 located at FR86, as

shown on Fig. A-GBBAB Sheet 08.

20 Remove the shim, item 8 and the doubler, item 4 from the fuselage structure.

21 Deburr the fastener holes.

22 Clean the shim, item 8, the doubler, item 4 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins , as shown on Fig. A-GBBAB Sheet 07:

1 Doubler F5357716920500 Item 4

1 Shim F5357798920700 Item 8

with:

sealant 09-005 As required

24 To the fuselage skin, the doubler, item 4 and the shim, item 8, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 08 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

4 Pin DAN5-6-3 Item 19

1 Pin DAN5-6-4 Item 20

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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4 Pin DAN5-6-5 Item 21

7 Pin DAN5-6-6 Item 22

3 Pin DAN5-6-8 Item 24

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

02.

3 Pin DAN7-8-9 Item 26

1 Pin DAN7-8-10 Item 27

1 Pin DAN7-8-11 Item 28

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

07.

5 Bolt EN6115K4Y7 Item 38

1 Bolt EN6115K4Y12 Item 42

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

08.

4 Bolt EN6115K3-3 Item 63

3 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

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

09.

4 Bolt EN6115K5-10 Item 68

4 Bolt EN6115K5-11 Item 69

4 Bolt EN6115K5-12 Item 70

NOTE: For the following fasteners, as shown onFig. A-GBCAA Sheet

10.

4 Bolt EN6115K5-19 Item 72

with

19 Collar NSA5075-6 Item 46

5 Collar DAN12-8 Item 48

10 Nut ASNA2528-3 Item 50

6 Nut ASNA2528-4 Item 51

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

16 Nut ASNA2528-5 Item 52

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(7) Subtask 533160-831-210-002 - Install reinforcement doublers and shims with cold

working on the upper fuselage shell at FR84.

Manpower Resources

Manhours 33.00

Minimum number of person 3

Subtask elapsed time 10.50

Skills AIRFRAME

Material necessary to do the job

Kit 533160D04R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 F5357716921800 1 DOUBLER

11 F5357716921900 1 DOUBLER

12 F5357716922100 1 DOUBLER

13 F5357716922000 1 DOUBLER

14 F5357798921200 1 SHIM

15 F5357798921400 1 SHIM

16 F5357798921700 1 SHIM

17 F5357798921600 1 SHIM

23 DAN5-6-7 8 PIN

24 DAN5-6-8 6 PIN

25 DAN5-6-10 8 PIN

28 DAN7-8-11 6 PIN

32 DAN5-6-7X 4 PIN

33 DAN5-6-10X 4 PIN

34 DAN7-6-11Y 2 PIN

35 DAN7-8-13Y 6 PIN

36 DAN7-8-15Y 6 PIN

37 DAN7-8-16Y 6 PIN

43 EN6115K4Y15 2 BOLT

44 EN6115K4Y16 2 BOLT

46 NSA5075-6 22 COLLAR

47 DAN12-6Y 2 COLLAR

48 DAN12-8 6 COLLAR

50 ASNA2528-3 34 NUT

51 ASNA2528-4 4 NUT

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

54 DAN12-8Y 62 COLLAR

55 DAN12-8X 2 COLLAR

56 DAN11-6X 8 COLLAR

59 DAN7-8-12X 2 PIN

60 DAN7-8-10Y 16 PIN

61 DAN7-8-11Y 16 PIN

62 DAN7-8-12Y 12 PIN

64 EN6115K3-4 4 BOLT

65 EN6115K3-5 12 BOLT

66 EN6115K3-7 10 BOLT

67 EN6115K3-8 8 BOLT

73 LN9198-4012CF 1 RIVET

74 LN9198-4014CF 1 RIVET

77 EN6081D6-08 4 RIVET

125 EN6115K3A8 2 BOLT

126 ASNA2528-3A 2 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) Task 20-28-00-912-801

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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References

Fig. A-GBBAB

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 10 and the doubler, item 14 to the fuselage structure.

2 Mark the new holes for the angles, item (130) and (131), as shown on Fig. AGBBAB Sheet 09, View N.

3 Drill with a 4.1 mm (0.16 in.) DIA drill the new holes with the angle, item (130).

4 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131).

5 Remove the angles, item (130) and (131) from the fuselage skin and deburr

the rivet holes.

6 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

7 Install to the mating surfaces install, as shown on Fig. A-GBBAB Sheet 09,

Fig. A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 06:

1 angle A5398525620600 Item (130)

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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1 angle F5357799000000 Item (131)

1 Rivet LN9198-4012CF Item 73

1 Rivet LN9198-4014CF Item 74

2 Rivet EN6081D6-08 Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131), as bonding point, refer to ESPM

20-51-20 refer to AMM Task 20-28-00-912-801.

8 Put the shim, item 14 and the doubler, item 10 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 09.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the pilot holes from the shim, item 14 and from the doubler, item

10 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

10 Transfer drill the fastener holes from the fuselage structure to the doubler, 10

using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

11 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 10.

12 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

13 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

14 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

16 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

17 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

18 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

19 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

20 Remove the doubler, item 10 and the shim, item 14 from the fuselage

structure.

21 Deburr the fastener holes.

22 Clean the shim, item 14, the doubler, item 10 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

23 Install with screw pins, as shown on Fig. A-GBBAB Sheet 09:

1 Doubler F5357716921800 Item 10

1 Shim F5357798921200 Item 14

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with:

sealant 09-005 As required

24 To the fuselage skin, the doubler, item 10 and the shim, item 14, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 10 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

1 Pin DAN5-6-7 Item 23

2 Pin DAN5-6-8 Item 24

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

02.

2 Pin DAN5-6-10 Item 25

1 Pin DAN7-8-11 Item 28

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

03.

2 Pin DAN5-6-7X Item 32

1 Pin DAN5-6-10X Item 33

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

04.

1 Pin DAN7-6-11Y Item 34

3 Pin DAN7-8-15Y Item 36

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

05.

4 Pin DAN7-8-10Y Item 60

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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4 Pin DAN7-8-11Y Item 61

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

06.

5 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y15 Item 43

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

3 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

with

5 Collar NSA5075-6 Item 46

1 Collar DAN12-6Y Item 47

1 Collar DAN12-8 Item 48

9 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

16 Collar DAN12-8Y Item 54

3 Collar DAN11-6X Item 56

25 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the reinforcement doublers and shims with cold working at FR84 at STGR2A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 11 and the doubler, item 15 to the fuselage structure.

2 Mark the new holes for the angle, item (131), as shown on Fig. A-GBBAB

Sheet 11, View R.

3 Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item (131).

4 Remove the angle, item (131) from the fuselage skin and deburr the rivet

holes.

5 Remove the surface protection around the rivet holes of the angle, item (131),

for electrical bonding.

6 Install to the mating surfaces, as shown on Fig. A-GBBAB Sheet 11, Fig. AGBBAB Sheet 12 and Fig. A-GBCAA Sheet 06:

1 angle F5357799000000 Item (131)

2 Rivet EN6081D6-08 Item 77

with:

sealant 09-005 As required

NOTE: Install the angle, item (131), as electrical bonding point, refer

to ESPM 20-51-20 refer to AMM Task 20-28-00-912-801.

7 Put the shim, item 15 and the doubler, item 11 in the final position on the

fuselage structure as shown on Fig. A-GBBAB Sheet 11.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Transfer drill the pilot holes from the shim, item 15 and from the doubler, item

11 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

9 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 11 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

10 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 12.

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11 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

12 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

14 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

15 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

16 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

17 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

18 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

19 Remove the doubler, item 11 and the shim, item 15 from the fuselage

structure.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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20 Deburr the fastener holes.

21 Clean the shim, item 15, the doubler, item 11 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

22 Install with screw pins, as shown on Fig. A-GBBAB Sheet 11:

1 Doubler F5357716921900 Item 11

1 Shim F5357798921400 Item 15

with:

sealant 09-005 As required

23 To the fuselage skin, the doubler, item 11 and the shim, item 15, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 12 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

1 Pin DAN5-6-7 Item 23

2 Pin DAN5-6-8 Item 24

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

02.

2 Pin DAN5-6-10 Item 25

1 Pin DAN7-8-11 Item 28

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

03.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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2 Pin DAN5-6-7X Item 32

1 Pin DAN5-6-10X Item 33

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

04.

1 Pin DAN7-6-11Y Item 34

3 Pin DAN7-8-15Y Item 36

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

05.

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

5 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y15 Item 43

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

3 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

with

5 Collar NSA5075-6 Item 46

1 Collar DAN12-6Y Item 47

1 Collar DAN12-8 Item 48

9 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

16 Collar DAN12-8Y Item 54

3 Collar DAN11-6X Item 56

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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24 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(c) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A

L/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 17 and the doubler, item 13 to the fuselage structure.

2 Put the shim, item 17 and the doubler, item 13 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 13.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 17 and from the doubler, item

13 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 13 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

5 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 14.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes as described in

Subtask 533160-831-207-002, to define the correct fastener dimension, refer

to SRM 51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 533160D04R01, use a smaller fastener (part of

Kit 533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

06.

14 Remove the doubler, item 13 and the shim, item 17 from the fuselage

structure.

15 Deburr the fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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16 Clean the shim, item 17, the doubler, item 13 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 13:

1 Doubler F5357716922000 Item 13

1 Shim F5357798921600 Item 17

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 13 and the shim, item 17, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

1 Pin DAN5-6-8 Item 24

3 Pin DAN5-6-7 Item 23

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

02.

2 Pin DAN5-6-10 Item 25

2 Pin DAN7-8-11 Item 28

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

03.

1 Pin DAN5-6-10X Item 33

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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

04.

3 Pin DAN7-8-16Y Item 37

3 Pin DAN7-8-13Y Item 35

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

05.

1 Pin DAN7-8-12X Item 59

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

1 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y16 Item 44

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

2 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

1 Bolt EN6115K3A8 Item 125

with

6 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

8 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

15 Collar DAN12-8Y Item 54

1 Collar DAN12-8X Item 55

1 Collar DAN11-6X Item 56

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 129

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SERVICE BULLETIN

1 nut ASNA2528-3A Item 126

19 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(d) Install the reinforcement doublers and shims with cold working at FR84 at STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

and remove parts of sealant from the structure corners to get a perfect fit of

the shim, item 12 and the doubler, item 16 to the fuselage structure.

2 Put the shim, item 12 and the doubler, item 16 in the final position on the

fuselage structure, as shown on Fig. A-GBBAB Sheet 13.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Transfer drill the pilot holes from the shim, item 16 and from the doubler, item

12 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

4 Transfer drill the fastener holes from the fuselage structure to the doubler,

item 12 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

5 Mark the fastener holes which have to be expand by cold working with a soft

felt pen, as shown on Fig. A-GBBAB Sheet 14.

6 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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7 Check the edge clearance of the fastener holes as described in Subtask

533160-831-207-002, to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 533160D04R01, use a smaller fastener (part of Kit

533160D06R01) as given in the fastener table, as shown on Fig. A-GBCAA

Sheet 01 thru Fig. A-GBCAA Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

8 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

9 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

10 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

11 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

12 Check the edge clearance of the unmarked fastener holes and define the

correct fastener dimension, refer to SRM 51-47-00. If the minimum edge

clearance is not given to the standard fastener installation (part of Kit

533160D04R01, use a smaller fastener (part of Kit 533160D06R01) as given

in the fastener table, as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA

Sheet 10.

NOTE: For information of undersize fasteners, refer to SUBTASK

533160-400-201 002 Installation of undersize fasteners of kit

533160D06R01 .

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

13 Drill the unmarked fastener holes to the correct dimension, as shown on Fig.

A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

05.

14 Remove the doubler, item 12 and the shim, item 16 from the fuselage

structure.

15 Deburr the fastener holes.

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16 Clean the shim, item 16, the doubler, item 12 and the fuselage structure with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

17 Install with screw pins, as shown on Fig. A-GBBAB Sheet 13:

1 Doubler F5357716922100 Item 12

1 Shim F5357798921700 Item 16

with:

sealant 09-005 As required

18 To the fuselage skin, the doubler, item 12 and the shim, item 16, install with

sealant 09-005 As required

as shown on Fig. A-GBBAB Sheet 14 and Fig. A-GBCAA Sheet 01 thru Fig.

A-GBCAA Sheet 10:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 533160D05R01.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

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

01.

1 Pin DAN5-6-8 Item 24

3 Pin DAN5-6-7 Item 23

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

02.

2 Pin DAN5-6-10 Item 25

2 Pin DAN7-8-11 Item 28

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

03.

1 Pin DAN5-6-10X Item 33

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

04.

3 Pin DAN7-8-16Y Item 37

3 Pin DAN7-8-13Y Item 35

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

05.

1 Pin DAN7-8-12X Item 59

4 Pin DAN7-8-10Y Item 60

4 Pin DAN7-8-11Y Item 61

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

06.

1 Pin DAN7-8-12Y Item 62

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

07.

1 Bolt EN6115K4Y16 Item 44

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

08.

1 Bolt EN6115K3-4 Item 64

3 Bolt EN6115K3-5 Item 65

2 Bolt EN6115K3-7 Item 66

2 Bolt EN6115K3-8 Item 67

1 Bolt EN6115K3A8 Item 125

with

6 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

8 Nut ASNA2528-3 Item 50

1 Nut ASNA2528-4 Item 51

15 Collar DAN12-8Y Item 54

1 Collar DAN12-8X Item 55

1 Collar DAN11-6X Item 56

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

1 nut ASNA2528-3A Item 126

19 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(8) Subtask 533160-831-211-002 - Install fasteners with cold working in the upper

fuselage skin at FR85

Manpower Resources

Manhours 2.25

Minimum number of person 2

Subtask elapsed time 1.25

Skills AIRFRAME

Material necessary to do the job

Kit 533160D04R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

38 EN6115K4Y7 4 BOLT

40 EN6115K4Y10 4 BOLT

41 EN6115K4Y11 4 BOLT

51 ASNA2528-4 12 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-005 As required

cleaning agent 11-026 As required

lint-free cloth 19-003 As required

References

Elec. Std. Practices Manual (ESPM) 20-51-20

Structural Repair Manual (SRM) 51-47-00

51-48-00, Page Block 001

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Fig. A-GBBAB

Installation of Reinforcement Brackets

and new Fastener with Cold Working

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

Sheet 11

Sheet 12

Sheet 13

Sheet 14

Sheet 15

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

(a) Install the fasteners with cold working at FR85 between STGR2B L/H and STGR5A

L/H.

1 Clean the working area with:

cleaning agent 11-026 As required

2 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

4 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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5 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

6 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

7 Deburr the fastener holes.

8 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

9 Install the fastener with

sealant 09-005 As required

, as shown on Fig. A-GBBAB Sheet 15 and Fig. A-GBCAA Sheet 07:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

2 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Nut ASNA2528-4 Item 51

10 Clean the repair area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(b) Install the fasteners with cold working at FR85 between STGR2B R/H and STGR5A

R/H.

1 Clean the working area with

cleaning agent 11-026 As required

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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2 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00 Page Block 001 for cold

working and as shown on Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet

10 for all fastener holes.

CAUTION: MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

3 Drill the marked fastener holes for cold working with the correct start drill, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

4 Ream the marked fastener holes for cold working with the correct start

reamer, as shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

5 Expand the marked fastener holes in accordance with the SRM 51-48-00

Page Block 001.

6 Ream the marked fastener holes with the correct gage finish reamer, as

shown on Fig. A-GBCAA Sheet 07 thru Fig. A-GBCAA Sheet 10.

7 Deburr the fastener holes.

8 Clean the repair area with:

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

9 Install the fastener with

sealant 09-005 As required

, as shown on Fig. A-GBBAB Sheet 15 and Fig. A-GBCAA Sheet 07:

NOTE: If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables, as shown on Fig. AGBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10 to find the

correct bolt or pin with the associated nut or collar.

NOTE: For information of oversize fasteners refer to SUBTASK

533160-400-202 002 Oversize fasteners of kit 533160D05R01

.

2 Bolt EN6115K4Y7 Item 38

2 Bolt EN6115K4Y10 Item 40

2 Bolt EN6115K4Y11 Item 41

6 Nut ASNA2528-4 Item 51

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10 Clean the repair area with

cleaning agent 11-026 As required

and

lint-free cloth 19-003 As required

(9) Subtask 533160-831-212-002 - Apply surface protection to the modification area.

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-013 As required

sealant 09-016 As required

corrosion preventive 15-005 As required

polyurethane primer 16-001 As required

polyurethane top coat 16-018 As required

wash primer 16-020 As required

CAUTION: MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION

AREA.

Apply surface protection to the modification area.

(a) Apply

sealant 09-013 As required

or

sealant 09-016 As required

to form a bead around the new doubler and reinstalled angles.

(b) Apply

wash primer 16-020 As required

to all reworked edges and heads of fasteners.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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(c) Apply

polyurethane primer 16-001 As required

to all reworked edges and heads of fasteners.

(d) Apply

polyurethane top

coat

16-018 As required

to all reworked edges and heads of fasteners.

(e) Apply

corrosion preventive 15-005 As required

to the modification area inside the fuselage.

(10) Subtask 533160-400-201-002 - Installation of undersize fasteners of kit

533160D06R01

Manpower Resources

Manhours 0.00

Minimum number of person 0

Subtask elapsed time 0.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533160D06R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

32 DAN5-6-7X 2 PIN

34 DAN7-6-11Y 5 PIN

40 EN6115K4Y10 5 BOLT

41 EN6115K4Y11 5 BOLT

42 EN6115K4Y12 5 BOLT

47 DAN12-6Y 5 COLLAR

51 ASNA2528-4 5 NUT

54 DAN12-8Y 5 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 4 COLLAR

59 DAN7-8-12X 5 PIN

61 DAN7-8-11Y 5 PIN

62 DAN7-8-12Y 5 PIN

82 DAN5-6-8X 4 PIN

84 DAN7-8-10X 5 PIN

85 DAN7-8-11X 5 PIN

114 DAN7-6-9Y 5 PIN

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

115 DAN7-6-10Y 2 PIN

116 DAN7-8-17Y 4 PIN

117 DAN7-6-11X 2 PIN

118 DAN7-8-13X 5 PIN

119 DAN7-8-15X 5 PIN

120 DAN7-8-16X 5 PIN

121 DAN12-6X 2 COLLAR

122 EN6115K4Y17 5 BOLT

123 EN6115K4Y19 5 BOLT

References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

(a) The subsequent undersize fasteners are parts of Kit 533160D06R01.

NOTE: Depending of the edge margin measurement requested with

subtask 533160-831-207-002 undersize fasteners can be installed.

Refer to Fig. A-GBCAA Sheet 01 thru Fig. A-GBCAA Sheet 10

NOTE: The installation of undersize fasteners is limited by five fasteners

per reinforcement bracket with a maximum of two fasteners

adjacent to each other.

If it is not the case, contact AIRBUS.

2 Pin DAN5-6-7X Item 32

5 Pin DAN7-6-11Y Item 34

5 Bolt EN6115K4Y10 Item 40

5 Bolt EN6115K4Y11 Item 41

5 Bolt EN6115K4Y12 Item 42

5 Collar DAN12-6Y Item 47

5 Nut ASNA2528-4 Item 51

5 Collar DAN12-8Y Item 54

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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5 Collar DAN12-8X Item 55

4 Collar DAN11-6X Item 56

5 Pin DAN7-8-12X Item 59

5 Pin DAN7-8-11Y Item 61

5 Pin DAN7-8-12Y Item 62

4 Pin DAN5-6-8X Item 82

5 Pin DAN7-8-10X Item 84

5 Pin DAN7-8-11X Item 85

5 Pin DAN7-6-9Y Item 114

2 Pin DAN7-6-10Y Item 115

4 Pin DAN7-8-17Y Item 116

2 Pin DAN7-6-11X Item 117

5 Pin DAN7-8-13X Item 118

5 Pin DAN7-8-15X Item 119

5 Pin DAN7-8-16X Item 120

2 Collar DAN12-6X Item 121

5 Bolt EN6115K4Y17 Item 122

5 Bolt EN6115K4Y19 Item 123

(11) Subtask 533160-400-202-002 - Oversize fasteners of kit 533160D05R01

Manpower Resources

Manhours 0.00

Minimum number of person 0

Subtask elapsed time 0.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533160D05R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

20 DAN5-6-4 2 PIN

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

28 DAN7-8-11 2 PIN

29 DAN7-10-11 5 PIN

30 DAN7-10-12 5 PIN

32 DAN5-6-7X 5 PIN

33 DAN5-6-10X 5 PIN

46 NSA5075-6 2 COLLAR

48 DAN12-8 2 COLLAR

49 DAN12-10 5 COLLAR

50 ASNA2528-3 5 NUT

51 ASNA2528-4 4 NUT

52 ASNA2528-5 4 NUT

53 NSA5330-6 5 COLLAR

54 DAN12-8Y 2 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

57 DAN5-6-7Y 4 PIN

62 DAN7-8-12Y 2 PIN

68 EN6115K5-10 5 BOLT

69 EN6115K5-11 5 BOLT

70 EN6115K5-12 5 BOLT

78 DAN5-6-3X 5 PIN

79 DAN5-6-4X 4 PIN

80 DAN5-6-5X 5 PIN

81 DAN5-6-6X 5 PIN

82 DAN5-6-8X 5 PIN

83 DAN7-8-9X 5 PIN

84 DAN7-8-10X 4 PIN

85 DAN7-8-11X 5 PIN

86 DAN7-10-11X 5 PIN

87 DAN7-10-12X 5 PIN

88 DAN7-10-17X 4 PIN

89 DAN5-6-10Y 4 PIN

90 DAN7-10-13 5 PIN

91 DAN7-10-15 5 PIN

92 DAN7-10-16 5 PIN

93 EN6115K5-7 5 BOLT

94 EN6115K5-8 BOLT

95 EN6115K5-15 2 BOLT

96 EN6115K5-16 2 BOLT

97 DAN12-10X 5 COLLAR

98 NSA5075-8 5 COLLAR

99 DAN5-8-7 2 PIN

100 DAN5-8-8 4 PIN

101 DAN7-10-10 5 PIN

102 EN6115K3X3 5 BOLT

103 EN6115K3X4 5 BOLT

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

104 EN6115K3X5 5 BOLT

105 EN6115K4-7 2 BOLT

106 EN6115K3X7 5 BOLT

107 EN6115K3X8 5 BOLT

108 EN6115K4-8 2 BOLT

109 EN6115K5X10 5 BOLT

110 EN6115K5X11 5 BOLT

111 EN6115K5X12 5 BOLT

112 EN6115K5X17 5 BOLT

113 EN6115K5X19 5 BOLT

References

Fig. A-GBCAA

Fastener Table

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Sheet 08

Sheet 09

Sheet 10

(a) If fasteners of Kit 533160D04R01 do not fit because oversize fasteners are

necessary, then refer to the fastener tables, as shown on Fig. A-GBCAA Sheet 01

thru Fig. A-GBCAA Sheet 10 to find the correct bolt or pin with the associated nut

or collar which is part of kit Kit 533160D05R01 and listed below:

2 Pin DAN5-6-4 Item 20

2 Pin DAN7-8-11 Item 28

5 Pin DAN7-10-11 Item 29

5 Pin DAN7-10-12 Item 30

5 Pin DAN5-6-7X Item 32

5 Pin DAN5-6-10X Item 33

2 Collar NSA5075-6 Item 46

2 Collar DAN12-8 Item 48

5 Collar DAN12-10 Item 49

5 Nut ASNA2528-3 Item 50

4 Nut ASNA2528-4 Item 51

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4 Nut ASNA2528-5 Item 52

5 Collar NSA5330-6 Item 53

2 Collar DAN12-8Y Item 54

5 Collar DAN12-8X Item 55

5 Collar DAN11-6X Item 56

4 Pin DAN5-6-7Y Item 57

2 Pin DAN7-8-12Y Item 62

5 Bolt EN6115K5-10 Item 68

5 Bolt EN6115K5-11 Item 69

5 Bolt EN6115K5-12 Item 70

5 Pin DAN5-6-3X Item 78

4 Pin DAN5-6-4X Item 79

5 Pin DAN5-6-5X Item 80

5 Pin DAN5-6-6X Item 81

5 Pin DAN5-6-8X Item 82

5 Pin DAN7-8-9X Item 83

4 Pin DAN7-8-10X Item 84

5 Pin DAN7-8-11X Item 85

5 Pin DAN7-10-11X Item 86

5 Pin DAN7-10-12X Item 87

4 Pin DAN7-10-17X Item 88

4 Pin DAN5-6-10Y Item 89

5 Pin DAN7-10-13 Item 90

5 Pin DAN7-10-15 Item 91

5 Pin DAN7-10-16 Item 92

5 Bolt EN6115K5-7 Item 93

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5 Bolt EN6115K5-8 Item 94

2 Bolt EN6115K5-15 Item 95

2 Bolt EN6115K5-16 Item 96

5 Collar DAN12-10X Item 97

5 Collar NSA5075-8 Item 98

4 Pin DAN5-8-8 Item 100

2 Pin DAN5-8-7 Item 99

5 Pin DAN7-10-10 Item 101

5 Bolt EN6115K3X3 Item 102

5 Bolt EN6115K3X4 Item 103

5 Bolt EN6115K3X5 Item 104

2 Bolt EN6115K4-7 Item 105

5 Bolt EN6115K3X7 Item 106

5 Bolt EN6115K3X8 Item 107

2 Bolt EN6115K4-8 Item 108

5 Bolt EN6115K5X10 Item 109

5 Bolt EN6115K5X11 Item 110

5 Bolt EN6115K5X12 Item 111

5 Bolt EN6115K5X17 Item 112

5 Bolt EN6115K5X19 Item 113

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

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SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 533160-831-223-001 - Close-up

Manpower Resources

Skills AIRFRAME

ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301

25-33-48, Page Block 401

25-33-53, Page Block 401

25-33-54, Page Block 401

29-00-00, Page Block 201

29-14-00, Page Block 201

36-12-14, Page Block 401

36-22-17, Page Block 401

52-10-00, Page Block 201

55-31-11, Page Block 401

(a) Install the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401).

(b) Reinstall the Bleed Air pipe between FR85 and FR87 (Refer to AMM 36-12-14,

Page Block 401).

(c) Reinstall the Bleed Air pipe sense line between FR85 and FR87 (Refer to AMM

36-22-17, Page Block 401).

(d) Install the AFT galley (Refer to AMM 25-33-53, Page Block 401 and AMM

25-33-54, Page Block 401).

(e) Install the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT

galley pelmet (Refer to AMM 25-33-48, Page Block 401).

(f) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(g) Close the access door 312AR in the REAR fuselage area.

(h) Remove the access platform(s) from the aircraft REAR section.

(i) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM

29-14-00, Page Block 201).

(j) Fill the Green hydraulic tank (Refer to AMM 12-12-29, Page Block 301).

(k) Pressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM

29-00-00, Page Block 201).

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 146

6

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@A330

SERVICE BULLETIN

(l) Remove the warning notices :

1 in the cockpit from the hydraulic section 40VU of the overhead panel,

2 on the ground service panel from each hydraulic system.

(m) Close the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page

Block 201).

(n) Remove the access platform from the passenger/crew doors.

**CONF 002

(1) Subtask 533160-831-223-001 - Close-up

Manpower Resources

Skills AIRFRAME

ELECTRICAL

References

Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301

25-33-48, Page Block 401

25-33-53, Page Block 401

25-33-54, Page Block 401

29-00-00, Page Block 201

29-14-00, Page Block 201

36-12-14, Page Block 401

36-22-17, Page Block 401

52-10-00, Page Block 201

55-31-11, Page Block 401

(a) Install the vertical stabilizer (Refer to AMM 55-31-11, Page Block 401).

(b) Reinstall the Bleed Air pipe between FR85 and FR87 (Refer to AMM 36-12-14,

Page Block 401).

(c) Reinstall the Bleed Air pipe sense line between FR85 and FR87 (Refer to AMM

36-22-17, Page Block 401).

(d) Install the AFT galley (Refer to AMM 25-33-53, Page Block 401 and AMM

25-33-54, Page Block 401).

(e) Install the AFT galley ceiling (Refer to AMM 25-33-54, Page Block 401) or the AFT

galley pelmet (Refer to AMM 25-33-48, Page Block 401).

(f) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(g) Close the access door 312AR in the REAR fuselage area.

(h) Remove the access platform(s) from the aircraft REAR section.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 147

6

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@A330

SERVICE BULLETIN

(i) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs (Refer to AMM

29-14-00, Page Block 201).

(j) Fill the Green hydraulic tank (Refer to AMM 12-12-29, Page Block 301).

(k) Pressurize the Green, the Blue and the Yellow hydraulic systems (Refer to AMM

29-00-00, Page Block 201).

(l) Remove the warning notices :

1 in the cockpit from the hydraulic section 40VU of the overhead panel,

2 on the ground service panel from each hydraulic system.

(m) Close the FWD passenger/crew doors (1L/1R) (Refer to AMM 52-10-00, Page

Block 201).

(n) Remove the access platform from the passenger/crew doors.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 148

6

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

SERVICE BULLETIN

**CONF 001

Z310

B

A

AD

Z270

A

C

C

STGR8 B

STGR8

FR91

FR87

FR79

G_SB_533160_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 149

6

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

SERVICE BULLETIN

**CONF 001

LH SHOWN

FASTENERS NOT EFFECTED RH SYMMETRICAL

NOTE:

REMOVE AND REUSE

REMOVE AND DISCARD

LH SIDE ONLY

CHECK THESE FASTENER HOLES FOR

EDGE CLEARANCE AND REWORK IF POSSIBLE,

REFER TO FIGURE 1.

AD

B

(130) 01 03

(131) 01

04

04

01

02

03

04

04

04

02 03

01

(132)

(131)

D

D

C

C

B

B

A

A

FR84 FR85 FR86

STGR3

STGR6

STGR8

G_SB_533160_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 150

6

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

SERVICE BULLETIN

**CONF 001

LH SHOWN

RH SYMMETRICAL

FASTENERS NOT EFFECTED

P/N DESCRIPTION

MIN MAX

ITEM KIT HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

COLLAR

COLLAR

COLLAR

NOMINAL SIZE

PIN UNI

PIN UNI

PIN UNI

NSA5075−6

TRANSITION FIT

4.78mm

(0.188in.)

4.78mm

(0.188in.)

6.31mm

(0.248in.)

4.78mm

(0.188in.)

4.06mm

(0.160in.)

6.31mm

(0.248in.)

6.31mm

(0.248in.)

6.31mm

(0.248in.)

6.31mm

(0.248in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

6.35mm

(0.250in.)

4.82mm

(0.190in.)

D01

D01

D01

D01

DAN5−6−5

NSA5075−6

DAN5−6−7

DAN5−8−7

NSA5075−8

COLLAR

PIN UNI

D01

DAN5−8−11

NSA5075−8

DAN5−8−14

COLLAR

D01

NSA5075−8

4.17mm

(0.164in.) D01

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

LN9198−4000CF

LN9198−4800CF

RIVET

RIVET

PIN, UNI

COLLAR

PIN UNI

D01

NSA5075−8

NOMINAL SIZE

TRANSITION FIT

COLLAR

PIN UNI

D01

DAN5−8−10

NSA5075−8

NOMINAL SIZE

TRANSITION FIT

DAN5−8−8

NOTE:

(36)

(54)

(37)

(54)

(38)

(51)

(39)

(51)

(40)

(51)

(41)

(51)

(42)

(51)

(43)

(44)

6.35mm

(0.250in.)

6.35mm

(0.250in.)

6.35mm

(0.250in.)

6.35mm

(0.250in.)

C

FR80

STGR2A

STGR5A

G_SB_533160_6_BAAA_03_00

Figure A-GBAAA - Sheet 03

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 151

6

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

SERVICE BULLETIN

**CONF 001

NOTE:

ONLY IN CASE OF LESS EDGE CLEARANCE AND NON REWORKABLE DRILL HOLE

INSTALL AN UNDERSIZE FASTENER WHICH IS PART OF KIT 533160D03 AND

GIVEN IN THE FASTENER TABLE AS ALTERNATIVE.

A A B B

C C D D

(0.57in.)

(14.5mm)

(0.52in.)

(13.3mm)

(0.52in.)

(13.1mm)

(0.49in.)

(12.4mm)

(0.49in.)

(12.4mm)

(0.51in.)

(13.0mm)

(0.53in.)

(13.4mm)

(0.51in.)

(13.0mm)

THE GIVEN VALUES ARE FOF INFORMATION ONLY.

IF THE MEASURED VALUES ON THE AIRCRAFT ARE SMALLER,

REFER TO THE SRM 51−47−00 FOR THE MINIMUM EDGE CLEARANCE. 06 05 06 05

06 05

06 05

06 05

06 05

06 05

06 05

05

06

A A B B

C C D D

G_SB_533160_6_BAAA_04_00

Figure A-GBAAA - Sheet 04

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 152

6

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

SERVICE BULLETIN

**CONF 002

Z310

B

A

AD

Z270

A

C

C

STGR8 B

STGR8

FR91

FR87

FR79

G_SB_533160_6_BAAB_01_00

Figure A-GBAAB - Sheet 01

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 153

6

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

SERVICE BULLETIN

**CONF 002

LH SHOWN

FASTENERS NOT EFFECTED RH SYMMETRICAL

NOTE:

REMOVE AND REUSE

REMOVE AND DISCARD

LH SIDE ONLY

CHECK THESE FASTENER HOLES FOR

EDGE CLEARANCE AND REWORK IF POSSIBLE,

REFER TO FIGURE 1.

AD

B

(130) 01 03

(131) 01

04

04

01

02

03

04

04

04

02 03

01

(132)

(131)

D

D

C

C

B

B

A

A

G_SB_533160_6_BAAB_02_00

FR84 FR85 FR86

STGR3

STGR6

STGR8

Figure A-GBAAB - Sheet 02

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 154

6

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

SERVICE BULLETIN

**CONF 002

LH SHOWN

RH SYMMETRICAL

FASTENERS NOT EFFECTED

P/N DESCRIPTION

MIN MAX

ITEM KIT HOLE

SYMBOL REMARKS

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

FINAL HOLE DIAMETER

COLLAR

COLLAR

COLLAR

PIN UNI

PIN UNI

PIN UNI

NSA5075−6

4.78mm

(0.188in.)

4.82mm

(0.190in.)

4.78mm

(0.188in.)

4.82mm

(0.190in.)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

4.78mm

(0.188in.)

4.82mm

(0.190in.)

D04

D04

D04

D04

DAN5−6−5

NSA5075−6

DAN5−6−7

DAN5−8−7

NSA5075−8

COLLAR

PIN UNI

D04

DAN5−8−11

NSA5075−8

DAN5−8−14

COLLAR

D04

NSA5075−8

4.06mm

(0.160in.)

4.17mm

(0.164in.) LN9198−4000CF D04

LN9198−4800CF

RIVET

RIVET

PIN, UNI

COLLAR

PIN UNI

D04

NSA5075−8

COLLAR

PIN UNI

D04

DAN5−8−10

NSA5075−8

DAN5−8−8

NOTE:

(36)

(54)

(37)

(54)

(38)

(51)

(39)

(51)

(40)

(51)

(41)

(51)

(42)

(51)

(43)

(44)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

C

FR80

STGR2A

STGR5A

G_SB_533160_6_BAAB_03_00

Figure A-GBAAB - Sheet 03

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 155

6

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

SERVICE BULLETIN

**CONF 002

NOTE:

ONLY IN CASE OF LESS EDGE CLEARANCE AND NON REWORKABLE DRILL HOLE

INSTALL AN UNDERSIZE FASTENER WHICH IS PART OF KIT 533160D06 AND

GIVEN IN THE FASTENER TABLE AS ALTERNATIVE.

THE GIVEN VALUES ARE FOF INFORMATION ONLY.

IF THE MEASURED VALUES ON THE AIRCRAFT ARE SMALLER,

REFER TO THE SRM 51−47−00 FOR THE MINIMUM EDGE CLEARANCE.

05

06

A A B B

C C D D

(0.57in.)

(14.5mm)

(0.52in.)

(13.3mm)

(0.52in.)

(13.1mm)

(0.49in.)

(12.4mm)

(0.49in.)

(12.4mm)

(0.51in.)

(13.0mm)

(0.53in.)

(13.4mm)

(0.51in.)

(13.0mm) 06 05

06 05

06 05

06 05

06 05

06 05

06 05

06 05

A A B B

C C D D

G_SB_533160_6_BAAB_04_00

Figure A-GBAAB - Sheet 04

Removal of Fastener from the upper fuselage shell between FR80 and FR86

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 156

6

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

SERVICE BULLETIN

**CONF 001

Z310

A Z270

FR91

A

FR80

FR84

B FR86

C

C

G_SB_533160_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 157

6

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

SERVICE BULLETIN

**CONF 001

01

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

C LH SHOWN

RH SYMMETRICAL

FWD

AD

T

V

H

H

V

T

Q L

F D

B

FR87

FR86

FR85

FR84

STGR2A

STGR5A

FR80

G_SB_533160_6_BBAA_02_02

Figure A-GBBAA - Sheet 02

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 158

6

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@A330

SERVICE BULLETIN

**CONF 001

(3 POS.)

(3 POS.)

1

38

5

51

9

E

75

D LH SHOWN

A

A

75

A A

G_SB_533160_6_BBAA_03_00

FR86 STGR2B

Figure A-GBBAA - Sheet 03

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 159

6

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

AD

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

F

W

D

NOTE:

01

01

01

E LH SHOWN

01

FR86

G_SB_533160_6_BBAA_04_00

STGR2B

Figure A-GBBAA - Sheet 04

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 160

6

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@A330

SERVICE BULLETIN

**CONF 001

2

6

51

38

G

F RH SHOWN

(3 POS.)

(3 POS.)

FR86

STGR2B

G_SB_533160_6_BBAA_05_00

Figure A-GBBAA - Sheet 05

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 161

6

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

SERVICE BULLETIN

**CONF 001

AD

F

W

D

G RH SHOWN

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

01 01

FR86

STGR2B

G_SB_533160_6_BBAA_06_00

Figure A-GBBAA - Sheet 06

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 162

6

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

SERVICE BULLETIN

**CONF 001

(5 POS.)

(5 POS.)

20.0mm

(0.79in.) (0.79in.)

3LH

4 RH

LH

RH

7

8

76

77

(131)

38

51

J

K

H

J

FWD

LH SHOWN

RH SYMMETRICAL

20.0mm

FR86

STGR5A

G_SB_533160_6_BBAA_07_00

Figure A-GBBAA - Sheet 07

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 163

6

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

01

F

W

D

K LH SHOWN

RH SYMMETRICAL

B B

8.0mm

(0.31in.)

max 16.0mm

(0.63in.)

SPOT

FACING

TOOL

1.6mm

(0.06in.)

B BR 1.5mm (0.059in.)

STGR5A

STGR5A

FR86

G_SB_533160_6_BBAA_08_00

Figure A-GBBAA - Sheet 08

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 164

6

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

SERVICE BULLETIN

**CONF 001

22.0mm

(0.87in.)

22.0mm

(0.87in.)

(2 POS.)

10

14

(131) 77

(130)

P

N

73

74

N FWD

L LH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAA_09_00

Figure A-GBBAA - Sheet 09

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 165

6

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

SERVICE BULLETIN

**CONF 001

0.2mm

(0.008in.)

56.5mm

(2.22in.)

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

F

W

D

P LH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAA_10_00

Figure A-GBBAA - Sheet 10

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 166

6

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

SERVICE BULLETIN

**CONF 001

(2 POS.)

22.0mm

(0.87in.)

11

15

77

(131)

S

R

R FWD

Q RH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAA_11_00

Figure A-GBBAA - Sheet 11

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 167

6

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

S RH SHOWN

01 0.2mm

(0.008in.)

56.5mm

(2.22in.)

F

W

D

FR84

STGR2A

G_SB_533160_6_BBAA_12_00

Figure A-GBBAA - Sheet 12

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 168

6

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

SERVICE BULLETIN

**CONF 001

LH

RH

U

13

12

LH

RH

17

16

T LH SHOWN

RH SYMMETRICAL

FR84

STGR5A

G_SB_533160_6_BBAA_13_00

Figure A-GBBAA - Sheet 13

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 169

6

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

U LH SHOWN

RH SYMMETRICAL

F

W

D

FR84

STGR2A

G_SB_533160_6_BBAA_14_00

Figure A-GBBAA - Sheet 14

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 170

6

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

SERVICE BULLETIN

**CONF 001

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

AD

01

01

01

01

V LH SHOWN

RH SYMMETRICAL

FWD

FR85

G_SB_533160_6_BBAA_15_01

Figure A-GBBAA - Sheet 15

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 171

6

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

SERVICE BULLETIN

**CONF 002

Z310

A Z270

FR91

A

FR80

FR84

B FR86

C

C

G_SB_533160_6_BBAB_01_00

Figure A-GBBAB - Sheet 01

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 172

6

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

SERVICE BULLETIN

**CONF 002

01

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

C LH SHOWN

RH SYMMETRICAL

FWD

AD

T

V

H

H

V

T

Q L

F D

B

FR87

FR86

FR85

FR84

STGR2A

STGR5A

FR80

G_SB_533160_6_BBAB_02_02

Figure A-GBBAB - Sheet 02

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 173

6

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

SERVICE BULLETIN

**CONF 002

(3 POS.)

(3 POS.)

1

38

5

51

9

E

75

D LH SHOWN

A

A

75

A A

G_SB_533160_6_BBAB_03_00

STGR2B FR86

Figure A-GBBAB - Sheet 03

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 174

6

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

AD

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

F

W

D

NOTE:

01

01

01

E LH SHOWN

01

FR86

G_SB_533160_6_BBAB_04_00

STGR2B

Figure A-GBBAB - Sheet 04

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 175

6

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

SERVICE BULLETIN

**CONF 002

2

6

51

38

G

F RH SHOWN

(3 POS.)

(3 POS.)

FR86

STGR2B

G_SB_533160_6_BBAB_05_00

Figure A-GBBAB - Sheet 05

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 176

6

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

SERVICE BULLETIN

**CONF 002

AD

F

W

D

G RH SHOWN

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

01 01

FR86

STGR2B

G_SB_533160_6_BBAB_06_00

Figure A-GBBAB - Sheet 06

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 177

6

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

SERVICE BULLETIN

**CONF 002

(5 POS.)

(5 POS.)

20.0mm

(0.79in.) (0.79in.)

3LH

4 RH

LH

RH

7

8

76

77

(131)

38

51

J

K

H

J

FWD

LH SHOWN

RH SYMMETRICAL

20.0mm

FR86

STGR5A

G_SB_533160_6_BBAB_07_00

Figure A-GBBAB - Sheet 07

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 178

6

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

01

F

W

D

K LH SHOWN

RH SYMMETRICAL

8.0mm

(0.31in.)

max 16.0mm

(0.63in.)

SPOT

FACING

TOOL

1.6mm

(0.06in.)

B B

B B

STGR5A

STGR5A

FR86

G_SB_533160_6_BBAB_08_00

R 1.5mm

(0.059in.)

Figure A-GBBAB - Sheet 08

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 179

6

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

SERVICE BULLETIN

**CONF 002

22.0mm

(0.87in.)

(2 POS.)

10

14

(131) 77

(130)

P

N

73

74

N FWD

L LH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAB_09_00

(0.87in.)

22.0mm

Figure A-GBBAB - Sheet 09

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 180

6

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

SERVICE BULLETIN

**CONF 002

0.2mm

(0.008in.)

56.5mm

(2.22in.)

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

F

W

D

P LH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAB_10_00

Figure A-GBBAB - Sheet 10

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 181

6

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

SERVICE BULLETIN

**CONF 002

(2 POS.)

22.0mm

(0.87in.)

11

15

77

(131)

S

R

R FWD

Q RH SHOWN

FR84

STGR2A

G_SB_533160_6_BBAB_11_00

Figure A-GBBAB - Sheet 11

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 182

6

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

S RH SHOWN

01 0.2mm

(0.008in.)

56.5mm

(2.22in.)

F

W

D

FR84

STGR2A

G_SB_533160_6_BBAB_12_00

Figure A-GBBAB - Sheet 12

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 183

6

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

SERVICE BULLETIN

**CONF 002

LH

RH

U

13

12

LH

RH

17

16

T LH SHOWN

RH SYMMETRICAL

FR84

STGR5A

G_SB_533160_6_BBAB_13_00

Figure A-GBBAB - Sheet 13

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 184

6

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

01

U LH SHOWN

RH SYMMETRICAL

F

W

D

FR84

STGR2A

G_SB_533160_6_BBAB_14_00

Figure A-GBBAB - Sheet 14

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 185

6

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

SERVICE BULLETIN

**CONF 002

FASTENERS NOT EFFECTED.

USE EXISTING RIVETHOLES.

POSITION OF SPLIT IN EXPANSION SLEEVE

DURING COLD EXPANSION.

NOTE:

01

AD

01

01

01

01

V LH SHOWN

RH SYMMETRICAL

FWD

FR85

G_SB_533160_6_BBAB_15_01

Figure A-GBBAB - Sheet 15

Installation of Reinforcement Brackets and new Fastener with Cold Working

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 186

6

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

SERVICE BULLETIN

**CONF ALL

COLLAR

PIN UNI

COLLAR

COLLAR

COLLAR

PIN UNI

PIN UNI

PIN, UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

PIN UNI

COLLAR

COLLAR

PIN, UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

PIN UNI

COLLAR

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

TRANSITION FIT

TRANSITION FIT

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

FIRST OVERSIZE

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

1ST OVERSIZE

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.78mm

(0.188in.)

4.13mm

(0.162in.)

5.11mm

(0.201in.)

5.11mm

(0.201in.)

5.11mm

(0.201in.)

5.11mm

(0.201in.)

5.11mm

(0.201in.)

5.11mm

(0.201in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.82mm

(0.190in.)

4.16mm

(0.164in.)

5.15mm

(0.203in.)

5.15mm

(0.203in.)

5.15mm

(0.203in.)

5.15mm

(0.203in.)

5.15mm

(0.203in.)

5.15mm

(0.203in.)

NSA5075−6

DAN5−6−5

DAN5−6−8

DAN5−5−4

NSA5075−5

DAN5−6−4

NSA5075−6

NSA5075−6

DAN5−6−3

DAN11−6X

DAN5−6−3X

DAN5−6−4

NSA5075−6

DAN5−6−4X

DAN11−6X

DAN5−6−5X

DAN11−6X

DAN5−6−6

NSA5075−6

DAN5−6−6X

DAN11−6X

DAN5−6−7

NSA5075−6

DAN5−6−7X

DAN11−6X

NSA5075−6

DAN5−6−8X

DAN11−6X

01

01

01

01

01

01

01

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

18

45

20

46

19

46

78

56

20

46

79

56

21

46

80

56

22

46

81

56

23

46

32

56

24

46

82

56

G_SB_533160_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 187

6

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

SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

COLLAR

PIN UNI

PIN UNI

COLLAR TRANSITION FIT

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

PIN UNI

COLLAR

COLLAR

PIN UNI

COLLAR

PIN UNI

PIN UNI

COLLAR

4.78mm

(0.188in.)

4.82mm

(0.190in.)

DAN5−6−10

NSA5075−6

PIN UNI

COLLAR

DAN5−6−10X

DAN11−6X

DAN7−8−10X

DAN12−8X

DAN7−8−11X

DAN12−8X

DAN7−6−9Y

DAN12−6Y

COLLAR

DAN7−8−10 PIN UNI

DAN12−8

DAN7−6−10Y

DAN12−6Y

PIN UNI

COLLAR

DAN7−8−11

DAN12−8

DAN7−6−11Y

DAN12−6Y

6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.31mm

(0.248in.)

6.35mm

(0.250in.)

5.11mm

(0.201in.)

5.15mm

(0.203in.)

5.51mm

(0.217in.)

5.55mm

(0.219in.)

5.51mm

(0.217in.)

5.55mm

(0.219in.)

5.51mm

(0.217in.)

5.55mm

(0.219in.)

6.71mm

(0.264in.)

6.75mm

(0.266in.)

6.71mm

(0.264in.)

6.75mm

(0.266in.)

COLLAR

DAN7−8−9X PIN UNI

DAN12−8X

COLLAR

PIN UNI

DAN12−8

DAN7−8−9 6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.71mm

(0.264in.)

6.75mm

(0.266in.)

COLLAR

DAN7−8−9X PIN UNI

DAN12−8X

COLLAR

PIN UNI

DAN12−8

DAN7−8−9 6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.71mm

(0.264in.)

6.75mm

(0.266in.)

COLLAR

DAN7−8−10X PIN UNI

DAN12−8X

COLLAR

DAN7−8−10 PIN UNI

DAN12−8

6.31mm

(0.248in.)

6.35mm

(0.250in.)

6.71mm

(0.264in.)

6.75mm

(0.266in.)

NOTE:

01

01

START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

01

01

01

01

25

46

33

56

114

47

26

48

83

55

26

48

83

55

115

47

27

48

84

55

27

48

84

55

34

47

28

48

85

55

G_SB_533160_6_BCAA_02_00

Figure A-GBCAA - Sheet 02

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 188

6

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

SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

COLLAR

COLLAR

PIN UNI

DAN5−6−7X PIN, UNI

DAN11−6X

DAN5−6−10X

DAN11−6X

COLLAR

COLLAR

PIN UNI

PIN, UNI

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

2ND OVERSIZE

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

2ND OVERSIZE

TRANSITION FIT

1ST OVERSIZE

PIN UNI

COLLAR

DAN7−10−12

DAN12−10

DAN7−10−12X

DAN12−10X

DAN12−10X

DAN7−10−17X

PIN UNI

DAN12−10 COLLAR

DAN7−10−17

PIN UNI

COLLAR

DAN7−8−12Y

DAN12−8Y

DAN7−8−17Y

DAN12−8Y

DAN5−6−7Y

NSA5330−6

DAN5−6−10Y

7.90mm

(0.311in.)

7.90mm

(0.311in.)

5.51mm

(0.217in.)

7.10mm

(0.280in.)

8.30mm

(0.327in.)

7.10mm

(0.280in.)

8.30mm

(0.327in.)

5.11mm

(0.201in.)

5.51mm

(0.217in.)

5.11mm

(0.201in.)

7.90mm

(0.311in.)

7.10mm

(0.280in.)

8.30mm

(0.327in.)

7.94mm

(0.313in.)

7.94mm

(0.313in.)

5.55mm

(0.219in.)

7.14mm

(0.281in.)

8.34mm

(0.328in.)

7.14mm

(0.281in.)

8.34mm

(0.328in.)

5.15mm

(0.203in.)

5.55mm

(0.219in.)

5.15mm

(0.203in.)

NSA5330−6

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN7−10−11X

DAN12−10X

PIN UNI

COLLAR

DAN7−10−11

DAN12−10

DAN7−8−11Y

DAN12−8Y

7.94mm

(0.313in.)

7.14mm

(0.281in.)

8.34mm

(0.328in.)

01

01

01

01

01

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

61

54

29

49

86

97

62

54

30

49

87

97

116

54

31

49

88

97

32

56

57

53

33

56

89

53

G_SB_533160_6_BCAA_03_00

Figure A-GBCAA - Sheet 03

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 189

6

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

SERVICE BULLETIN

**CONF ALL

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN7−8−16Y PIN UNI

DAN12−8Y

COLLAR

DAN7−8−15Y PIN UNI

DAN12−8Y

COLLAR

DAN7−8−13Y PIN UNI

DAN12−8Y

DAN7−10−13

DAN12−10 TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

1ST OVERSIZE

TRANSITION FIT

2ND OVERSIZE

DAN7−8−13X

DAN12−8X

DAN7−10−15

DAN12−10

DAN7−8−15X

DAN12−8X

DAN7−10−16

DAN12−10

DAN7−8−16X

DAN12−8X

7.90mm

(0.311in.)

7.90mm

(0.311in.)

7.90mm

(0.311in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

6.31mm

(0.248in.)

5.51mm

(0.217in.)

5.11mm

(0.201in.)

7.94mm

(0.313in.)

7.94mm

(0.313in.)

7.94mm

(0.313in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

COLLAR

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN7−6−11Y PIN UNI

DAN12−6Y

DAN7−8−11

DAN12−8

DAN12−6X

DAN7−6−11X

6.35mm

(0.250in.)

5.55mm

(0.219in.)

5.15mm

(0.203in.)

01

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

01

01

117

121

34

47

28

48

118

55

35

54

90

49

119

55

36

54

91

49

120

55

37

54

92

49

G_SB_533160_6_BCAA_04_00

Figure A-GBCAA - Sheet 04

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 190

6

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

SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

COLLAR

PIN UNI

COLLAR

PIN UNI

PIN UNI

COLLAR

DAN7−8−12X

DAN12−8X

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN5−6−8Y

NSA5330−6

PIN UNI

COLLAR

COLLAR

PIN UNI

COLLAR

PIN UNI

TRANSITION FIT

TRANSITION FIT

TRANSITION FIT

NOMINAL SIZE

NOMINAL SIZE

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

TRANSITION FIT

NOMINAL SIZE

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

COLLAR

DAN7−8−10Y PIN UNI

DAN12−8Y

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN7−8−11Y

DAN12−8Y

DAN5−8−8

NSA5075−8

DAN7−8−12Y

DAN12−8Y

DAN7−10−10

DAN12−10

DAN7−8−10X

DAN12−8X

DAN7−10−11

DAN12−10

DAN7−8−11X

DAN12−8X

7.90mm

(0.311in.)

7.90mm

(0.311in.)

6.31mm

(0.248in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

5.11mm

(0.201in.)

5.51mm

(0.217in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

6.71mm

(0.264in.)

7.10mm

(0.280in.)

6.31mm

(0.248in.)

5.11mm

(0.201in.)

5.51mm

(0.217in.)

7.94mm

(0.313in.)

7.94mm

(0.313in.)

6.35mm

(0.250in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

5.15mm

(0.203in.)

5.55mm

(0.219in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

6.75mm

(0.266in.)

7.14mm

(0.281in.)

DAN5−6−8X

DAN11−6X

PIN UNI

COLLAR

DAN5−6−7Y

NSA5330−6

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN5−6−7X

DAN5−8−7

NSA5075−8

6.35mm

(0.250in.)

5.15mm

(0.203in.)

5.55mm

(0.219in.)

DAN11−6X

01

01

01

01

01

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

32

56

57

53

99

98

82

56

58

53

100

98

59

55

62

54

84

55

60

54

101

49

85

55

61

54

29

49

G_SB_533160_6_BCAA_05_00

Figure A-GBCAA - Sheet 05

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 191

6

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

SERVICE BULLETIN

**CONF ALL

NOMINAL SIZE

TRANSITION FIT RIVET

NOMINAL SIZE

TRANSITION FIT

RIVET

RIVET

NOMINAL SIZE

TRANSITION FIT

EN6080D5−06

4.06mm

(0.16in.)

4.17mm

(0.164in.)

4.85mm

(0.191in.)

4.95mm

(0.195in.)

4.06mm

(0.16in.)

4.17mm

(0.164in.)

NOMINAL SIZE

TRANSITION FIT

RIVET

RIVET

NOMINAL SIZE

TRANSITION FIT

LN9198−4814CF

LN9198−4014CF

LN9198−4812CF

LN9198−4012CF

4.06mm

(0.16in.)

4.17mm

(0.164in.)

4.85mm

(0.191in.)

4.95mm

(0.195in.)

PIN UNI

COLLAR TRANSITION FIT

PIN UNI

COLLAR

PIN UNI

COLLAR

DAN7−8−12Y

DAN12−8Y

DAN7−10−12

DAN12−10

DAN7−8−12X

DAN12−8X

7.90mm NOMINAL SIZE

(0.311in.)

7.94mm

(0.313in.)

TRANSITION FIT

TRANSITION FIT

1ST OVERSIZE

2ND OVERSIZE

6.71mm

(0.264in.)

6.75mm

(0.266in.)

7.10mm

(0.280in.)

7.14mm

(0.281in.)

P/N DESCRIPTION

MIN MAX

ITEM HOLE

SYMBOL REMARKS

FINAL HOLE DIAMETER

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

59

55

62

54

30

49

73

76

75

74

77

G_SB_533160_6_BCAA_06_00

Figure A-GBCAA - Sheet 06

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 192

6

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

SERVICE BULLETIN

**CONF ALL

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

INTERFERENCE FIT

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

REMARKS

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

2ND OVERSIZE

ASNA2528−4

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

EN6115K4Y7

ASNA2528−4

BOLT

NUT

EN6115K5−7

ASNA2528−5

ASNA2528−4

EN6115K4Y8 BOLT

NUT

EN6115K5−8

ASNA2528−5

ASNA2528−4

EN6115K4Y10 BOLT

NUT

ASNA2528−5

EN6115K5−10

ASNA2528−4

EN6115K4Y11 BOLT

NUT

ASNA2528−5

EN6115K5−11

ASNA2528−4

EN6115K4Y12 BOLT

NUT

EN6115K5−12

ASNA2528−5

BOLT

ASNA2528−5 NUT

P/N DESCRIPTION GAGE FINISH REAMER

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

MIN

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

MAX

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

START REAMER

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−1−N−1

HOLE ITEM SYMBOL STDN

8−3−N

8−1−N

8−3−N

8−1−N

8−3−N

8−1−N

8−3−N

8−1−N

8−3−N

8−1−N

8−3−N

8−1−N

8−3−N

8−1−N

FINAL HOLE DIAMETER

START DRILL

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−1−N−1

ASNA2528−4

EN6115K4Y16 BOLT

NUT

BOLT

NUT

EN6115K5−16

ASNA2528−5

EN6115K4Y15

EN6115K5−15

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

01

01

01

01

01

01

38

51

93

52

39

51

94

52

40

51

68

52

41

51

69

52

42

51

70

52

43

51

95

52

44

51

96

52

G_SB_533160_6_BCAA_07_00

Figure A-GBCAA - Sheet 07

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 193

6

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

SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION GAGE FINISH REAMER

CBR−4−4−N−1−.1859

CBR−4−4−N−1−.1859

CBR−4−4−N−1−.1859

CBR−4−4−N−1−.1859

CBR−4−4−N−1−.1859

CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991

CBR−6−1−N−1−.215

CBR−6−3−N−1−.246

CBR−6−0−N−1−.1991

CBR−6−0−N−1−.1991

CBR−6−1−N−1−.215

CBR−6−3−N−1−.246

MIN

4.723mm

(0.1859in.)

4.723mm

(0.1859in.)

4.723mm

(0.1859in.)

4.723mm

(0.1859in.)

(0.1991in.)

5.056mm

4.723mm

(0.1859in.)

5.056mm

(0.1991in.)

5.056mm

(0.1991in.)

5.452mm

(0.215in.)

6.252mm

(0.246in.)

5.056

(0.1991in.)

5.056mm

(0.1991in.)

5.452mm

(0.215in.)

6.252mm

(0.246in.)

MAX

4.758mm

(0.1873in.)

4.758mm

(0.1873in.)

4.758mm

(0.1873in.)

4.758mm

(0.1873in.)

4.758mm

(0.1873in.)

5.090mm

(0.200in.)

5.090mm

(0.200in.)

5.090mm

(0.200in.)

5.487mm

(0.216in.)

6.287mm

(0.248in.)

5.090mm

(0.200in.)

5.090mm

(0.200in.)

5.487mm

(0.216in.)

6.287mm

(0.246in.)

START REAMER

CBSR−4−4−N−1

CBSR−4−4−N−1

CBSR−4−4−N−1

CBSR−4−4−N−1

CBSR−4−4−N−1

CBSR−6−0−N−1

CBSR−6−0−N−1

CBSR−6−0−N−1

CBSR−6−3−N−1

CBSR−6−1−N−1

CBSR−6−0−N−1

CBSR−6−0−N−1

CBSR−6−1−N−1

CBSR−6−3−N−1

HOLE ITEM SYMBOL STDN REMARKS

FINAL HOLE DIAMETER

START DRILL

CBSD−4−4−N−1

CBSD−4−4−N−1

CBSD−4−4−N−1

CBSD−4−4−N−1

CBSD−4−4−N−1

CBSD−6−0−N−1

CBSD−6−0−N−1

CBSD−6−0−N−1

CBSD−6−1−N−1

CBSD−6−0−N−1

CBSD−6−0−N−1

CBSD−6−1−N−1

CBSD−6−3−N−1

CBSD−6−3−N−1

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

NOMINAL SIZE 4−4−N

INTERFERENCE FIT

NOMINAL SIZE 4−4−N

INTERFERENCE FIT

NOMINAL SIZE

INTERFERENCE FIT

NOMINAL SIZE

ASNA2528−3

ASNA2528−3

ASNA2528−3

ASNA2528−3

EN6115K3−4

EN6115K3−5

EN6115K3−7

EN6115K3−8

ASNA2528−3A

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

INTERFERENCE FIT

BOLT

NUT

INTERFERENCE FIT ASNA2528−3

BOLT

NUT

INTERFERENCE FIT

NOMINAL SIZE BOLT

NUT

INTERFERENCE FIT

BOLT

NUT

INTERFERENCE FIT

BOLT

NUT

ASNA2528−3A

BOLT

NUT

ASNA2528−3

EN6115K3X4

EN6115K3X5

ASNA2528−4

EN6115K4−7

ASNA2528−3

EN6115K3X7

ASNA2528−3

EN6115K3X8

ASNA2528−4

INTERFERENCE FIT

BOLT

NUT

INTERFERENCE FIT

NOMINAL SIZE 4−4−N

EN6115K3−3

ASNA2528−3

BOLT

NUT

EN6115K3X3

ASNA2528−3

1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE

1ST OVERSIZE

EN6115K3A7

EN6115K3A8

EN6115K4−8

6−0−N

6−0−N

4−4−N

4−4−N

6−0−N

6−3−N

6−0−N

6−0−N

6−3−N

NOMINAL

NOMINAL

6−1−N

6−1−N

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

01

01

01

01

01

01 63

50

102

50

64

50

103

50

65

50

104

50

124

126

105

51

66

50

106

50

67

50

107

50

125

126

108

51

G_SB_533160_6_BCAA_08_00

Figure A-GBCAA - Sheet 08

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 194

6

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

SERVICE BULLETIN

**CONF ALL

INTERFERENCE FIT

NOMINAL SIZE EN6115K5−10

ASNA2528−5

INTERFERENCE FIT

NOMINAL SIZE

ASNA2528−5

EN6115K5−11

ASNA2528−5

INTERFERENCE FIT

NOMINAL SIZE

ASNA2528−5

EN6115K5−12

ASNA2528−5

INTERFERENCE FIT

NOMINAL SIZE

ASNA2528−5

EN6115K5−17

P/N DESCRIPTION GAGE FINISH REAMER

CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088

CBR−8−3−N−1−.3088

CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245

CBR−10−0−N−1−.3245

MIN

7.044mm

(0.2773in.)

7.044mm

(0.2773in.)

7.044mm

(0.2773in.)

7.044mm

(0.2773in.)

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

7.845mm

(0.3088in.)

7.845mm

(0.3088in.)

7.845mm

(0.3088in.)

8.241mm

(0.3245in.)

8.241mm

(0.3245in.)

8.241mm

(0.3245in.)

8.241mm

(0.3245in.)

MAX

7.078mm

(0.2787in.)

7.078mm

(0.2787in.)

7.078mm

(0.2787in.)

7.078mm

(0.2787in.)

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

7.879mm

(0.3102in.)

7.879mm

(0.3102in.)

7.879mm

(0.3102in.)

8.275mm

(0.3258in.)

8.275mm

(0.3258in.)

8.275mm

(0.3258in.)

8.275mm

(0.3258in.)

START REAMER

CBSR−8−1−N−1

CBSR−8−1−N−1

CBSR−8−1−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−8−3−N−1

CBSR−8−3−N−1

CBSR−8−3−N−1

CBSR−10−0−N−1

CBSR−10−0−N−1

CBSR−10−0−N−1

CBSR−10−0−N−1

ITEM HOLE

SYMBOL STDN REMARKS

8−1−N

8−1−N

8−1−N

8−1−N

8−3−N

8−3−N

8−3−N

8−3−N

10−0−N

10−0−N

10−0−N

10−0−N

FINAL HOLE DIAMETER

START DRILL

CBSD−8−1−N−1

CBSD−8−1−N−1

CBSD−8−1−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−8−3−N−1

CBSD−8−3−N−1

CBSD−8−3−N−1

CBSD−10−0−N−1

CBSD−10−0−N−1

CBSD−10−0−N−1

CBSD−10−0−N−1

EN6115K5X17

EN6115K4Y17

ASNA2528−4

EN6115K5X12

ASNA2528−4

EN6115K4Y12

ASNA2528−5

EN6115K5X11

ASNA2528−4

EN6115K4Y11

EN6115K5X10

ASNA2528−5

EN6115K4Y10

ASNA2528−4

INTERFERENCE FIT

1ST OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

2ND OVERSIZE

INTERFERENCE FIT

1ST OVERSIZE

INTERFERENCE FIT

1ST OVERSIZE

INTERFERENCE FIT

1ST OVERSIZE

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

01

01

01

01

NOTE:

01 START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

40

51

68

52

109

52

41

51

69

52

110

52

42

51

70

52

111

52

122

51

71

52

112

52

G_SB_533160_6_BCAA_09_00

Figure A-GBCAA - Sheet 09

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 195

6

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

SERVICE BULLETIN

**CONF ALL

P/N DESCRIPTION GAGE FINISH REAMER

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

CBR−10−0−N−1−.3245

MIN

7.044mm

(0.2773in.)

7.845mm

(0.3088in.)

8.241mm

(0.3245in.)

MAX

7.078mm

(0.2787in.)

7.879mm

(0.3102in.)

8.275mm

(0.3258in.)

START REAMER

CBSR−8−1−N−1

CBSR−8−3−N−1

CBSR−10−0−N−1

ITEM HOLE

SYMBOL STDN REMARKS

8−1−N

8−3−N

10−0−N

FINAL HOLE DIAMETER

START DRILL

CBSD−8−1−N−1

CBSD−8−3−N−1

CBSD−10−0−N−1 INTERFERENCE FIT ASNA2528−5

INTERFERENCE FIT

INTERFERENCE FIT

NOMINAL SIZE

ASNA2528−5

EN6115K5−19

EN6115K5X19

EN6115K4Y19

ASNA2528−4

2ND OVERSIZE

1ST OVERSIZE

BOLT

NUT

BOLT

NUT

BOLT

NUT

NOTE:

START IN THIS ROW TO DETERMINE

THE FINAL FASTENER SIZE.

01

01

123

51

72

52

113

52

G_SB_533160_6_BCAA_10_00

Figure A-GBCAA - Sheet 10

Fastener Table

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 196

6

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

SERVICE BULLETIN

**CONF ALL

FR91

Z310 Z270

A

B

B

D

D

E

E

A

FR80

FR84

FR86

G_SB_533160_6_BDAA_01_00

Figure A-GBDAA - Sheet 01

Inspection Areas of Fastener Hole Rototest and for HFEC Inspection

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 197

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SERVICE BULLETIN

**CONF ALL

A

A

FR80

STGR2A

STGR5A

STGR2A

STGR5A

C

B

C

A A

TYPICAL HOLE

LH SHOWN

RH SYMMETRICAL

FWD

01

adet = 1.0mm

(0.039in.)

NOTE:

01 TO BE INSPECTED BY ROTOTEST ONLY. G_SB_533160_6_BDAA_02_00

Figure A-GBDAA - Sheet 02

Inspection Areas of Fastener Hole Rototest and for HFEC Inspection

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 198

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SERVICE BULLETIN

**CONF ALL

FWD

FR84

D LH SHOWN

RH SYMMETRICAL

B

B

B

B

INSPECTION AREA B

FROM OUTSIDE

AD

NOTE:

DO THE ROTOTEST ONLY

IN THE HOLES OF AREA B

WHICH ARE ALREADY REMOVED.

STGR3

STGR5A

G_SB_533160_6_BDAA_03_00

Figure A-GBDAA - Sheet 03

Inspection Areas of Fastener Hole Rototest and for HFEC Inspection

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 199

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SERVICE BULLETIN

**CONF ALL

LH SHOWN

RH SYMMETRICAL

INSPECTION AREA C

FROM OUTSIDE

FR86

B

B

B

B

AD

FWD E

STGR3

STGR6

STGR8

NOTE:

DO THE ROTOTEST ONLY

IN THE HOLES OF AREA C

WHICH ARE ALREADY REMOVED. G_SB_533160_6_BDAA_04_00

Figure A-GBDAA - Sheet 04

Inspection Areas of Fastener Hole Rototest and for HFEC Inspection

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 200

6

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SERVICE BULLETIN

**CONF ALL

B B

2.0 mm

(0.079 in)

adet =

F

STGR

1.0mm

(0.39in.)

F

TYPICAL HOLE

FOR ROTOTEST INSPECTION

TYPICAL

FOR HFEC INSPECTION

G_SB_533160_6_BDAA_05_00

Figure A-GBDAA - Sheet 05

Inspection Areas of Fastener Hole Rototest and for HFEC Inspection

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 201

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**CONF ALL

REMOVE THE FASTENERS AS SHOWN IN FIGURE 2

DO A ROTOTEST OF ALL FASTENER HOLES AND

DO A HFEC TEST BETWEEN ALL FASTENER HOLES

CHECK THE EDGE CLEARENCE IN ACCORDANCE WITH

THE FINAL DIAMETER OF FASTENER HOLES AND SRM 51−47−00.

IS THE

EDGE CLEARANCE

TO MOVE THE HOLE CENTER POINT

REWORK THE FASTENER HOLE WITH A

MILLING TOOL TO ENSURE THE REQUIRED

EDGE CLEARENCE

IS THE REWORK

OF THE FASTENER HOLES

POSSIBLE?

INSTALL THE DOUPLER BY TRANSFER DRILLING

THE FASTENER HOLES WITH A DRILL

CORESPONDING WITH THE REWORKED

FASTENER HOLE DIMENSION.

INSTALL THE DOUBLER WITH

THE STANDARD FASTENERS OR

NEXT OVERSIZE FASTENERS

AS GIVEN IN THE SERVICE BULLETIN

INSTALL THE DOUBLER WITH

THE UNDERSIZE FASTENERS

NO

CHECK IF YOU CAN REWORK

THE FASTENER HOLES CORRECT?

YES NO

YES

AS GIVEN IN THE SERVICE BULLETIN

FOR ONE DOUBLER INSTALLATION ONLY FIVE UNDERSIZE FASTENERS ARE

ALLOWED WITH A MAXIMUM OF TWO FASTENERS ADJACENT TO EACH OTHER.

IF IT IS NECESSARY TO INSTALL MORE THAN FIVE UNDERSIZE FASTENERS

CONTACT AIRBUS.

NOTE:

01

01

G_SB_533160_6_BEAA_01_00

Figure A-GBEAA - Sheet 01

Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 202

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SERVICE BULLETIN

**CONF ALL

STEP 1 STEP 2 STEP 3

MILLING DRILL FINAL DRILL

X X Y X+Y

REMOVED

MATERIAL DIAMETER

DRILL HOLE

FINAL FASTENER

REWORKED

FASTENER HOLE

AFTER MILLING

= AFFECTED FASTENER HOLES

A B C

A B C

D E F

D E F

A

A

A A B B C C

G_SB_533160_6_BEAA_02_00

Figure A-GBEAA - Sheet 02

Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 203

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL

CHANGES DUE TO EF3 TEST RESULTS IN SECTION 19 (RETRO

SOLUTION) - INSTALLATION OF REINFORCEMENT DOUBLERS AND

COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A

AND 5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH

MODIFICATION No.: 53222D44560

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 1

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SERVICE BULLETIN

REPORTING SHEET

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 2

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jul 09/07 SERVICE BULLETIN No.: A330-53-3160

REVISION No.: 03 - Jan 06/12 Page: 1

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