@A330

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - PAX COMPARTMENT - MODIFY CDLS

WIRING LOOM IN UPPER COCKPIT DOOR PLATE COVER

MODIFICATION No.: 51911D44499

This page transmits Revision No.02 of Service Bulletin No.A330-25-3213

ADDITIONAL WORK

**CONF ALL

Additional work is required by this revision for aircraft modified by any previous issue of this Service

Bulletin.

AIRBUS recommends the additional work to be accomplished within one year after the issue of this

revision.

The additional work consists in:

- Replace the fasteners of the cover.

REASON

Revision No. 02 issued to incorporate changes found necessary and carried out during the

accomplishment of this Service Bulletin on aircraft with Manufacturer Serial Number (MSN) 0555, 0573

and 0587. An additional work added for aircraft modified by any previous revisions.

NOTE: This revision satisfies the requirements of the subsequent Technical Adaptations (TA)

issued for the related MSN:

TA MSN

TA 80105052/013/2016 0555, 0573 and 0587

CHANGES

The main changes of this revision are:

- Modification of the Kit 253213D02:

. 2 washers ASNA0113-56ADL replaced by NSA5379-3C

. 1 washer NAS1149CN949R replaced by NSA5379-3C

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 2 bolts NAS1096-3-14 replaced by MS21250-03006

. 1 cable tie NSA935401-03 added

- Introduction of the ADDITIONAL WORK, with the Kit COMPD01 and illustration BFAA created,

valid for aircraft modified by any previous issue

- Update of sentences in TEST paragraphs

- Revision of text and layout

- Addition of new sentence in ’ACCOMPLISHMENT INSTRUCTIONS’ paragraph.

NOTE: Revised text and layout changes of this revision are not identified with revision bars.

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

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

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

Material Effectivity 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

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE 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

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

Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

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

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 253213D02R02 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

Component COMPD01 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

Reidentified part set REIDD01 Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 253213- 831-848-001-Modification Minor editorial or document structure change N

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

Subtask 253213-910-201-001 Minor editorial or document structure change N

Subtask 253213-900-202-001 Minor editorial or document structure change N

Subtask 253213-941-201-001 Minor editorial or document structure change N

Subtask 253213-862-201-001 Minor editorial or document structure change N

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 253213-010-201-001 Minor editorial or document structure change N

Subtask 253213-831-203-001 Minor editorial or document structure change N

Subtask 253213-420-201-001 Minor editorial or document structure change N

Subtask 253213-861-201-001 Minor editorial or document structure change N

Subtask 253213-700-209-001 Minor editorial or document structure change N

Subtask 253213-942-209-001 Minor editorial or document structure change N

TASK 253213- 831-849-001-Modification -

Additional Work for Aircraft Modified by

Revision No. 01 or any Previous Issue

Minor editorial or document structure change N

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

Subtask 253213-910-202-001 Minor editorial or document structure change N

Subtask 253213-839-201-001 Minor editorial or document structure change N

Subtask 253213-941-202-001 Minor editorial or document structure change N

Subtask 253213-831-204-001 Minor editorial or document structure change N

Subtask 253213-942-210-001 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-GBAAA Sheet 05 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-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-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-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

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

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

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

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

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

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

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

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

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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

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

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

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

FILING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 was issued to add the removal/installation of the Anti Hijack Camera, update the

effectivity, add some covers to the parts to be re-identified and make some other minor changes.

NOTE: This is only applicable for Revision No. 02 and subsequent. If information is required for

Revisions issued previous to this, please check your copies of Revision Transmittal

Sheets or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL: Oct 12/04

REVISION No.: 01 - Apr 25/05

REVISION No. : 02 - Aug 12/16

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - PAX COMPARTMENT - MODIFY CDLS

WIRING LOOM IN UPPER COCKPIT DOOR PLATE COVER

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 51911D44499

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 the accomplishment of the Service Bulletin No. A340-25-4181 (EQUIPMENT/FURNISHINGS

- PASSENGER COMPARTMENT - INTRODUCE A MODIFIED INTRUSION AND PENETRATION

RESISTANCE COCKPIT DOOR), it was found that the electrical harness 7450VB, installed on the

cover of the upper cockpit door frame, is accessible from the cabin side. Therefore, the protection of

this harness must be improved.

This Service Bulletin introduces:

- a re-routing of the electrical harness 7450VB

- the installation of a protection plate for the electrical harness 7450VB.

This Service Bulletin has been validated on A340-600 aircraft MSN 0436.

Accomplishment of this Service Bulletin improves cockpit security by denying access to the electrical

harness from the cabin side.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD NO A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

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

disruptions.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 253213D02R02 1 260.00 Bolt, Washer, Screw, Wire protection,

Clamp, Nut, Cable Tie

Component COMPD01 1 See SB Bolt, Washer

EFFECTIVITY

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

38W 51X AAL ABD ACA ACI AEA AFR ALK ARG AZA AZU BEL

BER BGH CPA CRL CSA DAL DGA DLH EDW EIN F2I FWI G8E

GFA GIA GRL HDA HFY HVN KAL MAS MLM MOV OHY PLM QAF

QFA QTR RSY SAI SAS SXD TAE TAM TAP TCX THA THY TSC

UAE VKG WRC XAX XLF

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletin(s):

Service Bulletin No. A330-25-3161

NOTE: Service Bulletin No. A330-25-3161 (EQUIPMENT/FURNISHING - PASSENGER

COMPARTMENT - INTRODUCTION A MODIFIED INTRUSION AND PENETRATION

RESISTANCE COCKPIT DOOR) applies MOD 500014D44099.

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

ISI 00.00.00198

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 253213-831-848-001: Modification

TOTAL MANHOURS 18.50

ELAPSED TIME (HOURS) 14.00

Task 253213-831-849-001: Modification - Additional Work for Aircraft Modified by Revision No.

01 or any Previous Issue

TOTAL MANHOURS 1.00

APPENDICES

None

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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@A330

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR16A

FR12

B

A

32MQ

31MQ

30MQ

25MQ−A

KEYPAD 25MQ

317LG

6296VS

6294VS

6295VS

A

32MQ

31MQ

30MQ

25MQ−A

KEYPAD 25MQ

317LG

6296VS

6294VS

6295VS

FR11

B

BEFORE

B

AFTER

Z220

40MQ 40MQ

6297VS 6297VS

G_SB_253213_6_SAAA_01_00

Figure A-GSAAA - Sheet 01

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 4

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - PAX COMPARTMENT - MODIFY CDLS

WIRING LOOM IN UPPER COCKPIT DOOR PLATE COVER

MODIFICATION No.: 51911D44499

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

(1) Models

330-202 330-203 330-223 330-243 330-301 330-303 330-321 330-322

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

(2) Effectivity by MSN

0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0065 0070-0072

0082-0083 0086-0087 0095-0096 0098-0099 0102 0106 0109 0111-0113 0116 0118

0120-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172

0177 0181 0195 0200 0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238

0240-0241 0244 0247-0251 0253-0256 0258-0259 0261-0262 0265-0267 0269

0271-0272 0275-0277 0279 0281 0283-0288 0290-0291 0293-0296 0299-0301 0303

0305-0306 0308-0309 0311-0317 0320 0322-0324 0326 0328 0330 0333-0334

0337-0340 0342-0346 0348-0351 0353 0356-0358 0361-0362 0364-0366 0368-0370

0372 0375 0380 0382 0384 0386 0388-0389 0392-0393 0396-0398 0400-0401

0403-0405 0407-0409 0412 0418-0423 0425 0427-0428 0432 0437 0439 0441

0443-0444 0448 0451-0452 0454-0456 0458 0461-0463 0465-0466 0469 0472-0473

0476-0477 0479-0481 0484 0486-0487 0489-0491 0493-0494 0496-0498 0500-0501

0503-0513 0515-0516 0518-0519 0521-0522 0524-0527 0529-0530 0532-0533

0535-0536 0539 0542 0548-0553 0555 0558 0564-0565 0567-0568 0570-0571 0573

0576 0578-0579 0581 0584 0587-0588 0591 0597

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SERVICE BULLETIN

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

38W 0401

51X 0261

AAL 0315 0323 0333 0337 0342 0370 0375 0380 0388

ABD 0343

ACA 0277 0279 0284 0344 0400 0408 0412 0419

ACI 0507 0510

AEA 0461 0505 0526 0551 0597

AFR 0422 0443 0448 0458 0465 0481 0498 0500 0503 0516 0519 0567

0584

ALK 0303 0306 0311 0313 0456

ARG 0290 0300 0358 0364 0587

AZA 0272 0339

AZU 0462 0494 0527 0529 0532

BEL 0030 0037 0045 0082 0095 0229 0249 0324

BER 0288 0322 0403 0432 0444 0454 0469 0476 0493

BGH 0255

CPA 0102 0113 0121 0386 0389 0393 0418 0420 0421 0423 0439 0539

0548 0565

CRL 0285 0320

CSA 0425

DAL 0524 0533 0542 0549 0552 0578 0588 0591

DGA 0240

DLH 0570 0576 0579

EDW 0291

EIN 0269 0330 0397

F2I 0087 0200

FWI 0253

G8E 0294 0299

GFA 0276 0281 0286 0287 0334 0340

GIA 0138 0140 0144 0148 0153 0165

GRL 0230

HDA 0012 0017 0071 0083 0099 0106 0109 0118 0155 0234 0244 0405

0479 0512 0581

HFY 0127 0211 0262

HVN 0275 0366

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

0351 0368 0428 0484 0490 0550

MAS 0116

MLM 0451

MOV 0535

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SERVICE BULLETIN

OPERATOR MSN

OHY 0072 0098 0143 0316 0345 0353 0362 0404 0437

PLM 0265

QAF 0487

QFA 0506 0508 0513 0522 0553 0558 0564

QTR 0441 0473 0489 0511 0521 0571

RSY 0096 0120 0171

SAI 0055 0070 0086

SAS 0496 0497 0515 0568

SXD 0530 0555 0573

TAE 0348

TAM 0232 0238 0247 0259 0361 0466 0472

TAP 0181 0195 0223 0305 0308 0312 0317 0365 0372 0477 0486

TCX 0254 0266 0301 0398

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

THY 0463 0504

TSC 0111 0132 0177 0248 0250 0251 0271 0369 0407 0427 0480

UAE 0283 0293 0295 0314 0326 0328 0382 0384 0392 0396 0409 0452

0455 0491 0509 0518 0525 0536

VKG 0309 0349 0356 0357

WRC 0296

XAX 0054

XLF 0501

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064

0065 0070 0071 0072 0082 0083 0086 0087 0095 0096 0098

0099 0102 0106 0109 0111 0112 0113 0116 0118 0120 0121

0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162

0165 0171 0172 0177 0181 0195 0200 0206 0209 0211 0219

0222 0223 0224 0226 0229 0230 0231 0232 0234 0238 0240

0241 0244 0247 0248 0249 0250 0251 0253 0254 0255 0256

0258 0259 0261 0262 0265 0266 0267 0269 0271 0272 0275

0276 0277 0279 0281 0283 0284 0285 0286 0287 0288 0290

0291 0293 0294 0295 0296 0299 0300 0301 0303 0305 0306

0308 0309 0311 0312 0313 0314 0315 0316 0317 0320 0322

0323 0324 0326 0328 0330 0333 0334 0337 0338 0339 0340

0342 0343 0344 0345 0346 0348 0349 0350 0351 0353 0356

0357 0358 0361 0362 0364 0365 0366 0368 0369 0370 0372

0375 0380 0382 0384 0386 0388 0389 0392 0393 0396 0397

0398 0400 0401 0403 0404 0405 0407 0408 0409 0412 0418

0419 0420 0421 0422 0423 0425 0427 0428 0432 0437 0439

0441 0443 0444 0448 0451 0452 0454 0455 0456 0458 0461

0462 0463 0465 0466 0469 0472 0473 0476 0477 0479 0480

0481 0484 0486 0487 0489 0490 0491 0493 0494 0496 0497

0498 0500 0501 0503 0504 0505 0506 0507 0508 0509 0510

0511 0512 0513 0515 0516 0518 0519 0521 0522 0524 0525

0526 0527 0529 0530 0532 0533 0535 0536 0539 0542 0548

0549 0550 0551 0552 0553 0555 0558 0564 0565 0567 0568

0570 0571 0573 0576 0578 0579 0581 0584 0587 0588 0591

0597

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 253213D02R02 1

Consumable CMLD01 1

Reidentified part set REIDD01 1

Component COMPD01 1

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletin(s):

Service Bulletin No. A330-25-3161

NOTE: Service Bulletin No. A330-25-3161 (EQUIPMENT/FURNISHING -

PASSENGER COMPARTMENT - INTRODUCTION A MODIFIED INTRUSION

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 4

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SERVICE BULLETIN

AND PENETRATION RESISTANCE COCKPIT DOOR) applies MOD

500014D44099.

C. REASON

(1) History

During the accomplishment of the Service Bulletin No. A340-25-4181

(EQUIPMENT/FURNISHINGS - PASSENGER COMPARTMENT - INTRODUCE A

MODIFIED INTRUSION AND PENETRATION RESISTANCE COCKPIT DOOR), it was

found that the electrical harness 7450VB, installed on the cover of the upper cockpit

door frame, is accessible from the cabin side. Therefore, the protection of this harness

must be improved.

(2) Objective/Action

This Service Bulletin introduces:

- a re-routing of the electrical harness 7450VB

- the installation of a protection plate for the electrical harness 7450VB.

This Service Bulletin has been validated on A340-600 aircraft MSN 0436.

(3) Advantages

Accomplishment of this Service Bulletin improves cockpit security by denying access to

the electrical harness from the cabin side.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 253213-831-848-001: Modification

(1) Removal the Electrical Harness 7450VB and the Cover of the Cockpit Door Frame

(2) Modify the Cover of the Cockpit Door Frame on Bench

(3) Install the Cover and the Electrical Harness 7450VB on the Cockpit Door Frame

Task 253213-831-849-001: Modification - Additional Work for Aircraft Modified by Revision

No. 01 or any Previous Issue

(1) Replace the Fasteners of the Cover

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommended at the earliest opportunity

where manpower and facilities are available.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 253213-831-848-001: Modification

Get Access 3.50

On Aircraft

Removal the Electrical Harness 7450VB and the Cover

of the Cockpit Door Frame

3.00

Modify the Cover of the Cockpit Door Frame on Bench 2.00

Install the Cover and the Electrical Harness 7450VB on

the Cockpit Door Frame

3.00

Tests 3.00

Close-Up 4.00

TOTAL MANHOURS 18.50

ELAPSED TIME (HOURS) 14.00

Task 253213-831-849-001: Modification - Additional Work for Aircraft Modified by Revision No.

01 or any Previous Issue

On Aircraft

Replace the Fasteners of the Cover 1.00

TOTAL MANHOURS 1.00

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 6

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SERVICE BULLETIN

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of

MEW and operator’s items, refer to Weight and Balance Manual (WBM) 01-00-07.

Manufacturers Empty Weight 0.401 KG (+0.8840 LB)

Effect on Balance 4.117 KGM (+29.778 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-16-00 06-20-00 06-31-53

06-41-53 12-34-24 20-21-11

20-21-15 20-28-00 21-26-00

22-96-00 22-97-00 23-72-51

24-41-00 25-13-44 25-23-42

31-50-00 31-60-00 33-13-00

33-14-00 52-51-00

Consumable Material List (CML)

ATA Common Support Data Dictionary (CSDD),

Chapter 2

Elec. Std. Practices Manual (ESPM) 20-33-00 20-33-44 20-44-00

20-51-20 20-52-10 20-52-20

20-52-21 20-54-50 20-55-00

Service Bulletin (SB) A330-25-3161

A340-25-4181

Standards Manual (SM)

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

Weight and Balance Manual (WBM) 01-00-07

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 52-51-00 52-51-11 52-51-12

Aircraft Schematic Manual (ASM) 52-51-00

Illustrated Parts Catalog (IPC) 52-51-01

L. INTERCHANGEABILITY/MIXABILITY

The interchangeability/mixability possibilities are for new or modified parts introduced by the

accomplishment of this Service Bulletin.

DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Cover F2527487100200 F2528716800400 03 Not

Applicable

Cover F2527487100400 F2528716800600 03 Not

Applicable

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DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Cover F2527487100600 F2528716800800 03 Not

Applicable

Cover F2527487101000 F2528716801200 03 Not

Applicable

Cover F2527487101600 F2528716801800 03 Not

Applicable

Cover F2527487101800 F2528716802000 03 Not

Applicable

Cover F2527487102200 F2528716802400 03 Not

Applicable

Cover F2527487102400 F2528716802600 03 Not

Applicable

Cover F2527487102600 F2528716802800 03 Not

Applicable

Cover F2527487102800 F2528716803000 03 Not

Applicable

Cover F2527487103000 F2528716803200 03 Not

Applicable

Cover F2527487103200 F2528716803400 03 Not

Applicable

Cover F2527487103400 F2528716803600 03 Not

Applicable

Cover F2527487103600 F2528716803800 03 Not

Applicable

Cover F2527487104400 F2528716804600 03 Not

Applicable

Cover F2527487104600 F2528716804800 03 Not

Applicable

Cover F2527487104800 F2528716805000 03 Not

Applicable

Cover F2527487105000 F2528716805200 03 Not

Applicable

Cover F2527487105200 F2528716805400 03 Not

Applicable

Cover F2527487105800 F2528716806000 03 Not

Applicable

Cover F2527487600200 F2528717000200 03 Not

Applicable

Cover F2527487601600 F2528717001600 03 Not

Applicable

Cover F2527487603200 F2528717003200 03 Not

Applicable

Cover F2527487604000 F2528717004000 03 Not

Applicable

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DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE

NOTES

Cover F2527487605000 F2528717005000 03 Not

Applicable

Cover F2527487605800 F2528717005800 03 Not

Applicable

Cover F2527487606000 F2528717006000 03 Not

Applicable

Cover F2527487606200 F2528717006200 03 Not

Applicable

Cover F2527487606400 F2528717006400 03 Not

Applicable

Cover F2527487106400 F2528717006400 03 Not

Applicable

Cover F2527487606600 F2528717006600 03 Not

Applicable

Cover F2527487106600 F2528717006600 03 Not

Applicable

Cover F2527487611200 F2528717011200 03 Not

Applicable

Cover F2527487106800 F2528717006800 03 Not

Applicable

Cover F2527487601800 F2528717001800 03 Not

Applicable

NOTE: For definitions of interchangeability codes in column INT., refer to ATA

Common Support Data Dictionary (CSDD), Chapter 2.

M. SPARES

Cover F2527487100200

Cover F2527487100400

Cover F2527487100600

Cover F2527487101000

Cover F2527487101600

Cover F2527487101800

Cover F2527487102200

Cover F2527487102400

Cover F2527487102600

Cover F2527487102800

Cover F2527487103000

Cover F2527487103200

Cover F2527487103400

Cover F2527487103600

Cover F2527487104400

Cover F2527487104600

Cover F2527487104800

Cover F2527487105000

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Cover F2527487105200

Cover F2527487105800

Cover F2527487106400

Cover F2527487106600

Cover F2527487600200

Cover F2527487601600

Cover F2527487601800

Cover F2527487603200

Cover F2527487604000

Cover F2527487605000

Cover F2527487605800

Cover F2527487606000

Cover F2527487606200

Cover F2527487606400

Cover F2527487606600

Cover F2527487611200

The parts listed here must not be installed anymore on aircraft which have accomplished this

Service Bulletin or which have the equivalent production modification embodied.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :

Kit 253213D02R02 AIRBUS Material, Logistics and Suppliers

ATP II B,

Hein-Sass-Weg 24

21129 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

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

Telephone Hotline:

+49 40 743 51616

(2) Price and Availability

Kit 253213D02R02

Cost 260.00 USD

Availability 90 calendar days from receipt of order

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

order. If items are required 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.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 253213D02R02

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

NOTES

3 NAS1833C08-370 4 INSERT

4 MS21250-03012 1 BOLT

5 NSA5379-3C 3 WASHER

6 DAN125-4 4 WASHER

7 NAS1102-08-6 4 SCREW

8 F2527496220200 1 WIREPROT

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

NOTES

9 MS21250-03006 2 BOLT

11 MS21919WCH7 4 CLAMP

12 NAS1096-2-10 4 SCREW

13 MS21042L08 4 NUT

14 NAS1149CN832R 8 WASHER

26 NSA935401-03 3 TIE

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

Epoxy Adhesive-- Legacy 2 05EML8 As required

Non Aqueous Cleaner-General 08BAA9 As required

Textile-Lint Free Cotton 14SBA1 As required

(2) Components

Component COMPD01

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

NOTES

5 NSA5379-3C 3 WASHER

9 MS21250-03006 2 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.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if ADDITIONAL WORK

task is to be accomplished. The quantity of these items are to be ordered

as required.

(3) Equipment

None

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

Reidentified part set REIDD01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

1 F2528716800400 COVER (1) F2527487100200

1 F2528716800600 COVER (1) F2527487100400

1 F2528716800800 COVER (1) F2527487100600

1 F2528716801200 COVER (1) F2527487101000

1 F2528716801800 COVER (1) F2527487101600

1 F2528716802000 COVER (1) F2527487101800

1 F2528716802400 COVER (1) F2527487102200

1 F2528716802600 COVER (1) F2527487102400

1 F2528716802800 COVER (1) F2527487102600

1 F2528716803000 COVER (1) F2527487102800

1 F2528716803200 COVER (1) F2527487103000

1 F2528716803400 COVER (1) F2527487103200

1 F2528716803600 COVER (1) F2527487103400

1 F2528716803800 COVER (1) F2527487103600

1 F2528716804600 COVER (1) F2527487104400

1 F2528716804800 COVER (1) F2527487104600

1 F2528716805000 COVER (1) F2527487104800

1 F2528716805200 COVER (1) F2527487105000

1 F2528716805400 COVER (1) F2527487105200

1 F2528716806000 COVER (1) F2527487105800

1 F2528717000200 COVER (1) F2527487600200

1 F2528717001600 COVER (1) F2527487601600

1 F2528717001800 COVER (1) F2527487601800

1 F2528717003200 COVER (1) F2527487603200

1 F2528717004000 COVER (1) F2527487604000

1 F2528717005000 COVER (1) F2527487605000

1 F2528717005800 COVER (1) F2527487605800

1 F2528717006000 COVER (1) F2527487606000

1 F2528717006200 COVER (1) F2527487606200

1 F2528717006400 COVER (1) F2527487106400

(1) F2527487606400

1 F2528717006600 COVER (1) F2527487106600

(1) F2527487606600

1 F2528717006800 COVER (1) F2527487106800

1 F2528717011200 COVER (1) F2527487611200

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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F. TOOLING

None

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 253213-831-848-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

CAUTION: BEFORE YOU DO WORK ON THE ELECTRICAL CIRCUIT AT THE REAR OF

A CIRCUIT BREAKER PANEL, OPEN THE CIRCUIT BREAKER 2XD(PANEL

721VU POSITION X5). THEN REMOVE THE CBMU FROM THE RACK. IF YOU

DO NOT OBEY THIS PRECAUTION, THERE IS A RISK OF DAMAGE TO THE

CBMU FROM UNWANTED VOLTAGE INJECTION.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

’refer to’ are used and the operator has procedure accepted by the local authorities

he belongs to, the accepted alternative procedure can be used. When the words ’in

accordance with’ are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin contains the instructions for the on-aircraft maintenance

necessary to ensure the continued airworthiness of the aircraft.

For any deviations to the instructions contained herein, contact Airbus for repair

instructions and approval.

NOTE: Discarded parts must be managed at the operator’s discretion.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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Task Associated Data

Zone

From 210 to 220

Modified FIN

317LG 7450VB

Access

Door 831 841

Manpower

TOTAL MANHOURS 18.50

ELAPSED TIME (HOURS) 14.00

A. GENERAL

(1) Subtask 253213-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 06-16-00-912-801

06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-15-912-801

Task 20-28-00-912-802

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-00

20-33-44

20-51-20

20-52-10

20-54-50

Structural Repair Manual (SRM) 51-42-00

51-44-00

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

(b) For identification of the zones, refer to AMM 06-20-00, Page Block 001.

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

(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Material List (CML).

(e) For circuit breaker safety practices, refer to AMM Task 06-16-00-912-801.

(f) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

(g) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(h) For the cable tie application and tooling, refer to ESPM 20-33-44.

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(i) For the protection of the connectors, contacts and terminals, refer to ESPM

20-54-50.

(j) Do a check of the electrical connectors before you connect them, refer to ESPM

20-52-10.

(k) Remove and install fasteners in accordance with SRM 51-42-00.

(l) To torque tighten the electrical component fasteners, refer to AMM Task

20-21-15-912-801.

(m) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(n) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(2) Subtask 253213-900-202-001 - Administrative

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

Service Bulletin.

B. PREPARATION

(1) Subtask 253213-941-201-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

Task 23-72-51-000-801

Task 25-13-44-000-801

Task 25-23-42-000-801

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

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- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) If installed, remove the Anti Hijack Camera 12RA, refer to AMM Task

23-72-51-000-801.

(c) Remove the ceiling and sidewall panels 211MC, refer to AMM 06-41-53, Page

Block 001 and AMM Task 25-13-44-000-801.

(d) Remove the cover panels 221AC, refer to AMM 06-41-53, Page Block 001 and

AMM Task 25-23-42-000-801.

(e) In the cockpit, on the overhead panel, remove all the blanking plates necessary to

get access to the modification of the equipment and wiring.

(2) Subtask 253213-862-201-001 - De-Energize Electrical

Manpower Resources

Skills NON SPECIFIC

(a) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, 2, APU GEN,

- EXT A (B).

(b) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(c) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panel:

- 211VU (EMER ELEC PWR),

- 235VU (ELEC).

(d) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to

start the APU.

(e) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR A (B).

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(f) Make sure that there is warning notice at the access door 121EL to tell persons not

to connect the external power connector(s).

C. PROCEDURE

(1) Subtask 253213-010-201-001 - Removal the Electrical Harness 7450VB and the

Cover of the Cockpit Door Frame

Work Zones and Access Panels

Zone Access/Work location

From 210 Access Door 831, Door 841

To 220

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

References

Elec. Std. Practices Manual (ESPM) 20-33-00

Structural Repair Manual (SRM) 51-42-00

Fig. A-GBAAA

Removal of the Electrical Harness

7450VB

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Fig. A-GWAAA

Wiring of the Electrical Harness 7450VB,

pre SB A330-25-3213

Sheet 01

Fig. A-GWBAA

Wiring of the Electrical Harness 7450VB,

post SB A330-25-3213

Sheet 01

Fig. A-GBCAA

Modification of the Cover of the Cockpit

Door Frame

Sheet 01

Sheet 02

Fig. A-GBBAA

Removal of the Cover from the Cockpit

Door Frame

Sheet 01

Sheet 02

(a) From the secure part, Item (28) of the RH cockpit door post, remove in accordance

with SRM 51-42-00 and as shown on Fig. A-GBAAA Sheet 04, View E:

1 Cover Item (20) Retain

and

2 Screw Item (21) Retain

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(b) Modify the wiring:

Refer to Fig. A-GBAAA Sheet 04, View F and ESPM 20-33-00

1 Disconnect the plug 25MQA from the key pad 25MQ.

2 From the plug 25MQA, remove:

1 Cable Tie Item (26) Discard

1 Plug Cover Item (27) Retain

2 Screw With Clamp Item (25) Retain

3 Remove the wires of the electrical harness 7450VB, Item (2), from the plug

25MQA.

(c) From the RH cockpit door post, remove in accordance with SRM 51-42-00 and as

shown on Fig. A-GBAAA Sheet 02, Fig. A-GBAAA Sheet 03 and Fig. A-GBAAA

Sheet 04, View G, H and J:

1 Secure Part Item (28) Retain

1 Cover Plate Item (29) Retain

attached with:

6 Screw Item (30) Retain

5 Spacer Item (31) Retain

attached with:

10 Screw Item (32) Retain

6 Clamp Item (35) Retain

3 Clamp Item (36) Retain

9 Spacer Item (37) Retain

attached with:

9 Screw Item (33) Retain

9 Washer Item (34) Retain

NOTE: Remove and retain the spacers, Item (37), if installed.

(d) Modify the wiring

Refer to ESPM 20-33-00.

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1 Disconnect the wires of the electrical harness 7450VB, Item (2), from the

release latches 30MQ, 31MQ and 32MQ as shown on Fig. A-GBAAA Sheet

01 and Fig. A-GWAAA.

2 If installed, disconnect the electrical harness 7450VB from the circuit breaker

box 40MQ as shown on Fig. A-GBAAA Sheet 05, View L and Fig. A-GWBAA.

(e) From the cover, Item (1), remove in accordance with SRM 51-42-00 and as shown

on Fig. A-GBAAA Sheet 02 and Fig. A-GBAAA Sheet 05, View K:

FIN 317LG

1 Limit Switch Item (38) Retain

attached with:

2 Screw Item (39) Retain

As

required

Cable Tie Item (40) Discard

(f) Modify the wiring

Refer to ESPM 20-33-00

1 Disconnect the wires of the electrical harness 7450VB from the Limit Switch

317LG, Item (38), as shown on Fig. A-GBAAA Sheet 05, View K.

2 Remove the electrical harness 7450VB, Item (2), from the cover of the cockpit

door frame, Item (1), as shown on Fig. A-GBAAA Sheet 02, in accordance

with SRM 51-42-00:

(g) From the cockpit door frame, remove in accordance with SRM 51-42-00 and as

shown on Fig. A-GBBAA Sheet 02:

3 Cover Item (45) Retain

1 Cover Item (1) Retain

attached with:

1 Screw Item (41) Discard

1 Washer Item (43) Discard

and

2 Screw Item (42) Discard

2 Washer Item (44) Discard

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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(h) From the cover, Item (1), remove as shown on Fig. A-GBCAA Sheet 01:

5 Cable Mount Item (46) Discard

(2) Subtask 253213-831-203-001 - Modify the Cover of the Cockpit Door Frame on

Bench

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 253213D02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 NAS1833C08-370 4 INSERT

Reidentified part set REIDD01

ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

1 F2528716800400 COVER (1) F2527487100200

1 F2528716800600 COVER (1) F2527487100400

1 F2528716800800 COVER (1) F2527487100600

1 F2528716801200 COVER (1) F2527487101000

1 F2528716801800 COVER (1) F2527487101600

1 F2528716802000 COVER (1) F2527487101800

1 F2528716802400 COVER (1) F2527487102200

1 F2528716802600 COVER (1) F2527487102400

1 F2528716802800 COVER (1) F2527487102600

1 F2528716803000 COVER (1) F2527487102800

1 F2528716803200 COVER (1) F2527487103000

1 F2528716803400 COVER (1) F2527487103200

1 F2528716803600 COVER (1) F2527487103400

1 F2528716803800 COVER (1) F2527487103600

1 F2528716804600 COVER (1) F2527487104400

1 F2528716804800 COVER (1) F2527487104600

1 F2528716805000 COVER (1) F2527487104800

1 F2528716805200 COVER (1) F2527487105000

1 F2528716805400 COVER (1) F2527487105200

1 F2528716806000 COVER (1) F2527487105800

1 F2528717000200 COVER (1) F2527487600200

1 F2528717001600 COVER (1) F2527487601600

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ITEM NEW PART N ̊ KEYWORD ITEM OLD PART N ̊ SEE

NOTES

1 F2528717001800 COVER (1) F2527487601800

1 F2528717003200 COVER (1) F2527487603200

1 F2528717004000 COVER (1) F2527487604000

1 F2528717005000 COVER (1) F2527487605000

1 F2528717005800 COVER (1) F2527487605800

1 F2528717006000 COVER (1) F2527487606000

1 F2528717006200 COVER (1) F2527487606200

1 F2528717006400 COVER (1) F2527487106400

(1) F2527487606400

1 F2528717006600 COVER (1) F2527487106600

(1) F2527487606600

1 F2528717006800 COVER (1) F2527487106800

1 F2528717011200 COVER (1) F2527487611200

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Adhesive-- Legacy 2 05EML8

Non Aqueous CleanerGeneral08BAA9

Textile-Lint Free Cotton 14SBA1

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-GBBAA

Removal of the Cover from the Cockpit

Door Frame

Sheet 01

Sheet 02

Fig. A-GBCAA

Modification of the Cover of the Cockpit

Door Frame

Sheet 01

Sheet 02

Fig. A-GBDAA

Installation of the Cover on the Cockpit

Door Frame

Sheet 01

Sheet 02

(a) Cut out the cable channels in the upper edge of the cover, Item (1), to the shape

that the electrical harness 7450VB can lead in a 90 degrees angle to the FWD

direction, as shown on Fig. A-GBCAA Sheet 02, View A and View B.

(b) Round the edges of the cable channel as shown Fig. A-GBCAA Sheet 02, View A

and View B.

(c) Drill four holes to the diameter of 14.5 mm (0.57 in.) in the upper edge of the cover,

Item (1), as shown on Fig. A-GBCAA Sheet 02, View C and Section A-A in

accordance with SRM 51-44-00.

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(d) Deburr the holes in accordance with SRM 51-44-00 and clean the contact surfaces

with:

Textile-Lint Free

Cotton

14SBA1 As required

made moist with:

Non Aqueous

Cleaner-General

08BAA9 As required

(e) In the upper edge of the cover, Item (1), install, as shown on Fig. A-GBCAA Sheet

02, View C and Section A-A:

4 Insert NAS1833C08-370 Item 3

with:

Epoxy Adhesive--

Legacy 2

05EML8 As required

(f) Re-identify the cover, Item (1):

1 Cover F2527487100200 Item (1)

becomes:

1 Cover F2528716800400 Item 1

or

1 Cover F2527487100400 Item (1)

becomes:

1 Cover F2528716800600 Item 1

or

1 Cover F2527487100600 Item (1)

becomes

1 Cover F2528716800800 Item 1

or

1 Cover F2527487101000 Item (1)

becomes:

1 Cover F2528716801200 Item 1

or

1 Cover F2527487101600 Item (1)

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becomes:

1 Cover F2528716801800 Item 1

or

1 Cover F2527487101800 Item (1)

becomes:

1 Cover F2528716802000 Item 1

or

1 Cover F2527487102200 Item (1)

becomes:

1 Cover F2528716802400 Item 1

or

1 Cover F2527487102400 Item (1)

becomes:

1 Cover F2528716802600 Item 1

or

1 Cover F2527487102600 Item (1)

becomes:

1 Cover F2528716802800 Item 1

or

1 Cover F2527487102800 Item (1)

becomes:

1 Cover F2528716803000 Item 1

or

1 Cover F2527487103000 Item (1)

becomes:

1 Cover F2528716803200 Item 1

or

1 Cover F2527487103200 Item (1)

becomes:

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1 Cover F2528716803400 Item 1

or

1 Cover F2527487103400 Item (1)

becomes:

1 Cover F2528716803600 Item 1

or

1 Cover F2527487103600 Item (1)

becomes:

1 Cover F2528716803800 Item 1

or

1 Cover F2527487104400 Item (1)

becomes:

1 Cover F2528716804600 Item 1

or

1 Cover F2527487104600 Item (1)

becomes:

1 Cover F2528716804800 Item 1

or

1 Cover F2527487104800 Item (1)

becomes:

1 Cover F2528716805000 Item 1

or

1 Cover F2527487105000 Item (1)

becomes:

1 Cover F2528716805200 Item 1

or

1 Cover F2527487105200 Item (1)

becomes:

1 Cover F2528716805400 Item 1

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or

1 Cover F2527487105800 Item (1)

becomes:

1 Cover F2528716806000 Item 1

or

1 Cover F2527487600200 Item (1)

becomes:

1 Cover F2528717000200 Item 1

or

1 Cover F2527487601600 Item (1)

becomes:

1 Cover F2528717001600 Item 1

or

1 Cover F2527487601800 Item (1)

becomes:

1 Cover F2528717001800 Item 1

or

1 Cover F2527487603200 Item (1)

becomes:

1 Cover F2528717003200 Item 1

or

1 Cover F2527487604000 Item (1)

becomes:

1 Cover F2528717004000 Item 1

or

1 Cover F2527487605000 Item (1)

becomes:

1 Cover F2528717005000 Item 1

or

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1 Cover F2527487605800 Item (1)

becomes:

1 Cover F2528717005800 Item 1

or

1 Cover F2527487606000 Item (1)

becomes:

1 Cover F2528717006000 Item 1

or

1 Cover F2527487606200 Item (1)

becomes:

1 Cover F2528717006200 Item 1

or

1 Cover F2527487606400 Item (1)

becomes:

1 Cover F2528717006400 Item 1

or

1 Cover F2527487606600 Item (1)

becomes:

1 Cover F2528717006600 Item 1

or

1 Cover F2527487611200 Item (1)

becomes:

1 Cover F2528717011200 Item 1

or

1 Cover F2527487106400 Item (1)

becomes:

1 Cover F2528717006400 Item 1

or

1 Cover F2527487106600 Item (1)

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becomes:

1 Cover F2528717006600 Item 1

or

1 Cover F2527487106800 Item (1)

becomes:

1 Cover F2528717006800 Item 1

(3) Subtask 253213-420-201-001 - Install the Cover and the Electrical Harness 7450VB

on the Cockpit Door Frame

Work Zones and Access Panels

Zone Access/Work location

From 210 Access Door 831, Door 841

To 220

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 253213D02R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 MS21250-03012 1 BOLT

5 NSA5379-3C 3 WASHER

6 DAN125-4 4 WASHER

7 NAS1102-08-6 4 SCREW

8 F2527496220200 1 WIREPROT

9 MS21250-03006 2 BOLT

11 MS21919WCH7 4 CLAMP

12 NAS1096-2-10 4 SCREW

13 MS21042L08 4 NUT

14 NAS1149CN832R 8 WASHER

26 NSA935401-03 3 TIE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Elec. Std. Practices Manual (ESPM) 20-33-00

20-33-44

20-44-00

20-52-21

Structural Repair Manual (SRM) 51-42-00

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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References

Fig. A-GBDAA

Installation of the Cover on the Cockpit

Door Frame

Sheet 01

Sheet 02

Fig. A-GBEAA

Installation of the Electrical Harness

7450VB

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

Fig. A-GWAAA

Wiring of the Electrical Harness 7450VB,

pre SB A330-25-3213

Sheet 01

Fig. A-GWBAA

Wiring of the Electrical Harness 7450VB,

post SB A330-25-3213

Sheet 01

(a) Install the re-identified cover, Item 1, in accordance with SRM 51-42-00 and as

shown on Fig. A-GBDAA Sheet 02, with:

2 Bolt MS21250-03006 Item 9

2 Washer NSA5379-3C Item 5

and

1 Screw MS21250-03012 Item 4

1 Washer NSA5379-3C Item 5

(b) Install on the cover, Item 1, in accordance with SRM 51-42-00 and as shown on

Fig. A-GBDAA Sheet 02:

3 Cover Item (45) Retained at

removal

(c) Lead the electrical harness 7450VB, Item (2), to the cover of the cockpit door frame

and the RH cockpit door post, as shown on Fig. A-GBEAA Sheet 02, and Fig. AGBEAA Sheet 07, View L.

(d) Connect the electrical harness 7450VB:

Refer to ESPM 20-33-00

1 Connect the wires of the electrical harness 7450VB, Item (2), to the release

latches 30MQ, 31MQ and 32MQ, as shown on Fig. A-GBEAA Sheet 01, Fig.

A-GBEAA Sheet 03 and on this Wiring Diagram, Fig. A-GWAAA.

2 If installed, connect the wires of the electrical harness 7450VB, Item (2), to the

circuit breaker box 40MQ as shown on Fig. A-GBEAA Sheet 04 and on this

Wiring Diagram, Fig. A-GWBAA

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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3 Attach the wires, as shown on Fig. A-GBEAA Sheet 02, Fig. A-GBEAA Sheet

03, View D, E, F and Fig. A-GBEAA Sheet 04.

4 Connect the wires of the electrical harness 7450VB, Item (2), to the limit

switch 317LG, Item (38), as shown on this Wiring Diagram, Fig. A-GWBAA.

5 Attach the additional wire length in a loop to the electrical harness 7450VB, as

shown on Fig. A-GBEAA Sheet 07, View L, with:

Refer to ESPM 20-33-44

2 Cable Tie NSA935401-03 Item 26

(e) Install on the cover, Item 1, in accordance with SRM 51-42-00 and as shown on

Fig. A-GBEAA Sheet 07, View L:

FIN 317LG

1 Limit Switch Item (38) Retained at

removal

attach with:

2 Screw Item (39) Retained at

removal

(f) Install on the RH cockpit door post, in accordance with SRM 51-42-00 and as

shown on Fig. A-GBEAA Sheet 02, Fig. A-GBEAA Sheet 03, View D, E, F and Fig.

A-GBEAA Sheet 04:

Refer to AMM Task 20-21-11-911-801

6 Clamp Item (35) Retained at

removal

3 Clamp Item (36) Retained at

removal

9 Spacer Item (37) Retained at

removal

attach with:

9 Screw Item (33) Retained at

removal

9 Washer Item (34) Retained at

removal

NOTE: Install the spacers, Item (37), if retained at removal.

5 Spacer Item (31) Retained at

removal

attach with:

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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10 Screw Item (32) Retained at

removal

1 Secure Part Item (28) Retained at

removal

1 Cover Plate Item (29) Retained at

removal

attach with:

6 Screw Item (30) Retained at

removal

NOTE: Before you install the secure part, Item (38), and the cover plate,

Item (29), lead the wires of the key pad plug 25MQA through the

hole of the secure part and cover plate as shown on Fig. A-GBEAA

Sheet 06, View J.

(g) To the plug 25MQA, connect the wires and install as shown on Fig. A-GBEAA

Sheet 06, View K:

Refer to ESPM 20-33-44

1 Plug Cover Item (27) Retained at

removal

2 Screw with clamps Item (25) Retained at

removal

1 Cable Tie NSA935401-03 Item 26

(h) Connect the plug 25MQA to the key pad 25MQ, refer to ESPM 20-44-00.

(i) Install on the secure part of the RH cockpit door post, Item (28), in accordance with

SRM 51-42-00 and as shown on Fig. A-GBEAA Sheet 02 and Fig. A-GBEAA Sheet

06, View J:

1 Cover Item (20) Retained at

removal

attach with:

2 Screw Item (21) Retained at

removal

(j) Install on the cover, Item 1, in accordance with SRM 51-42-00 and as shown on

Fig. A-GBEAA Sheet 07, View L and N:

1 Wire Protection F2527496220200 Item 8

attach with:

4 Screw NAS1102-08-6 Item 7

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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4 Washer DAN125-4 Item 6

4 Screw NAS1096-2-10 Item 12

8 Washer NAS1149CN832R Item 14

4 Clamp MS21919WCH7 Item 11

4 Nut MS21042L08 Item 13

(k) Do a continuity test of the modified electrical wires, refer to ESPM 20-52-21.

D. TEST

(1) Subtask 253213-861-201-001 - Energize Electrical Network

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

(a) Job Set-up:

1 In the cockpit, on the panel 235VU, push these pushbutton switches:

- GEN 1, GEN 2,

- APU GEN (only if the A/C is energized from the external power).

2 Remove the warning notices.

3 Energize the aircraft electrical circuits, ref to AMM Task 24-41-00-861-801.

NOTE: If the A/C is energized from the external power, make sure that

the pushbutton switches BAT 1, BAT 2, APU BAT and EXT A

(B) are pushed.

NOTE: If the A/C is energized from APU, make sure that the

pushbutton switches BAT 1, BAT 2, APU BAT and APU GEN

are pushed.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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4 Remove the safety clips and/or tags and close/unlock tag these circuit

breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742VU 701PP 10PB1 72 S

742VU 702PP 10PB2 71 S

(b) Preliminary Tests:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test requested by this

ESPM procedure is given hereafter.

2 Do the Operational Test of the Instrument and Panel Integral Lighting, refer to

AMM Task 33-13-00-710-801.

3 Do the Operational Test of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the Operational Test of the Avionics-Equipment Ventilation System, refer to

AMM Task 21-26-00-710-803.

5 Do the Bite Test of the Auto Flight System (SYSTEM TEST), refer to AMM

Task 22-96-00-740-801.

6 Do the Operational Test of the Electronic Centralized Aircraft Monitoring

(ECAM) Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the Flight Warning System (FWS), refer to AMM Task

31-50-00-740-801.

8 Do the Operational Test of the Electronic Instrument System (EIS), refer to

AMM Task 31-60-00-710-802.

(2) Subtask 253213-700-209-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-51-00-710-801

Task 52-51-00-710-802

Task 52-51-00-710-803

Task 52-51-00-710-805

(a) Do the operational test of the Cockpit Door Lock System (CDLS), refer to AMM

Task 52-51-00-710-801.

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(b) Do the operational test of the cockpit door routine access, refer to AMM Task

52-51-00-710-802.

(c) Do the operational test of the cockpit door emergency access, refer to AMM Task

52-51-00-710-803.

(d) Do the functional decompression test on the control box 24MQ, refer to AMM Task

52-51-00-710-805.

E. CLOSE-UP

(1) Subtask 253213-942-209-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 23-72-51-400-801

(a) Install the Anti Hijack Camera 12RA (if removed on SUBTASK 253213-941-201 001

Job Set-up ), refer to AMM Task 23-72-51-400-801.

(b) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(c) Remove the access platform(s).

(d) Put the aircraft back to its initial configuration.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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This Page Intentionally Left Blank

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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Task 253213-831-849-001 - Modification - Additional Work for Aircraft Modified by Revision

No. 01 or any Previous Issue

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

’refer to’ are used and the operator has procedure accepted by the local authorities

he belongs to, the accepted alternative procedure can be used. When the words ’in

accordance with’ are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin contains the instructions for the on-aircraft maintenance

necessary to ensure the continued airworthiness of the aircraft.

For any deviations to the instructions contained herein, contact Airbus for repair

instructions and approval.

NOTE: Discarded parts must be managed at the operator’s discretion.

Task Associated Data

Zone

210

Manpower

TOTAL MANHOURS 1.00

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

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A. GENERAL

(1) Subtask 253213-910-202-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

Structural Repair Manual (SRM) 51-42-00, Page Block 001

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

(b) For identification of the zones, refer to AMM 06-20-00, Page Block 001.

(c) Remove and install fasteners, in accordance with SRM 51-42-00, Page Block 001.

(d) Put all retained hardware in identified plastic bags and attach the bags to the

related unit.

(2) Subtask 253213-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 253213-941-202-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 38

6

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@A330

SERVICE BULLETIN

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

C. PROCEDURE

(1) Subtask 253213-831-204-001 - Replace the Fasteners of the Cover

Work Zones and Access Panels

Zone Access/Work location

210 Work location Frame 11

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPD01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 NSA5379-3C 3 WASHER

9 MS21250-03006 2 BOLT

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only necessary if ADDITIONAL WORK

task is to be accomplished. The quantity of these items are to be ordered

as required.

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-GBFAA

Replacement of the Fasteners of the

Cover of the Cockpit Door Frame -

ADDITIONAL WORK

Sheet 01

Sheet 02

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 39

6

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

SERVICE BULLETIN

(a) Remove, refer to Fig. A-GBFAA:

1 Remove from the cover, Item (1), in accordance with SRM 51-42-00 and as

shown on Fig. A-GBFAA Sheet 01, view A and Fig. A-GBFAA Sheet 02, view

B:

3 Cover Item (45) Retain

2 Screw Item (9) Discard

2 Washer Item (10) Discard

1 Screw Item (4) Retain

1 Washer Item (5) Discard

(b) Install, refer to Fig. A-GBFAA:

1 Install in the cover, Item (1), in accordance with SRM 51-42-00, as shown on

Fig. A-GBFAA Sheet 01, view A and Fig. A-GBFAA Sheet 02, view B:

2 Bolt MS21250-03006 Item 9

2 Washer NSA5379-3C Item 5

1 Screw Item (4) Retained at

removal

1 Washer NSA5379-3C Item 5

2 Install on the cover, Item (1), in accordance with SRM 51-42-00, as shown on

Fig. A-GBFAA Sheet 01, view A and Fig. A-GBFAA Sheet 02, view B:

3 Cover Item (45) Retained at

removal

D. TEST

None

E. CLOSE-UP

(1) Subtask 253213-942-210-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Make sure that the work areas are clean and clear of tools and other items or

equipment.

(b) Put the aircraft back to its initial configuration.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 40

6

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

SERVICE BULLETIN

**CONF ALL

FR16A

FR12

B

B

32MQ

31MQ

30MQ

25MQ−A

KEYPAD 25MQ

317LG

6296VS

6294VS

6295VS

FR11

A

C

A

Z220

40MQ

6297VS

1

1

NOTE:

INSTALLED AFTER ACCOMPLISHMENT

OF SERVICE BULLETIN A330−25−3215.

G_SB_253213_6_BAAA_01_00

Figure A-GBAAA - Sheet 01

Removal of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 41

6

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

SERVICE BULLETIN

**CONF ALL

6296VS

6295VS

7450VB

G

G

G

G

G

E

D

C

J

H

H

J

J

6294VS

H

H

H

H

5128VN

TO 1181VC−A

5259VN5199VN

(1)

(40)

(2)

(28)

(29)

(2)

7450VB

6297VS

40MQ

K

L

1

NOTE:

INSTALLED AFTER ACCOMPLISHMENTOF SERVICE BULLETIN A330−25−3215.

1

(20)

G_SB_253213_6_BAAA_02_00

Figure A-GBAAA - Sheet 02

Removal of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 42

6

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

SERVICE BULLETIN

**CONF ALL

(6 POS.)

D

(29) (28)

(30)

G_SB_253213_6_BAAA_03_00

Figure A-GBAAA - Sheet 03

Removal of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 43

6

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

SERVICE BULLETIN

**CONF ALL

E

25MQ−A

F

25MQ−A

F

(25) (25)

(20)

7450VB

(21) (26)

(27)

(2) (2)

G

7450VB

(2)

(31)

(32)

H J

(37)

(34)

(33)

(35)

(36)

2

2

NOTE:

REMOVE THE SPACER, ITEM (37), IF INSTALLED

(28)

VIEW H

VIEW J

G_SB_253213_6_BAAA_04_00

Figure A-GBAAA - Sheet 04

Removal of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 44

6

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

SERVICE BULLETIN

**CONF ALL

40MQ

6297VS−B,D,F

L

(2)

K

317LG

(38)

(39)

1

NOTE:

INSTALLED AFTER ACCOMPLISHMENT

OF SERVICE BULLETIN A330−25−3215.

1

(1)

7450VB

G_SB_253213_6_BAAA_05_00

Figure A-GBAAA - Sheet 05

Removal of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 45

6

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

SERVICE BULLETIN

**CONF ALL

FR16A

FR12

A

B

B

C

(1)

A

Z220

G_SB_253213_6_BBAA_01_00

Figure A-GBBAA - Sheet 01

Removal of the Cover from the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 46

6

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

SERVICE BULLETIN

**CONF ALL

C

(45)

(41)

(45)

(42)

(43)

(45)

(44)

(1)

G_SB_253213_6_BBAA_02_00

Figure A-GBBAA - Sheet 02

Removal of the Cover from the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 47

6

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

SERVICE BULLETIN

**CONF ALL

(1)

(46)

BEFORE

(1)

AFTER

A

B

C

G_SB_253213_6_BCAA_01_00

Figure A-GBCAA - Sheet 01

Modification of the Cover of the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 48

6

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

SERVICE BULLETIN

**CONF ALL (0.51in.) 13.0mm

(0.35in.)

R 9.0mm

(0.50in.)

12.6mm

EDGES ROUNDED

EXISTING

DUCT

(0.24in.)

6.0mm

(0.56in.)

(14.3mm)

(0.20in.)

R 5.0mm

DUCT

EXISTING

A

B

(4.65in.)

118.0mm

(12.72in.)

323.0mm

(17.96in.)

458.0mm

(20.79in.)

528.0mm

(0.46in.)

11.6mm

A A

C

(0.57in.)

14.5mm DIA

(0.38in.)

9.5mm

ADHESIVE

(MAT.NO.08−010A)

SECTION

A A

3

(1)

(1)

(1)

3 3 3

EDGES ROUNDED

G_SB_253213_6_BCAA_02_00

Figure A-GBCAA - Sheet 02

Modification of the Cover of the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 49

6

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

SERVICE BULLETIN

**CONF ALL

FR16A

FR12

A

B

B

C

(1)

A

Z220

G_SB_253213_6_BDAA_01_00

Figure A-GBDAA - Sheet 01

Installation of the Cover on the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 50

6

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

SERVICE BULLETIN

**CONF ALL

C

(45)

4

(45)

9

5

(45)

5

(1)

G_SB_253213_6_BDAA_02_01

Figure A-GBDAA - Sheet 02

Installation of the Cover on the Cockpit Door Frame

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 51

6

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

SERVICE BULLETIN

**CONF ALL

FR16A

FR12

B

B

FR11

A

C

A

Z220

32MQ

31MQ

30MQ

25MQ−A

KEYPAD 25MQ

317LG

6296VS

6294VS

6295VS

40MQ

6297VS

1

1

NOTE:

INSTALLED AFTER ACCOMPLISHMENT

OF SERVICE BULLETIN A330−25−3215.

G_SB_253213_6_BEAA_01_00

Figure A-GBEAA - Sheet 01

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 52

6

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

SERVICE BULLETIN

**CONF ALL

6296VS

6295VS

7450VB

D

D

D

D

D

J

H

C

F

E

E

F

F

6294VS

E

E

E

E

(28)

(29)

7450VB

(2)

(2)

L

6297VS

40MQ

G

1

OF SERVICE BULLETIN A330−25−3215.INSTALLED AFTER ACCOMPLISHMENT 1

NOTE:

(20)

(1)

G_SB_253213_6_BEAA_02_00

Figure A-GBEAA - Sheet 02

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 53

6

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

SERVICE BULLETIN

**CONF ALL

D

7450VB

E F

(2)

(31)

(37)

(34)

(33)

(35)

(36)

(32) 2

2

NOTE:

INSTALL THE SPACER, ITEM (37) IF REMOVED.

6295VS C 5251−5165 (YY24) 4

32MQ

2

1

5

(YY24) 6

5251−5163 (YY18)

6295VS E 5251−5164

7450VB 6295VS D

6295VS A 5251−5162 (YY20)

6295VS B 5251−5161 (YY20)

6294VS C

6294VS E

4

6

5251−5159

5251−5160

(YY24)

(YY24)

2

1

5

(YY24) 7

5251−5157 (YY18)

6294VS F 5251−5158

6294VS D

6294VS A 5251−5156 (YY20)

6294VS B 5251−5155 (YY20)

31MQ

6296VS C 5251−5154 (YY24) 4

2

1

5

(YY24) 6

5251−5152 (YY18)

6296VS E

6296VS D

6296VS A 5251−5151 (YY20)

6296VS B 5251−5150 (YY20)

30MQ

5251−5153

7450VB

7450VB

VIEW E

VIEW F

G_SB_253213_6_BEAA_03_00

Figure A-GBEAA - Sheet 03

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 54

6

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

SERVICE BULLETIN

**CONF ALL

40MQ

6297VS−B,D,F

G

(2)

CONNECTION

CA

L1

5251−5194

5251−5195

6297VS D

6297VS E

U1

UA

C1

5251−5192

6297VS C 5251−5193 7450VB

6297VS A 5251−5191

40MQ

6297VS F 5251−5196 LA

6297VS B

5251−5120

5251−5199

5251−5115

5251−5198

5251−5111

5251−5197

G_SB_253213_6_BEAA_04_00

Figure A-GBEAA - Sheet 04

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 55

6

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

SERVICE BULLETIN

**CONF ALL

(6 POS.)

H

(29) (28)

(30)

G_SB_253213_6_BEAA_05_00

Figure A-GBEAA - Sheet 05

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 56

6

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

SERVICE BULLETIN

**CONF ALL

J

25MQ−A

K

25MQ−A

K

(25) (25)

(20)

7450VB

(21)

26

(27)

(2)

(2)

1 5251−7900 R

2 5251−7900 B

3 5251−7901 R

4 5251−7901 B

7 5251−5102

8 5251−5101

9 5251−5107

10 5251−5108

11 5251−5104

15 5251−5100

25MQ

−

A

CONNECTION

7450VB

7450VB

7450VB

7450VB

7450VB

7450VB

7450VB

7450VB

7450VB

7450VB

G_SB_253213_6_BEAA_06_01

Figure A-GBEAA - Sheet 06

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 57

6

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

SERVICE BULLETIN

**CONF ALL

L

317LG FROM 30MQ

31MQ

32MQ

25MQ

5128VN

TO 1181VC−A

5259VN

5199VN

7450VB

26

N

N

N

N

6

7

8

13

14

8

12

14

11

(2)

(2)

N

4

3

(38)

(39)

3 ATTACH THE ADDITIONAL

4 ADD 200.0mm (7,87in.)

WIRE LENGHT IN A LOOP

TO THE ELECTRICAL HARNESS.

TO THE INSTALLATION LENGHT

OF THE WIRE.

1

NOTE:

INSTALLED AFTER ACCOMPLISHMENT

OF SERVICE BULLETIN A330−25−3215.

1 40MQ

(1)

G_SB_253213_6_BEAA_07_01

Figure A-GBEAA - Sheet 07

Installation of the Electrical Harness 7450VB

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 58

6

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@A330

SERVICE BULLETIN

**CONF ALL

A

FR16A

Z220

Z210

A

FR11

B

G_SB_253213_6_BFAA_01_00

Figure A-GBFAA - Sheet 01

Replacement of the Fasteners of the Cover of the Cockpit Door Frame - ADDITIONAL WORK

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 59

6

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

SERVICE BULLETIN

**CONF ALL

(1)

(45)

(45)

(45)

(9)

9

(10)

5

(4) (5)

5

B

G_SB_253213_6_BFAA_02_00

Figure A-GBFAA - Sheet 02

Replacement of the Fasteners of the Cover of the Cockpit Door Frame - ADDITIONAL WORK

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 60

6

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@A330

SERVICE BULLETIN

**CONF ALL

15

8

 B2

5199VN1

7

25MQ

KEYPAD

LED2

5102−CF18

1181VC A

DATA3

DATA2

DATA1

DATA0

4

3

2

1

GND

VCC

10

9 LED1

7901−TK24

7902−SJ20

7903−SJ20

7904−SJ20

A

7900−TK24

5111−CF20

5115−CF20

5120−CF20

5

6

12

13

11

14

−S

−T

−R

−Q

−N

W

−K

−J

−I

−H

−G

−F

−E

−D

−C

−B

−A

Z

Y

X

−M

−P

30MQ

UPPER RELEASE LATCH

31MQ

CENTER RELEASE LATCH

32MQ

LOWER RELEASE LATCH

2

1

2

1

2

1

 B2

5259VN1

5122−CF18 5

5124−CF18 5

5126−CF18 5

6

6

6

 28DC2

5128VN1

4

4

7

4

5101

5100

5103

5105

5107

5108

5104

5106

5109

5112

5113

5118

6296VS

5123−CF20

5125−CF20

5127−CF20

 B2

5259VN1

 28DC2

5128VN1

 B2

5259VN1

 28DC2

5128VN1

5116

5117

5121

R

B

R

B

6294VS

6295VS

5152−YY18

5151−YY20

5150−YY20

5153−YY24

5154−YY24

5155−YY20

5156−YY20

5157−YY18

5158−YY24

5159−YY24

5160−YY24

5161−YY20

5162−YY20

5163−YY18

5164−YY24

5165−YY24

B

A

D

E

C

B

A

D

F

C

E

B

A

D

E

C

EXISTING WIRE

317LG

COCKPIT DOOR SWITCH

OPEN

1

2

3

3321−5919−CF20

3321−5920−CF20

 B

 C

UNLESS OTHERWISE SPECIFIED

PREFIX ALL WIRE IDENTIFICATION

WITH ATA NO 5251.

UNLESS OTHERWISE SPECIFIED

ALL WIRES CF24 GAUGE.

UNLESS OTHERWISE SPECIFIED

ALL ROUTES ARE 2M.

NOTE:

G_SB_253213_6_WAAA_01_00

Figure A-GWAAA - Sheet 01

Wiring of the Electrical Harness 7450VB, pre SB A330-25-3213

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 61

6

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

SERVICE BULLETIN

**CONF ALL

15

8

 B2

5199VN1

7

25MQ

KEYPAD

LED2

5102−CF18

1181VC A

DATA3

DATA2

DATA1

DATA0

4

3

2

1

GND

VCC

10

9 LED1

7901−TK24

7902−SJ20

7903−SJ20

7904−SJ20

A

7900−TK24

5111−CF20

5115−CF20

5120−CF20

5

6

12

13

11

14

−S

−T

−R

−Q

−N

W

−K

−J

−I

−H

−G

−F

−E

−D

−C

−B

−A

Z

Y

X

−M

−P

30MQ

UPPER RELEASE

LATCH

31MQ

CENTER RELEASE

LATCH

32MQ

LOWER RELEASE

LATCH

2

1

2

1

2

1

 B2

5259VN1

5122−CF18 5

5124−CF18 5

5126−CF18 5

6

6

6

 28DC2

5128VN1

4

4

7

4

5101

5100

5103

5105

5107

5108

5104

5106

5109

5112

5113

5118

6296VS

5123−CF20

5125−CF20

5127−CF20

 B2

5259VN1

 28DC2

5128VN1

 B2

5259VN1

 28DC2

5128VN1

5116

5117

5121

R

B

R

B

6294VS

6295VS

5152−YY18

5151−YY20

5150−YY20

5153−YY24

5154−YY24

5155−YY20

5156−YY20

5157−YY18

5158−YY24

5159−YY24

5160−YY24

5161−YY20

5162−YY20

5163−YY18

5164−YY24

5165−YY24

B

A

D

E

C

B

A

D

F

C

E

B

A

D

E

C

OPEN 317LG/COCKPIT DOOR SWITCH

1

2

3

3321−5925−CF20

3321−5926−CF20

 B

 C

UNLESS OTHERWISE SPECIFIED

PREFIX ALL WIRE IDENTIFICATION

WITH ATA NO 5251.

UNLESS OTHERWISE SPECIFIED

ALL WIRES CF24 GAUGE.

UNLESS OTHERWISE SPECIFIED

ALL ROUTES ARE 2M.

NOTE:

TTT

1.5A1.5A1.5A

5191−YY20 U15192−YY20 UA5193−YY20 C15194−YY20 CA5195−YY20 L15196−YY20 LA

A

BCDEF

6297VS

40MQ

CIRCUIT

BREAKER BOX

5197−CF20

5198−CF20

5199−CF20

G_SB_253213_6_WBAA_01_00

Figure A-GWBAA - Sheet 01

Wiring of the Electrical Harness 7450VB, post SB A330-25-3213

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 62

6

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@A330

SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - PAX COMPARTMENT - MODIFY CDLS

WIRING LOOM IN UPPER COCKPIT DOOR PLATE COVER

MODIFICATION No.: 51911D44499

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 1

6

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

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Oct 12/04 SERVICE BULLETIN No.: A330-25-3213

REVISION No.: 02 - Aug 12/16 Page: 1

6

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