@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 - CENTER FUSELAGE - REINFORCE CIRCUMFERENTIAL

JOINT FR 53.3,STR 13 LH TO STR 13 RH - FATIGUE LIFE

IMPROVEMENT.

MODIFICATION No.: 49403S16334

This page transmits Revision No.05 of Service Bulletin No.A330-53-3143

ADDITIONAL WORK

**CONF ALL

NOTE: No additional work is required by this revision for aircraft modified by any previous

issue.

REASON

Revision 05 issued to correct the number of holes to be counterdrilled for the installation of the butt

strap on the fuselage skin and to add minor improvements on the procedure.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

WEIGHT AND BALANCE WEIGHT AND BALANCE UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED R

LIST OF COMPONENTS

Supplementary Kit 533143A02S02 PART MATERIAL SET UPDATED

QUANTITY UPDATED

R

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

ACCOMPLISHMENT INSTRUCTIONS

TASK 533143- 831-801-001-

MODIFICATION

Subtask 533143-831-004-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 533143-831-005-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 533143-831-006-001 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 533143-831-004-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

R

Subtask 533143-831-005-002 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 533143-831-006-002 SUBTASK SOLUTION UPDATED

FIGURE REFERENCE UPDATED

R

Subtask 533143-700-001-001 SUBTASK SOLUTION UPDATED R

Subtask 533143-700-001-001 SUBTASK SOLUTION UPDATED R

Fig. A-FCAAA FIGURE SOLUTION UPDATED R

Fig. A-FCAAA Sheet 04 SHEET UPDATED R

Fig. A-FCAAA Sheet 05 SHEET UPDATED R

Fig. A-FCAAB FIGURE SOLUTION UPDATED R

Fig. A-FCAAB Sheet 04 SHEET UPDATED R

Fig. A-FCAAB Sheet 05 SHEET UPDATED R

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to inform the operators that this Service Bulletin is rendered Mandatory.

Revision No 02 issued to :

add new PNs of Hoist fittings at FR 17, FR 59 and FR 76 in Appendix 01,

remove P/N TR09000, TR470000, TR120000 for Main jacking in Appendix 01,

remove the sentence which speak about ALI,

update sentence in para industry support information,

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

update sentence in compliance paragraph.

Revision 03 of this Service Bulletin issued to add a configuration to take into account the aircraft

on which the Mod No. 44723S13226 (FUSELAGE - CENTER FUSELAGE - REINFORCE ORBITAL

JUNCTION AT FR53.3) is embodied.

Revision 04 of this Service Bulletin issued to modify the threshold values and to add the grace period

value.

REVISION SEQUENCE

ORIGINAL: Dec 24/04

REVISION No. : 01 - Jun 29/06

REVISION No. : 02 - Aug 31/10

REVISION No. : 03 - Mar 03/11

REVISION No. : 04 - Dec 06/11

REVISION No. : 05 - May 29/12

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 4

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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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE CIRCUMFERENTIAL

JOINT FR 53.3,STR 13 LH TO STR 13 RH - FATIGUE LIFE

IMPROVEMENT.

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 49403S16334

MINOR None

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

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

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

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Further to damages which occurred during fatigue tests, it has been decided to install an external

stiffener of butt strap type at the upper part of the circumferential joint at FR53.3, in order to improve

fatigue life.

This Service Bulletin requires the reinforcement of the circumferential joint at the upper part at FR53.3

by installing external stiffeners between LH and RH STGR13.

Accomplishment of this Service Bulletin will improve the fatigue life of the circumferential joint at FR53.3

and will thus postpone the next inspection to beyond the design service goal.

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

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

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SERVICE BULLETIN

SUMMARY

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 533143A01R00 1 16,900.00 Butt Strap

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 533143A02R01 1 17,000.00 Butt Strap

Supplementary kit

533143A02S02

1 950.00 Bolt

TOTAL 17,950.00

EFFECTIVITY

**CONF ALL

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

ACA ACI AEA AFR AGC ALK AZA BEL BER BMA BTV CPA CRL

CYP DGA EDW EIN FWI GFA GIA GRL HDA HFY HVN IAC JAV

JST KAL KKK MAS MON OHY PAL QAF QTR RSY SAS SWR TAM

TAP TCX THA THY TSC UAE USA VKG VOZ XLF

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHERS None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 533143-831-801-001: MODIFICATION

TOTAL MANHOURS 327.00

ELAPSED TIME (HOURS) 74.50

**CONF 002

Task 533143-831-801-001: MODIFICATION

TOTAL MANHOURS 327.00

ELAPSED TIME (HOURS) 74.50

APPENDICES

**CONF ALL

Appendix 01

Appendix 02

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR54

FR38

FR53.3

STGR5

STGR5

STGR13

BUTT STRAPS

G_SB_533143_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 4

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@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 - CENTER FUSELAGE - REINFORCE CIRCUMFERENTIAL

JOINT FR 53.3,STR 13 LH TO STR 13 RH - FATIGUE LIFE

IMPROVEMENT.

MODIFICATION No.: 49403S16334

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 modification is applicable by Service Bulletin only.

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

No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE A340

COMMONALITY ITEMS) is embodied and on which modification No.

49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION

15/21) is not embodied. For aircraft on which modification No. 41652S11819

is not embodied, the Service bulletin No. A330-53-3127 is applicable.

(1) Models

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

330-341 330-342 330-343

(2) Effectivity by MSN

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

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

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

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

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 0500-0510 0512 0522

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

ACA 0277 0279 0284 0344 0400 0408 0412 0419

ACI 0507 0510

AEA 0461

AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503

AGC 0324

ALK 0303 0306 0311 0313 0404 0456

AZA 0272 0339

BEL 0229

BER 0120 0127 0288 0322 0403 0432 0444 0454 0469 0476 0493

BMA 0398 0401

BTV 0205 0330

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

0439

CRL 0285 0320

CYP 0505

DGA 0240

EDW 0291

EIN 0269 0397

FWI 0253

GFA 0276 0281 0286 0287 0334 0340

GIA 0138 0140 0144 0148 0153 0165

GRL 0230

HDA 0234 0405 0479 0512

HFY 0211

HVN 0262 0275 0294 0299 0366

IAC 0353 0362

JAV 0255

JST 0506 0508 0522

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

0351 0368 0425 0428 0484 0490

KKK 0343 0358 0364

MAS 0116 0119 0290 0296 0300

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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@A330

SERVICE BULLETIN

OPERATOR MSN

MON 0261 0265

OHY 0143

PAL 0183 0184 0188 0189 0191 0198 0200 0203

QAF 0487

QTR 0441 0473 0489

RSY 0171

SAS 0496 0497

SWR 0249

TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486

TAP 0181 0195 0223 0305 0308 0312 0317

TCX 0254 0266 0301

THA 0122 0209 0224 0231 0346

THY 0463 0504

TSC 0132 0177 0250 0271 0369 0407 0427 0480

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

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

USA 0315 0323 0333 0337 0342 0370 0375 0380 0388

VKG 0309 0349 0356 0357

VOZ 0365 0372

XLF 0501

(4) Configuration by MSN

MSN CONFIGURATION

0113 0116 0118 0119 0120 0121 0122 0127 0132 0138 0140

0143 0144 0148 0153 0155 0162 0165 0171 0172 0177

001

0181 0183 0184 0188 0189 0191 0195 0198 0200 0203 0205

0206 0209 0211 0219 0222 0223 0224 0226 0229 0230 0231

0232 0234 0238 0240 0241 0244 0247 0248 0249 0250 0251

0253 0254 0255 0256 0258 0259 0261 0262 0265 0266 0267

0269 0271 0272 0275 0276 0277 0279 0281 0283 0284 0285

0286 0287 0288 0290 0291 0293 0294 0295 0296 0299 0300

0301 0303 0305 0306 0308 0309 0311 0312 0313 0314 0315

0316 0317 0320 0322 0323 0324 0326 0328 0330 0333 0334

0337 0338 0339 0340 0342 0343 0344 0345 0346 0348 0349

0350 0351 0353 0356 0357 0358 0361 0362 0364 0365 0366

0368 0369 0370 0372 0375 0380 0382 0384 0386 0388 0389

0392 0393 0396 0397 0398 0400 0401 0403 0404 0405 0407

0408 0409 0412 0418 0419 0420 0421 0422 0423 0425 0427

0428 0432 0437 0439 0441 0443 0444 0448 0451 0452 0454

0455 0456 0458 0461 0462 0463 0465 0466 0469 0472 0473

0476 0477 0479 0480 0481 0484 0486 0487 0489 0490 0491

0493 0494 0496 0497 0498 0500 0501 0502 0503 0504 0505

0506 0507 0508 0509 0510 0512 0522

002

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 01 is valid for aircraft on which Mod No. 44723S13226 (FUSELAGE - CENTER

FUSELAGE - REINFORCE ORBITAL JUNCTION AT FR53.3) is not embodied.

**CONF 002

Config. 02 is valid for aircraft on which Mod No. 44723S13226 (FUSELAGE - CENTER

FUSELAGE - REINFORCE ORBITAL JUNCTION AT FR53.3) is embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 533143A01R00 1

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 533143A02R01 1

Consumable CMLA01 1

Supplementary kit 533143A02S02 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Further to damages which occurred during fatigue tests, it has been decided to install an

external stiffener of butt strap type at the upper part of the circumferential joint at

FR53.3, in order to improve fatigue life.

(2) Objective/Action

This Service Bulletin requires the reinforcement of the circumferential joint at the upper

part at FR53.3 by installing external stiffeners between LH and RH STGR13.

(3) Advantages

Accomplishment of this Service Bulletin will improve the fatigue life of the circumferential

joint at FR53.3 and will thus postpone the next inspection to beyond the design service

goal.

(4) Operational/Maintenance Consequences

None

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 533143-831-801-001: MODIFICATION

(1) Install the Butt Strap at FR 53.3 on the fuselage skin, between LH and RH STGR 5

(2) Install the Butt Strap at FR 53.3 on the fuselage skin between LH STGR 5 and LH

STGR 13

(3) Install the Butt Strap at FR 53.3 on the fuselage skin between RH STGR 5 and RH

STGR 13

(4) Apply a bead of 09-016 sealant around the Butt Straps

(5) Paint the modified area

**CONF 002

Task 533143-831-801-001: MODIFICATION

(1) Install the Butt Strap at FR 53.3 on the fuselage skin, between LH and RH STGR 5

(2) Install the Butt Strap at FR 53.3 on the fuselage skin between LH STGR 5 and LH

STGR 13

(3) Install the Butt Strap at FR 53.3 on the fuselage skin between RH STGR 5 and RH

STGR 13

(4) Apply a bead of 09-016 sealant around the Butt Straps

(5) Paint the modified area

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an

Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA).

The AD must be used as the reference document for the mandatory accomplishment

timescale.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

Two sets of thresholds/intervals (Short Range, Threshold 1/Interval 1 (SR) and Long

Range, Threshold 2/Interval 2 (LR)) have been established. Both sets ensure continued

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

is an equivalent damage approach corresponding to a trade off between FC/FH to

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

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold 1 or Interval 1) or LR

(Threshold 2 or Interval 2) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

A/C TYPE COMPLIANCE TIME (whichever occurs later)

THRESHOLD

(Whichever occurs first)

GRACE PERIOD

(Whichever occurs first)

Threshold 1(SR)

- 20,500FC

- 72,000FH

A330-200

Threshold 2(LR)

- 16,800FC

- 109,700FH

20 months from this revision 04

issuance date or 17,600 FC or

61,600 FH.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

A/C TYPE COMPLIANCE TIME (whichever occurs later)

THRESHOLD

(Whichever occurs first)

GRACE PERIOD

(Whichever occurs first)

Threshold 1(SR)

- 18,300FC

- 55,100FH

A330-300 WV000 thru 014 (mod

41652S11819 embodied and

mod 44723S13226 not

embodied)

Threshold 2(LR)

- 15,700FC

- 94,600FH

Threshold 1(SR)

- 25,600FC

- 77,000FH

A330-300 WV000 thru 014 (mod

41652S11819 embodied and

mod 44723S13226 embodied)

Threshold 2(LR)

- 22,000FC

- 132,300FH

Threshold 1(SR)

- 20,400FC

- 61,300FH

A330-300 (WV022)

Threshold 2(LR)

- 17,500FC

- 105,300FH

Threshold 1(SR)

- 20,900FC

- 62,800FH

A330-300 (WV020 thru 027

except 022)

Threshold 2(LR)

- 17,900FC

- 107,900FH

20 months from this revision 04

issuance date or 17,600 FC or

61,600 FH.

F. APPROVAL

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

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

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 533143-831-801-001: MODIFICATION

Get Access 66.50

On Aircraft

Install the Butt Strap at FR 53.3 on the fuselage skin,

between LH and RH STGR 5

60.00

Install the Butt Strap at FR 53.3 on the fuselage skin

between LH STGR 5 and LH STGR 13

60.00

Install the Butt Strap at FR 53.3 on the fuselage skin

between RH STGR 5 and RH STGR 13

60.00

Apply a bead of 09-016 sealant around the Butt Straps 3.00

Paint the modified area 8.00

Tests 3.00

Close-Up 66.50

TOTAL MANHOURS 327.00

ELAPSED TIME (HOURS) 74.50

NOTE: For detail concerning the elapsed time, refer to Appendix 02.

**CONF 002

Task 533143-831-801-001: MODIFICATION

Get Access 66.50

On Aircraft

Install the Butt Strap at FR 53.3 on the fuselage skin,

between LH and RH STGR 5

60.00

Install the Butt Strap at FR 53.3 on the fuselage skin

between LH STGR 5 and LH STGR 13

60.00

Install the Butt Strap at FR 53.3 on the fuselage skin

between RH STGR 5 and RH STGR 13

60.00

Apply a bead of 09-016 sealant around the Butt Straps 3.00

Paint the modified area 8.00

Tests 3.00

Close-Up 66.50

TOTAL MANHOURS 327.00

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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SERVICE BULLETIN

Task 533143-831-801-001: MODIFICATION

ELAPSED TIME (HOURS) 74.50

NOTE: For detail concerning the elapsed time, refer to Appendix 02.

**CONF ALL

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 item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +4.3 KG (+9.4797 LB)

Effect on Balance +173.982 KGM (+1258.411 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 05-53-00 12-34-24 20-21-11

21-20-00 25-23-41 25-24-51

25-24-61 25-25-61 25-80-00

52-10-00

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-53-3127

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-42-11 51-43-00 51-46-11

51-48-00 51-76-11

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 002

Aircraft Maintenance Manual (AMM) 05-53-00 12-34-24 20-21-11

21-20-00 25-23-41 25-24-51

25-24-61 25-25-61 25-80-00

52-10-00

Consumable Material List (CML)

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

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

Service Bulletin (SB) A330-53-3127

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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Structural Repair Manual (SRM) 51-42-11 51-43-00 51-46-11

51-48-00 51-76-11

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Structural Repair Manual (SRM) 53-31-11

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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

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

Kit 533143A01R00

Kit 533143A02R01

Supplementary kit 533143A02S02

AIRBUS

Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335

HAMBURG

GERMANY

For ordering by internet :

http://spares.airbus.com

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

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

(2) Price and Availability

Kit Held by operator Supplementary Kits

Required

Latest Status of Kit INST/DISP

533143A01R00 533143A02S02 533143A02R01

533143A02R01 NONE 533143A02R01

NOTE: Kit 533143A02R01 does not require an Kit 533143A02S02 because Kit

533143A02S02 is included in Kit 533143A02R01.

Kit 533143A01R00

Cost 16,900.00 USD

Availability 120 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 533143A02R01

Cost 17,000.00 USD

Availability 120 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Supplementary kit 533143A02S02

Cost 950.00 USD

Availability 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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B. INDUSTRY SUPPORT INFORMATION

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

policy.

C. LIST OF COMPONENTS

Kit 533143A01R00

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

NOTES

1 ASNA2026-4-11 2 Bolt

2 ASNA2026-4-12 2 Bolt

3 ASNA2026-4-13 4 Bolt

4 ASNA2026-4-14 4 Bolt

5 ASNA2026V4-8 68 Bolt

6 ASNA2026V4-9 208 Bolt

7 ASNA2026V4-10 48 Bolt

8 ASNA2026V4-11 368 Bolt

9 ASNA2026V4-12 40 Bolt

10 ASNA2026V4-13 36 Bolt

11 ASNA2026V4-14 24 Bolt

12 ASNA2528-4 792 Nut

13 ASNA2531-4 12 Nut

14 F5332578120095 2 Shim

15 F5332579020096 1 ButtStrp

16 F5332579120096 1 ButtStrp

17 F5332579120196 1 ButtStrp

18 F5332579220096 1 Shim

19 F5332579220196 1 Shim

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 533143A02R01

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

NOTES

1 ASNA2026-4-11 2 Bolt

2 ASNA2026-4-12 2 Bolt

3 ASNA2026-4-13 4 Bolt

4 ASNA2026-4-14 4 Bolt

6 ASNA2026V4-9 268 Bolt

7 ASNA2026V4-10 20 Bolt

8 ASNA2026V4-11 396 Bolt

9 ASNA2026V4-12 44 Bolt

10 ASNA2026V4-13 40 Bolt

11 ASNA2026V4-14 24 Bolt

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

NOTES

12 ASNA2528-4 792 Nut

13 ASNA2531-4 12 Nut

14 F5332578120095 2 Shim

15 F5332579020096 1 ButtStrp

16 F5332579120096 1 ButtStrp

17 F5332579120196 1 ButtStrp

18 F5332579220096 1 Shim

19 F5332579220196 1 Shim

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

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

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

to part number relationship.

Supplementary kit 533143A02S02

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

NOTES

6 ASNA2026V4-9 Bolt

8 ASNA2026V4-11 Bolt

9 ASNA2026V4-12 Bolt

10 ASNA2026V4-13 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 CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016 As required

Solvent General 11-026 As required

Chemical Conversion Coating 13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top coat grey 16-002 As required

External Decoration Paint 16-016 As required

External Top Coat 16-018 As required

(2) Components

None

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(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

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

cold working:

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

51-012

- Capital tooling : ref. FTI-A330-53-3143-1

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

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

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

- Durable tooling : ref. DK-A330-53-3143-1

- Expendable tooling : ref.EK-A330-53-3143-1

Operators interested in obtaining the FTI tool kits should contact:

Fatigue Technologie Inc.

401 ANDOVER PARK EAST

SAETTLE, WA 98188-7605

USA

E.mail: sales@fatiguetech.com

aog@fatiguetech.com

phone: (1) 206 2462010

fax: (1) 206 2449886

To accomplish this Service Bulletin, it is necessary to use the following tools and

equipment :

- Equipment and materials for check of holes refer to NTM 51-10-01 Part 6 Procedure

A

- Equipment and materials for the jacking procedure (refer to Appendix 01 ).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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(3) Special Tools

None

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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This Page Intentionally Left Blank

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 533143-831-801-001 - MODIFICATION

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

**CONF 001

Manpower

TOTAL MANHOURS 327.00

ELAPSED TIME (HOURS) 74.50

**CONF 002

Manpower

TOTAL MANHOURS 327.00

ELAPSED TIME (HOURS) 74.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 533143-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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(2) Subtask 533143-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General 11-026 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top coat grey 16-002 As required

References

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

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-42-11

51-43-00

51-46-11

51-48-00

51-76-11

(a) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(b) Remove and install the fasteners, (refer to SRM 51-42-11).

(c) For the cold expansion of the fastener holes, (refer to SRM 51-48-00).

(d) Countersink the holes, (refer to SRM 51-46-11).

(e) Clean the surface to seal with

Solvent General 11-026 As required

(f) To apply sealant, (Refer to SRM 51-76-11).

(g) Torque the standard threaded fasteners, (refer to AMM 20-21-11 Page Block 201).

(h) Renew the protective finish with :

Chemical

Conversion Coating

13-002 As required

Anti-Corrosion

Primer

16-001 As required

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

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Polyurethane Top

coat grey

16-002 As required

(i) For alternative and substitute fasteners (refer to SRM 51-43-00).

**CONF 002

(1) Subtask 533143-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

(2) Subtask 533143-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General 11-026 As required

Chemical Conversion

Coating

13-002 As required

Anti-Corrosion Primer 16-001 As required

Polyurethane Top coat grey 16-002 As required

References

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

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-42-11

51-43-00

51-46-11

51-48-00

51-76-11

(a) For the specification of the material numbers (Mat. No.), refer to the Consumable

Material List (CML).

(b) Remove and install the fasteners, (refer to SRM 51-42-11).

(c) For the cold expansion of the fastener holes, (refer to SRM 51-48-00).

(d) Countersink the holes, (refer to SRM 51-46-11).

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(e) Clean the surface to seal with

Solvent General 11-026 As required

(f) To apply sealant, (Refer to SRM 51-76-11).

(g) Torque the standard threaded fasteners, (refer to AMM 20-21-11 Page Block 201).

(h) Renew the protective finish with :

Chemical

Conversion Coating

13-002 As required

Anti-Corrosion

Primer

16-001 As required

Polyurethane Top

coat grey

16-002 As required

(i) For alternative and substitute fasteners (refer to SRM 51-43-00).

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 533143-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

21-20-00, Page Block 201

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-80-00, Page Block 201

52-10-00, Page Block 201

(a) Electrically ground the aircraft, (refer to AMM 12-34-24 Page Block 201).

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

(c) Open the passenger/crew door 831, (refer to AMM 52-10-00 Page Block 201).

(d) Remove the ceiling panels 251PC, 251QC, 252PC and 252QC, (refer to AMM

25-23-41 Page Block 401).

(e) Remove the center stowage compartment at FR53.3, (refer to AMM 25-24-61 Page

Block 401).

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(f) Remove the LH and RH lateral overhead stowage compartments at FR53.3, (refer

to AMM 25-24-51 Page Block 401).

(g) Remove the air distribution ducts for an easier access to the work area, (refer to

AMM 21-20-00, Page Block 201).

(h) Disengage the electrical wires and the insulation blankets from the work area, (refer

to AMM 25-80-00 Page Block 201).

NOTE: If necessary, disengage the support plates of the decoder/encoder

units 200RH17 and 200RH18 to get access to the work area. Hold

the support plates because you must not pull the electrical wires.

Retain the fasteners.

(i) Do the jacking procedure, (refer to Appendix 01 ).

**CONF 002

(1) Subtask 533143-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

21-20-00, Page Block 201

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-80-00, Page Block 201

52-10-00, Page Block 201

(a) Electrically ground the aircraft, (refer to AMM 12-34-24 Page Block 201).

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

(c) Open the passenger/crew door 831, (refer to AMM 52-10-00 Page Block 201).

(d) Remove the ceiling panels 251PC, 251QC, 252PC and 252QC, (refer to AMM

25-23-41 Page Block 401).

(e) Remove the center stowage compartment at FR53.3, (refer to AMM 25-24-61 Page

Block 401).

(f) Remove the LH and RH lateral overhead stowage compartments at FR53.3, (refer

to AMM 25-24-51 Page Block 401).

(g) Remove the air distribution ducts for an easier access to the work area, (refer to

AMM 21-20-00, Page Block 201).

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(h) Disengage the electrical wires and the insulation blankets from the work area, (refer

to AMM 25-80-00 Page Block 201).

NOTE: If necessary, disengage the support plates of the decoder/encoder

units 200RH17 and 200RH18 to get access to the work area. Hold

the support plates because you must not pull the electrical wires.

Retain the fasteners.

(i) Do the jacking procedure, (refer to Appendix 01 ).

**CONF ALL

C. PROCEDURE

WARNING: WEAR AND ATTACH A SAFETY HARNESS WHEN YOU WORK ON HIGH

SECTIONS. A FALL CAN KILL OR INJURE YOU.

NOTE: Do not remove all the fasteners from the fuselage at the same time. First,

remove the fasteners between the LH and RH STGR 5 and install the upper

Butt Strap; Then you can remove the other fasteners and install the RH and

LH lateral Butt strap, between STGR 5 - STGR 13, at the same time.

NOTE: 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 fasteners grip length in accordance with SRM

Chapter 51.

**CONF 001

(1) Subtask 533143-831-004-001 - Install the Butt Strap at FR 53.3 on the fuselage

skin, between LH and RH STGR 5

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2026-4-11 2 Bolt

2 ASNA2026-4-12 2 Bolt

3 ASNA2026-4-13 4 Bolt

4 ASNA2026-4-14 4 Bolt

5 ASNA2026V4-8 68 Bolt

6 ASNA2026V4-9 28 Bolt

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 ASNA2026V4-10 32 Bolt

8 ASNA2026V4-11 116 Bolt

9 ASNA2026V4-12 8 Bolt

10 ASNA2026V4-13 20 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 280 Nut

13 ASNA2531-4 12 Nut

14 F5332578120095 2 Shim

15 F5332579020096 1 ButtStrp

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Structural Repair Manual (SRM) 51-48-00

Fig. A-FCAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) Remove the fasteners between LH and RH STGR 5.

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02 and Fig. A-FCAAA Sheet

03

1 Remove

292 Nut Item (1) Discard

292 Bolt Item (2) Discard

(b) Do a rototest in the 152 holes, refer to Fig. A-FCAAA Sheet 02 and refer to NTM

51-10-01 Part 6, Procedure A.

1 If a crack is found: Contact AIRBUS.

2 If no crack, do the steps that follow.

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(c) Put in position on the skin between LH and RH STGR 5, refer to Fig. A-FCAAA

Sheet 05 and Fig. A-FCAAA Sheet 06

1 Butt Strap F5332579020096 Item 15

2 Shim F5332578120095 Item 14

NOTE: Put the shims in position to fill the clearance between the skin and

the Butt Strap.

(d) Counter - drill the 280 fasteners holes in the Butt Strap Item 15 and Shims Item 14.

CAUTION: DO NOT DRILL THE 12 HOLES AT LH AND RH STGR 5 AT

THIS TIME. YOU WILL DRILL THESE HOLES DURING THE COLD

EXPANSION STEP.

(e) Deburr the holes.

(f) Do the cold expansion of the 6 holes at LH STGR 5 and 6 holes at RH STGR 5,

refer to Fig. A-FCAAA Sheet 03

NOTE: For the cold expansion, use the tools supplied in kit FTIA330-53-3143-1

1 On the LH and RH sides, counter - drill 8 holes in the Butt Strap Item 15 and

shims Item 14.

2 Ream the 12 holes to the start hole diameter between 5.75 mm (0.22638 in.)

and 5.79mm (0.22795 in.).

3 Deburr the holes.

4 Identify with a mark the LH and RH sides on the Butt Strap Item 15 before

removal, to prevent a wrong position when you reinstall the butt strap.

5 If necessary, adjust the length of the Butt Straps and the shims and renew the

protective finish on the reworked surfaces as per Para 3.A.(2).(h).

6 Remove the Butt Strap and the shims

7 Do the cold expansion of the holes in the fuselage (refer to SRM 51-48-00).

(g) Apply

sealant 09-016 As required

to the attachment areas between the Butt Strap, the shims and the fuselage.

(h) Put in position and temporarily attach the Butt Strap Item 15 and the shims Item 14.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

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(i) Ream the fastener holes in Butt Strap and shims.

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

1 Ream the 12 cold expanded holes to the finish hole diameter between

6.227mm (0.24516 in.) and 6.262 mm (0.24654 in.).

2 Ream the 280 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350

mm (0.25000 in.).

3 Countersink the 292 holes in the Butt Strap and Shims, refer to Para.

3.A.(2).(d).

4 Deburr the holes.

(j) Attach the Butt Strap Item 15 and shims Item 14 with :

refer to Fig. A-FCAAA Sheet 03

2 Bolt-Countersunk

Head,Short Head

ASNA2026-4-11 Item 1

2 Bolt-Countersunk

Head,Short Head

ASNA2026-4-12 Item 2

4 Bolt-Countersunk

Head,Short Head

ASNA2026-4-13 Item 3

4 Bolt-Countersunk

Head,Short Head

ASNA2026-4-14 Item 4

12 Nut ASNA2531-4 Item 13

refer to Fig. A-FCAAA Sheet 02

68 Bolt-Countersunk Head

Short Head

ASNA2026V4-8 Item 5

28 Bolt ASNA2026V4-9 Item 6

32 Bolt ASNA2026V4-10 Item 7

116 Bolt ASNA2026V4-11 Item 8

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

20 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

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8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

280 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

(2) Subtask 533143-831-005-001 - Install the Butt Strap at FR 53.3 on the fuselage skin

between LH STGR 5 and LH STGR 13

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 ASNA2026V4-9 90 Bolt

7 ASNA2026V4-10 8 Bolt

8 ASNA2026V4-11 126 Bolt

9 ASNA2026V4-12 16 Bolt

10 ASNA2026V4-13 8 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 256 Nut

16 F5332579120096 1 ButtStrp

18 F5332579220096 1 Shim

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013

sealant 09-016 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 26

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@A330

SERVICE BULLETIN

References

Fig. A-FCAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) At FR53.3, between STGR 5 and STGR13, refer to Fig. A-FCAAA Sheet 04, Fig. AFCAAA Sheet 05, Fig. A-FCAAA Sheet 06 and Fig. A-FCAAA Sheet 07

remove :

256 Nut Item (1) Discard

256 Bolt Item (2) Discard

(b) Do a rototest in the 128 holes, refer to Fig. A-FCAAA Sheet 04 and refer to NTM

51-10-01 Part 6, Procedure A.

1 If a crack is found, contact AIRBUS.

2 If no crack, do the steps as follow.

(c) Put in position and hold on the skin, refer to figure Fig. A-FCAAA Sheet 05, Fig. AFCAAA Sheet 06 and Fig. A-FCAAA Sheet 07

1 Butt Strap F5332579120096 Item 16

1 Shim F5332579220096 Item 18

NOTE: Put the shim Item 18 in position to fill the clearance between the

skin and the Butt Strap.

(d) Counter - drill the 256 fastener holes in the Butt Strap and shim.

(e) Deburr the holes.

(f) Identify with a mark the upper and lower sides on the Butt Strap Item 16 before

removal, to prevent a wrong position when you reinstall the butt strap.

(g) If necessary, adjust the length of the Butt Strap and Shim and renew the protective

finish on the reworked surfaces as per Para 3.A.(2).(h).

(h) Remove the Butt Strap and the Shim.

(i) Apply

sealant 09-016 As required

to the attachment areas between the Butt Strap, the Shim and the fuselage.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 27

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@A330

SERVICE BULLETIN

(j) Put and temporarily attach the Butt Strap and the Shim in position on the fuselage.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

(k) Ream the 256 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350 mm

(0.25000 in.).

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

(l) Countersink the 256 holes in the Butt Strap Item 16, refer to Para.3.A.(2).(d).

(m) Deburr the holes.

(n) Attach the Butt Strap Item 16 and the Shim Item 18, refer to Fig. A-FCAAA Sheet

04 with :

90 Bolt ASNA2026V4-9 Item 6

8 Bolt ASNA2026V4-10 Item 7

126 Bolt ASNA2026V4-11 Item 8

16 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

256 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 28

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@A330

SERVICE BULLETIN

(3) Subtask 533143-831-006-001 - Install the Butt Strap at FR 53.3 on the fuselage skin

between RH STGR 5 and RH STGR 13

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 ASNA2026V4-9 90 Bolt

7 ASNA2026V4-10 8 Bolt

8 ASNA2026V4-11 126 Bolt

9 ASNA2026V4-12 16 Bolt

10 ASNA2026V4-13 8 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 256 Nut

17 F5332579120196 1 ButtStrp

19 F5332579220196 1 Shim

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FCAAA

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) At FR53.3, between STGR 5 and STGR 13, refer to Fig. A-FCAAA Sheet 04, Fig.

A-FCAAA Sheet 05, Fig. A-FCAAA Sheet 06 and Fig. A-FCAAA Sheet 07

remove :

256 Nut Item (1) Discard

256 Bolt Item (2) Discard

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 29

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@A330

SERVICE BULLETIN

(b) Do a rototest in the 128 holes, refer to Fig. A-FCAAA Sheet 04 and refer to NTM

51-10-01 Part 6, Procedure A.

1 If a crack is found, contact AIRBUS.

2 If no crack, do the steps as follow.

(c) Put in position and hold on the skin, refer to Fig. A-FCAAA Sheet 05, Fig. AFCAAA Sheet 06 and Fig. A-FCAAA Sheet 07

1 Butt Strap F5332579120196 Item 17

1 Shim F5332579220196 Item 19

NOTE: Put the shim Item 19 in position to fill the clearance between the

skin and the Butt Strap.

(d) Counter - drill the 256 fastener holes in the Butt Strap and shim.

(e) Deburr the holes.

(f) Identify with a mark the upper and lower sides on the Butt Strap Item 17 before

removal, to prevent a wrong position when you reinstall the butt strap.

(g) If necessary, adjust the length of the Butt Strap and Shim and renew the protective

finish on the reworked surfaces as per para 3.A.(2).(h).

(h) Remove the Butt Strap and the Shim.

(i) Apply

sealant 09-016 As required

to the attachment areas between the Butt Strap, the Shim and the fuselage.

(j) Put and temporarily attach the Butt Strap and the Shim in position on the fuselage.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

(k) Ream the 256 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350 mm

(0.25000 in.).

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

(l) Countersink the 256 holes in the Butt Strap Item 16, refer to Para.3.A.(2).(d).

(m) Deburr the holes.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 30

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@A330

SERVICE BULLETIN

(n) Attach the Butt Strap Item 17 and the Shim Item 19, refer to Fig. A-FCAAA Sheet

04 with :

90 Bolt ASNA2026V4-9 Item 6

8 Bolt ASNA2026V4-10 Item 7

126 Bolt ASNA2026V4-11 Item 8

16 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

256 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

(4) Subtask 533143-831-007-001 - Apply a bead of 09-016 sealant around the Butt

Straps

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-016 As required

Apply a bead of

sealant 09-016 As required

around the Butt Straps.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 31

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@A330

SERVICE BULLETIN

(5) Subtask 533143-831-008-001 - Paint the modified area

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

External Decoration Paint 16-016

External Top Coat 16-018

(a) Apply

External Top Coat 16-018 As required

or

External Decoration

Paint

16-016 As required

to the bolt heads and the Butt Straps.

**CONF 002

(1) Subtask 533143-831-004-002 - Install the Butt Strap at FR 53.3 on the fuselage

skin, between LH and RH STGR 5

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2026-4-11 2 Bolt

2 ASNA2026-4-12 2 Bolt

3 ASNA2026-4-13 4 Bolt

4 ASNA2026-4-14 4 Bolt

6 ASNA2026V4-9 96 Bolt

8 ASNA2026V4-11 148 Bolt

9 ASNA2026V4-12 8 Bolt

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 32

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@A330

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 ASNA2026V4-13 20 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 280 Nut

13 ASNA2531-4 12 Nut

14 F5332578120095 2 Shim

15 F5332579020096 1 ButtStrp

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, procedure A

Structural Repair Manual (SRM) 51-48-00

Fig. A-FCAAB

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) Remove the fasteners between LH and RH STGR 5.

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02 and Fig. A-FCAAB Sheet

03

1 Remove :

292 Nut Item (1) Discard

292 Bolt Item (2) Discard

(b) Do a rototest in the 152 holes, refer to Fig. A-FCAAB Sheet 02 and refer to NTM

51-10-01 Part 6, procedure A.

1 If a crack is found: Contact AIRBUS.

2 If no crack, do the steps that follow.

(c) Put in position on the skin between LH and RH STGR 5, refer to Fig. A-FCAAB

Sheet 05 and Fig. A-FCAAB Sheet 06

1 Butt Strap F5332579020096 Item 15

2 Shim F5332578120095 Item 14

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 33

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@A330

SERVICE BULLETIN

NOTE: Put the shims in position to fill the clearance between the skin and

the Butt Strap.

(d) Counter - drill the 280 fasteners holes in the Butt Strap Item 15 and Shims Item 14.

CAUTION: DO NOT DRILL THE 12 HOLES AT LH AND RH STGR 5 AT

THIS TIME. YOU WILL DRILL THESE HOLES DURING THE COLD

EXPANSION STEP.

(e) Deburr the holes.

(f) Do the cold expansion of the 6 holes at LH STGR 5 and 6 holes at RH STGR 5,

refer to Fig. A-FCAAB Sheet 03

NOTE: For the cold expansion, use the tools supplied in kit FTIA330-53-3143-1

1 On the LH and RH sides, counter - drill 8 holes in the Butt Strap Item 15 and

shims Item 14.

2 Ream the 12 holes to the start hole diameter between 5.75 mm (0.22638 in.)

and 5.79mm (0.22795 in.).

3 Deburr the holes.

4 Identify with a mark the LH and RH sides on the Butt Strap Item 15 before

removal, to prevent a wrong position when you reinstall the butt strap.

5 If necessary, adjust the length of the Butt Straps and the shims and renew the

protective finish on the reworked surfaces as per Para 3.A.(2).(h).

6 Remove the Butt Strap and the shims

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

(g) Apply

sealant 09-016 As required

to the attachment areas between the Butt Strap, the shims and the fuselage.

(h) Put in position and temporarily attach the Butt Strap Item 15 and the shims Item 14.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

(i) Ream the fastener holes in Butt Strap and shims.

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 34

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@A330

SERVICE BULLETIN

1 Ream the 12 cold expanded holes to the finish hole diameter between

6.227mm (0.24516 in.) and 6.262 mm (0.24654 in.).

2 Ream the 280 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350

mm (0.25000 in.).

3 Countersink the 292 holes in the Butt Strap and Shims, refer to Para.

3.A.(2).(d).

4 Deburr the holes.

(j) Attach the Butt Strap Item 15 and shims Item 14 with :

Refer to Fig. A-FCAAB Sheet 03

2 Bolt-Countersunk

Head,Short Head

ASNA2026-4-11 Item 1

2 Bolt-Countersunk

Head,Short Head

ASNA2026-4-12 Item 2

4 Bolt-Countersunk

Head,Short Head

ASNA2026-4-13 Item 3

4 Bolt-Countersunk

Head,Short Head

ASNA2026-4-14 Item 4

12 Nut ASNA2531-4 Item 13

refer to Fig. A-FCAAB Sheet 02

96 Bolt ASNA2026V4-9 Item 6

148 Bolt ASNA2026V4-11 Item 8

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

20 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

280 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 35

5

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

SERVICE BULLETIN

(2) Subtask 533143-831-005-002 - Install the Butt Strap at FR 53.3 on the fuselage skin

between LH STGR 5 and LH STGR 13

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 ASNA2026V4-9 86 Bolt

7 ASNA2026V4-10 10 Bolt

8 ASNA2026V4-11 124 Bolt

9 ASNA2026V4-12 18 Bolt

10 ASNA2026V4-13 10 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 256 Nut

16 F5332579120096 1 ButtStrp

18 F5332579220096 1 Shim

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FCAAB

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) At FR53.3, between STGR 5 and STGR13, refer to Fig. A-FCAAB Sheet 04, Fig. AFCAAB Sheet 05, Fig. A-FCAAB Sheet 06 and Fig. A-FCAAB Sheet 07

remove :

256 Nut Item (1) Discard

256 Bolt Item (2) Discard

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 36

5

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@A330

SERVICE BULLETIN

(b) Do a rototest in the 128 holes, refer to Fig. A-FCAAB Sheet 04 and refer to NTM

51-10-01 Part 6, Procedure A.

1 If a crack is found, contact AIRBUS.

2 If no crack, do the steps as follow.

(c) Put in position and hold on the skin, refer to figure Fig. A-FCAAB Sheet 05, Fig. AFCAAB Sheet 06 and Fig. A-FCAAB Sheet 07

1 Butt Strap F5332579120096 Item 16

1 Shim F5332579220096 Item 18

NOTE: Put the shim Item 18 in position to fill the clearance between the

skin and the Butt Strap.

(d) Counter - drill the 256 fastener holes in the Butt Strap and shim.

(e) Deburr the holes.

(f) Identify with a mark the upper and lower sides on the Butt Strap Item 16 before

removal, to prevent a wrong position when you reinstall the butt strap.

(g) If necessary, adjust the length of the Butt Strap and Shim and renew the protective

finish on the reworked surfaces as per Para 3.A.(2).(h).

(h) Remove the Butt Strap and the Shim.

(i) Apply :

sealant 09-016 As required

to the attachment areas between the Butt Strap, the Shim and the fuselage.

(j) Put and temporarily attach the Butt Strap and the Shim in position on the fuselage.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

(k) Ream the 256 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350 mm

(0.25000 in.).

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

(l) Countersink the 256 holes in the Butt Strap Item 16, refer to Para.3.A.(2).(d).

(m) Deburr the holes.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 37

5

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@A330

SERVICE BULLETIN

(n) Attach the Butt Strap Item 16 and the Shim Item 18, refer to Fig. A-FCAAB Sheet

04 with :

86 Bolt ASNA2026V4-9 Item 6

10 Bolt ASNA2026V4-10 Item 7

124 Bolt ASNA2026V4-11 Item 8

18 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

10 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

256 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

(3) Subtask 533143-831-006-002 - Install the Butt Strap at FR 53.3 on the fuselage skin

between RH STGR 5 and RH STGR 13

Manpower Resources

Manhours 60.00

Minimum number of person 1

Subtask elapsed time 60.00

Skills NON SPECIFIC

Material necessary to do the job

Kit 533143A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 ASNA2026V4-9 86 Bolt

7 ASNA2026V4-10 10 Bolt

8 ASNA2026V4-11 124 Bolt

9 ASNA2026V4-12 18 Bolt

10 ASNA2026V4-13 10 Bolt

11 ASNA2026V4-14 8 Bolt

12 ASNA2528-4 256 Nut

17 F5332579120196 1 ButtStrp

19 F5332579220196 1 Shim

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 38

5

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@A330

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

sealant 09-016 As required

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-FCAAB

Butt Strap Installation

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

Sheet 07

(a) At FR53.3, between STGR 5 and STGR 13, refer to Fig. A-FCAAB Sheet 04, Fig.

A-FCAAB Sheet 05, Fig. A-FCAAB Sheet 06 and Fig. A-FCAAB Sheet 07

remove :

256 Nut Item (1) Discard

256 Bolt Item (2) Discard

(b) Do a rototest in the 128 holes, refer to Fig. A-FCAAB Sheet 04 and refer to NTM

51-10-01 Part 6, Procedure A.

1 If a crack is found, contact AIRBUS.

2 If no crack, do the steps as follow.

(c) Put in position and hold on the skin, refer to Fig. A-FCAAB Sheet 05, Fig. AFCAAB Sheet 06 and Fig. A-FCAAB Sheet 07

1 Butt Strap F5332579120196 Item 17

1 Shim F5332579220196 Item 19

NOTE: Put the shim Item 19 in position to fill the clearance between the

skin and the Butt Strap.

(d) Counter - drill the 256 fastener holes in the Butt Strap and shim.

(e) Deburr the holes.

(f) Identify with a mark the upper and lower sides on the Butt Strap Item 17 before

removal, to prevent a wrong position when you reinstall the butt strap.

(g) If necessary, adjust the length of the Butt Strap and Shim and renew the protective

finish on the reworked surfaces as per para 3.A.(2).(h).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 39

5

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@A330

SERVICE BULLETIN

(h) Remove the Butt Strap and the Shim.

(i) Apply

sealant 09-016 As required

to the attachment areas between the Butt Strap, the Shim and the fuselage.

(j) Put and temporarily attach the Butt Strap and the Shim in position on the fuselage.

1 Smooth the burr of sealant.

2 let the sealant dry as necessary.

(k) Ream the 256 holes to a diameter between 6.310 mm (0.24842 in.) and 6.350 mm

(0.25000 in.).

NOTE: To prevent butt strap debonding during reaming, do not remove all

the temporary fasteners at the same time. Install the new fasteners

in the reamed holes one after the other as specified in the steps

that follow.

(l) Countersink the 256 holes in the Butt Strap Item 16, refer to Para.3.A.(2).(d).

(m) Deburr the holes.

(n) Attach the Butt Strap Item 17 and the Shim Item 19, refer to Fig. A-FCAAB Sheet

04 with :

86 Bolt ASNA2026V4-9 Item 6

10 Bolt ASNA2026V4-10 Item 7

124 Bolt ASNA2026V4-11 Item 8

18 Bolt-Countersunk Head

Short Head

ASNA2026V4-12 Item 9

10 Bolt-Countersunk Head

Short Head

ASNA2026V4-13 Item 10

8 Bolt-Countersunk Head

Short Head

ASNA2026V4-14 Item 11

256 Nut ASNA2528-4 Item 12

NOTE : Apply :

Sealant-Brush

Consistency

09-013 As required

to the countersink holes before fastener installation.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 40

5

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@A330

SERVICE BULLETIN

(4) Subtask 533143-831-007-001 - Apply a bead of 09-016 sealant around the Butt

Straps

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

sealant 09-016 As required

Apply a bead of

sealant 09-016 As required

around the Butt Straps.

(5) Subtask 533143-831-008-001 - Paint the modified area

Manpower Resources

Manhours 8.00

Minimum number of person 1

Subtask elapsed time 8.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

External Decoration Paint 16-016

External Top Coat 16-018

(a) Apply

External Top Coat 16-018 As required

or

External Decoration

Paint

16-016 As required

to the bolt heads and the Butt Straps.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 41

5

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@A330

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 533143-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 05-53-00, Page Block 501

21-20-00, Page Block 401

25-23-41, Page Block 401

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-25-61, Page Block 401

25-80-00, Page Block 201

(a) Do a test for leakage in the repair area, (refer to AMM 05-53-00 Page Block 501).

(b) Install the removed equipment

1 Install the electrical wires and the insulation blankets that you disengaged to

get access to the work area, (refer to AMM 25-80-00 Page Block 201).

NOTE: If you disengaged the support plates of the decoder/encoder

units 200RH17 and 200RH18, put them in position and attach

with the fasteners retained at removal.

2 Install the air distribution ducts that you removed for an easier access to the

work area, (refer to AMM 21-20-00 Page Block 401).

3 Install the LH and RH lateral overhead stowage compartments at Frame 53.3,

(refer to AMM 25-24-51 Page Block 401).

4 Install the center stowage compartment at FR53.3, (refer to AMM 25-24-61

Page Block 401).

5 Install the ceiling panels 251PC, 251QC, 252PC and 252QC, (refer to AMM

25-23-41 Page Block 401).

(c) Do the test after the removal/installation of the ceiling panels, (refer to AMM

25-23-41 Page Block 401).

(d) Do the test after the removal/installation of the center-overhead stowage

compartments, (refer to AMM 25-24-61 Page Block 401).

(e) Do the test after the removal/installation of the lateral-overhead stowagecompartments, (refer to AMM 25-24-51 Page Block 401).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 42

5

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@A330

SERVICE BULLETIN

**CONF 002

(1) Subtask 533143-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 05-53-00, Page Block 501

21-20-00, Page Block 401

25-23-41, Page Block 401

25-23-41, Page Block 401

25-24-51, Page Block 401

25-24-51, Page Block 401

25-24-61, Page Block 401

25-25-61, Page Block 401

25-80-00, Page Block 201

(a) Do a test for leakage in the repair area, (refer to AMM 05-53-00 Page Block 501).

(b) Install the removed equipment

1 Install the electrical wires and the insulation blankets that you disengaged to

get access to the work area, (refer to AMM 25-80-00 Page Block 201).

NOTE: If you disengaged the support plates of the decoder/encoder

units 200RH17 and 200RH18, put them in position and attach

with the fasteners retained at removal.

2 Install the air distribution ducts that you removed for an easier access to the

work area, (refer to AMM 21-20-00 Page Block 401).

3 Install the LH and RH lateral overhead stowage compartments at Frame 53.3,

(refer to AMM 25-24-51 Page Block 401).

4 Install the center stowage compartment at FR53.3, (refer to AMM 25-24-61

Page Block 401).

5 Install the ceiling panels 251PC, 251QC, 252PC and 252QC, (refer to AMM

25-23-41 Page Block 401).

(c) Do the test after the removal/installation of the ceiling panels, (refer to AMM

25-23-41 Page Block 401).

(d) Do the test after the removal/installation of the center-overhead stowage

compartments, (refer to AMM 25-24-61 Page Block 401).

(e) Do the test after the removal/installation of the lateral-overhead stowagecompartments, (refer to AMM 25-24-51 Page Block 401).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 43

5

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@A330

SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 533143-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

52-10-00, Page Block 201

(a) Put the aircraft on its wheels and remove the jacking equipment, (refer to Appendix

01 ).

(b) Close the passenger/crew door 831, (refer to AMM 52-10-00 Page Block 201).

(c) Remove the access platform(s).

(d) Disconnect the aircraft electrical ground-connection, (refer to AMM 12-34-24 Page

Block 201).

**CONF 002

(1) Subtask 533143-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

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

52-10-00, Page Block 201

(a) Put the aircraft on its wheels and remove the jacking equipment, (refer to Appendix

01 ).

(b) Close the passenger/crew door 831, (refer to AMM 52-10-00 Page Block 201).

(c) Remove the access platform(s).

(d) Disconnect the aircraft electrical ground-connection, (refer to AMM 12-34-24 Page

Block 201).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 44

5

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@A330

SERVICE BULLETIN

**CONF 001

L A/C C

FR53.3

FR54

FR38

FR53.3

STGR5

STGR5

STGR13

STGR5

STGR9

STGR13

STGR5

STGR9

STGR13

B B C C

A

E

A

G_SB_533143_5_CAAA_01_00

Figure A-FCAAA - Sheet 01

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 45

5

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@A330

SERVICE BULLETIN

**CONF 001

SYMBOL

REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM

ASNA2026V4−8

PN ITEM

ASNA2528−4

ASNA2528−4

FASTENERS NOT REMOVED

L A/C C

ASNA2528−4

MIN. mm

(in)

MAX.

DO A ROTOTEST IN THESE HOLES

A

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

ASNA2026V4−13

ASNA2026V4−11

DO A COLD EXPANSION OF THESE HOLES

(REFER TO DETAIL SHEET 3)

ASNA2026V4−9 ASNA2528−4

ASNA2528−4

ASNA2528−4

6.310

(0.24842)

6.350

(0.25000)

ASNA2026V4−14 ASNA2528−4

ASNA2026V4−10

ASNA2026V4−12

mm

(in)

FWD

(1) (2)

(1) (2)

(1) (2)

(1) (2)

(1) (2)

(1) (2)

(1) (2)

5

6

7

8

9

10

11

12

12

12

12

12

12

12

FR53.3

STGR1

STGR2

STGR3

STGR4

STGR5

B

G_SB_533143_5_CAAA_02_01

Figure A-FCAAA - Sheet 02

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 46

5

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@A330

SERVICE BULLETIN

**CONF 001

NUT BOLT

STGR5 =

TO A/C CL

A

B

MIN. MAX.

REMOVED

ITEMS STDN

MIN. MAX.

NEW

BOLT

NEW

NUT

mm

(in.)

mm

(in.)

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

FASTENERS NOT REMOVED

COLD EXPANSION, HOLES AND FASTENERS DATA

PN/ITEM PN/ITEM

*

START *

HOLE DIAMETER

FINISH *

HOLE DIAMETER

ASNA

2531−4

ASNA

2531−4

A

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

DETAIL

COLD EXPANSION OF THE HOLES

PRINCIPLE DIAGRAM FOR

THE INSTALLATION

DIRECTIONOF THE

EXPANSION SLEEVE:

A C C D D B

HOLES

ASNA

2026−4−12

ASNA

2026−4−11

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

ASNA

2531−4

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

ASNA

2531−4

C

D

ASNA

2026−4−13

ASNA

2026−4−14

− REAM THE START HOLE DIAMETERS WITH THE BUTT STRAP ITEM AND THE SHIMS

ITEM ATTACHED TO THE FUSELAGE

− REMOVE THE BUTT STRAP ITEM AND THE SHIMS ITEM AND DO THE

COLD EXPANSION OF HOLES IN THE FUSELAGE

− ATTACH THE BUTT STRAP ITEM AND THE SHIMS ITEM AGAIN TO THE

FUSELAGE AND REAM THE FINISH HOLE DIAMETERS.

G_SB_533143_5_CAAA_03_00

FWD

(1) (2) 1 13

(1) (2) 2 13

(1) (2) 3 13

(1) (2) 4 13

15

14

15 14

15 14

FR53.3

Figure A-FCAAA - Sheet 03

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 47

5

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@A330

SERVICE BULLETIN

**CONF 001

LH SIDE SEEN FROM THE INSIDE

RH SIDE SYMMETRICAL

SYMBOL

REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM PN ITEM

ASNA2528−4

FASTENERS NOT REMOVED

6.310

(0.24842)

6.350

(0.25000)

MIN. mm

(in.) (in.)

MAX. mm

ASNA2026V4−9

DO A ROTOTEST IN THESE HOLES

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2026V4−11

ASNA2026V4−10

ASNA2026V4−14

ASNA2026V4−12

ASNA2026V4−13

FR53.3 FR53.3

STGR5

STGR9

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

STGR13

C FWD

(1) (2) 6 12

(1) (2) 7 12

(1) (2) 8 12

(1) (2) 9 12

(1) (2) 10 12

(1) (2) 11 12

G_SB_533143_5_CAAA_04_01

Figure A-FCAAA - Sheet 04

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 48

5

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@A330

SERVICE BULLETIN

**CONF 001

L A/C C

SHIM

IF NECESSARY ADJUST THE LENGTH OF THE BUTT STRAP AND SHIMS

SHIM

SKIN

PANELS

SHIM

SHIM

15

17

19

14

14

16

18

NOTE:

STGR11

STGR12

STGR13

STGR5

STGR5 STGR12

STGR11

STGR13

E

D

D

A

A

C

C

B

B

FR53.3

G_SB_533143_5_CAAA_05_01

Figure A-FCAAA - Sheet 05

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 49

5

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@A330

SERVICE BULLETIN

**CONF 001

LH

RH

VIEW LOOKING AFT

G_SB_533143_5_CAAA_06_00

FR53.3

15 14

14

15

16

17

A A

D D

FWD

Figure A-FCAAA - Sheet 06

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 50

5

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@A330

SERVICE BULLETIN

**CONF 001

LH

RH

NOTE 2:

LH SIDE SECTIONS SHOWN

RH SIDE SYMMETRICAL

ADJUST IF NECESSARY

VIEW LOOKING AFT

G_SB_533143_5_CAAA_07_00

STGR11

STGR12

STGR13

18

19

16

17

LH

RH

B B

LH

RH

18

19

16

17

LH

FR53.3 RH

C C

FWD

NOTE 1:

Figure A-FCAAA - Sheet 07

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 51

5

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@A330

SERVICE BULLETIN

**CONF 002

L A/C C

FR53.3

FR54

FR38

FR53.3

STGR5

STGR5

STGR13

STGR5

STGR9

STGR13

STGR5

STGR9

STGR13

B B C C

A

E

A

G_SB_533143_5_CAAB_01_00

Figure A-FCAAB - Sheet 01

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 52

5

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@A330

SERVICE BULLETIN

**CONF 002

SYMBOL

REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM PN ITEM

ASNA2528−4

FASTENERS NOT REMOVED

L A/C C

ASNA2528−4

MIN. mm

(in)

MAX.

DO A ROTOTEST IN THESE HOLES

A

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

ASNA2026V4−13

ASNA2026V4−11

DO A COLD EXPANSION OF THESE HOLES

(REFER TO DETAIL SHEET 3)

ASNA2026V4−9 ASNA2528−4

ASNA2528−4 6.310

(0.24842)

6.350

(0.25000)

ASNA2026V4−14 ASNA2528−4

ASNA2026V4−12

mm

(in)

FWD

(1) (2)

(1) (2)

(1) (2)

(1) (2)

(1) (2)

6

8

9

10

11

12

12

12

12

12

FR53.3

STGR1

STGR2

STGR3

STGR4

STGR5

B

G_SB_533143_5_CAAB_02_00

Figure A-FCAAB - Sheet 02

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 53

5

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@A330

SERVICE BULLETIN

**CONF 002

NUT BOLT

=

TO A/C CL

A

B

MIN. MAX.

REMOVED

ITEMS STDN

MIN. MAX.

NEW

BOLT

NEW

NUT

mm

(in)

mm

(in)

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

FASTENERS NOT REMOVED

COLD EXPANSION, HOLES AND FASTENERS DATA

PN/ITEM PN/ITEM

*

START *

HOLE DIAMETER

FINISH *

HOLE DIAMETER

ASNA

2531−4

ASNA

2531−4

A

LH SIDE SHOWN FROM THE INSIDE

RH SIDE SYMMETRICAL

DETAIL

COLD EXPANSION OF THE HOLES

PRINCIPLE DIAGRAM FOR

THE INSTALLATION

DIRECTIONOF THE

EXPANSION SLEEVE:

A C C D D B

HOLES

ASNA

2026−4−12

ASNA

2026−4−11

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

ASNA

2531−4

5.75

(0.22638)

5.79

(0.22795) 6.3N 6.227

(0.24516)

6.262

(0.24654)

ASNA

2531−4

C

D

ASNA

2026−4−13

ASNA

2026−4−14

− REAM THE START HOLE DIAMETERS WITH THE BUTT STRAP ITEM AND THE SHIMS

ITEM ATTACHED TO THE FUSELAGE

− REMOVE THE BUTT STRAP ITEM AND THE SHIMS ITEM AND DO THE

COLD EXPANSION OF HOLES IN THE FUSELAGE

− ATTACH THE BUTT STRAP ITEM AND THE SHIMS ITEM AGAIN TO THE

FUSELAGE AND REAM THE FINISH HOLE DIAMETERS.

FWD

(1) (2) 1 13

(1) (2) 2 13

(1) (2) 3 13

(1) (2) 4 13

15

14

15 14

15 14

FR53.3

STGR5

G_SB_533143_5_CAAB_03_00

Figure A-FCAAB - Sheet 03

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 54

5

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@A330

SERVICE BULLETIN

**CONF 002

LH SIDE SEEN FROM THE INSIDE

RH SIDE SYMMETRICAL

SYMBOL

REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT

NUT BOLT PN ITEM PN ITEM

ASNA2528−4

FASTENERS NOT REMOVED

6.310

(0.24842)

6.350

(0.25000)

MIN. mm

(in) (in)

MAX. mm

ASNA2026V4−9

DO A ROTOTEST IN THESE HOLES

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2528−4

ASNA2026V4−11

ASNA2026V4−10

ASNA2026V4−14

ASNA2026V4−12

ASNA2026V4−13

FR53.3 FR53.3

STGR5

STGR9

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

STGR13

C FWD

(1) (2) 6 12

(1) (2) 7 12

(1) (2) 8 12

(1) (2) 9 12

(1) (2) 10 12

(1) (2) 11 12

G_SB_533143_5_CAAB_04_01

Figure A-FCAAB - Sheet 04

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 55

5

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@A330

SERVICE BULLETIN

**CONF 002

L A/C C

SHIM

IF NECESSARY ADJUST THE LENGTH OF THE BUTT STRAP AND SHIMS

SHIM

SKIN

PANELS

SHIM

SHIM

15

17

19

14

14

16

18

NOTE:

STGR11

STGR12

STGR13

STGR5

STGR5 STGR12

STGR11

STGR13

E

D

D

A

A

C

C

B

B

FR53.3

G_SB_533143_5_CAAB_05_01

Figure A-FCAAB - Sheet 05

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 56

5

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@A330

SERVICE BULLETIN

**CONF 002

LH

RH

VIEW LOOKING AFT

FR53.3

15 14

14

15

16

17

A A

D D

FWD

G_SB_533143_5_CAAB_06_00

Figure A-FCAAB - Sheet 06

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 57

5

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@A330

SERVICE BULLETIN

**CONF 002

LH

RH

NOTE 2:

LH SIDE SECTIONS SHOWN

RH SIDE SYMMETRICAL

ADJUST IF NECESSARY

VIEW LOOKING AFT

STGR11

STGR12

STGR13

18

19

16

17

LH

RH

B B

LH

RH

18

19

16

17

LH

FR53.3 RH

C C

FWD

NOTE 1:

G_SB_533143_5_CAAB_07_00

Figure A-FCAAB - Sheet 07

Butt Strap Installation

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 58

5

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@A330

SERVICE BULLETIN

Appendix 01

**CONF ALL

(1) Jacking procedure for the installation of the butt straps on the fuselage skin at FR53.3, between

STGR13 LH and STGR13 RH

(a) FIXTURE, TOOLS, TEST AND SUPPORT EQUIPMENT

ITEM PART NUMBER QTY DESCRIPTION

RECOMMEND ALTERNATIVE

2 98F07203002000 98F07203002001 6 HOIST TRIPOD

4 98F07203000150 98F07203000120 1 FR17 HOIST

FITTING

5 98F07203000151 98F07203000121 1 FR17 HOIST

FITTING

6 98F07203000140 98F07203000110 1 FR59 HOIST

FITTING

7 98F07203000141 98F07203000111 1 FR59 HOIST

FITTING

8 98F07203000142 98F07203000126 1 FR76 HOIST

FITTING

9 98F07203000143 98F07203000127 1 FR76 HOIST

FITTING

11 343A160KN2 1 LOAD CELL

12 343A1MN3 2 LOAD CELL

13 343A63KN2 3 LOAD CELL

14 343A100KN2 4 LOAD CELL

15 98A07003906200 8 LOAD CELL

ADAPTOR

16 98A07003912200 2 LOAD CELL

ADAPTOR

17 98A07003907200 7 LOAD CELL

ADAPTOR

18 98A07003907201 2 LOAD CELL

ADAPTOR

20 98A07003907202 1 LOAD CELL

ADAPTOR

Refer to figure Fig. A-FAIAA

NOTE: For Main Jack, Front Jack and Safety Jack, use your own standard tool or

refer to SRM 51-51-00.

(b) AIRCRAFT CONFIGURATION

- This jacking procedure is only applicable to the configuration below: The aircraft without :

. Fuel (except undrainable fuel)

. Payload

. Water (potable)

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

5

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@A330

SERVICE BULLETIN

Appendix 01

. Baggage containers

. Pallets

. Emergency equipment

. Catering

. Documents and aircraft tool package.

- For the remaining aircraft configuration :

Refer to Fig. A-FAHAA

NOTE: If the aircraft configuration is not the same as the configuration above, contact

AIRBUS.

NOTE: If you do other tasks on the aircraft at the same time, contact AIRBUS.

(c) JACKING PROCEDURE

1 Obey the general jacking instructions, (refer to SRM 51-51-00).

2 Lift the aircraft on the front, main and safety jacks shown in Fig. A-FAJAA, (refer to AMM

07-11-00, Page Block 201).

3 Install the additional jacking equipment at FR17, FR59 and FR76 (refer to Fig. AFAJAA).

CAUTION : MAKE SURE THAT THE LOADS NEVER EXCEED THE MAXIMUM

PERMITTED LOADS SPECIFIED IN FIGURE Fig. A-FAJAA

4 Apply the loads to the jacks at FR17, FR59 and FR76, one step after the other (refer to

Fig. A-FAJAA)

a Gradually apply the loads shown in step 1 to the jacks at FR17, FR59 and FR76.

Wait until the loads on the jacks become stable and make sure that they are within

a tolerance of +/- 10 percent. Make sure that the safety jack at FR87 is in contact

without load.

b Continue the same procedure as above to apply the loads shown in step 2, then

step 3 and step 4.

NOTE: When the loads given in step 4 are stable within a tolerance of

+/- 10 percent on the jacks at FR17, FR59 and FR76, you can

do the procedure given in ACCOMPLISHMENT INSTRUCTIONS,

TASK 533143-831-801 001 MODIFICATION TASK 533143-831-801

001 MODIFICATION .

(d) CLOSE-UP

1 Gradually decrease the loads one step after the other, from step 4 to zero on the jacks

at FR17, FR59 and FR76 (refer to Fig. A-FAJAA).

2 Remove the jacks at FR17, FR59 and FR76.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 2

5

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@A330

SERVICE BULLETIN

Appendix 01

3 Lower the aircraft and remove the front, main and safety jacks, (refer to AMM 07-11-00,

Page Block 201).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 3

5

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

SERVICE BULLETIN

Appendix 01

**CONF ALL

X

X

X

X

FUSELAGE

AIRCRAFT CONFIGURATION FOR JACKING:

X

X

X

X

X

X

X

X

INSTALLED REMOVED

X

X

X

X

X

INSTALLED REMOVED

NOSE LANDING GEAR

L/H MAIN LANDING GEAR

R/H MAIN LANDING GEAR

LANDING GEARS

MOVABLE ELEMENTS

X

X

X

INSTALLED REMOVED

X

L/H WING

INSTALLED REMOVED

X

X

INSTALLED REMOVED

R/H WING

X

X

INSTALLED REMOVED

ENGINES

L/H ENGINE

R/H ENGINE

PYLONS

L/H PYLON

R/H PYLON

FUEL

O

O

O

EXCEPT UNDRAINABLE FUEL

EQUIPEMENT/FURNISHING INSTALLED REMOVED

X

X

X

X

X

X

X

X

X

X

X

HORIZONTAL STABILIZER

VERTICAL STABILIZER

L/H PAX DOOR 1

R/H PAX DOOR 1

L/H PAX DOOR 2

R/H PAX DOOR 2

L/H PAX DOOR 3

R/H PAX DOOR 3

L/H PAX DOOR 4

R/H PAX DOOR 4

FWD CARGO DOOR

AFT CARGO DOOR

BULK CARGO DOOR

APU

CREW REST X

L/H WINGLET

L/H SLATS

L/H FLAPS

L/H SPOILERS

L/H AILERONS X

X

X

X

X

X

X

X

INSTALLED REMOVED

L/H ENGINE

R/H ENGINE

THRUST REVERSERS

L/H WING TANKS

R/H WING TANKS

TRIM TANKS

FUSELAGE SECTION 11

FUSELAGE SECTION 12

FUSELAGE SECTION 13

FUSELAGE SECTION 14

FUSELAGE SECTION 14A

FUSELAGE SECTION 15

FUSELAGE SECTION 16

FUSELAGE SECTION 17

FUSELAGE SECTION 18

FUSELAGE SECTION 19

FUSELAGE SECTION 19.1

R/H WINGLET

R/H SLATS

R/H FLAPS

R/H SPOILERS

R/H AILERONS

G_SB_533143_5_AHAA_01_00

Figure A-FAHAA - Sheet 01

Aircraft Configuration for Jacking

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 4

5

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

SERVICE BULLETIN

Appendix 01

**CONF ALL

ITEM DESIGNATION RECOMMEND PN

6 HOIST TRIPOD

1 FR17 HOIST FITTING

1 FR17 HOIST FITTING

1 FR59 HOIST FITTING

1 FR59 HOIST FITTING

1 FR76 HOIST FITTING

1 FR76 HOIST FITTING

1 LOAD CELL

2 LOAD CELL

LOAD CELL 343A63KN2

LOAD CELL 343A100KN2

8

2

7

2

1

QUANTITY

343A160KN2

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

LOAD CELL ADAPTOR

98F07203002000

98F07203000150

98F07203000151

98F07203000140

98F07203000141

98A07003906200

98A07003912200

98A07003907200

98A07003907202

98A07003907201

98F07203000142

98F07203000143

343A1MN3

3

4

ALTERNATIVE PN

98F07203002001

98F07203000120

98F07203000121

98F07203000110

98F07203000111

98F07203000126

98F07203000127

2

4

5

6

7

8

9

11

12

13

14

15

16

17

18

20

2

5

14

15

17

2

4

14

15

17

2

6

13

15

2

7

13

15

17

2

9

14

15

17

2

8

14

15

17

13

15

17

12

16

18

11

15

20

12

16

18

G_SB_533143_5_AIAA_01_04

17

Figure A-FAIAA - Sheet 01

Jacking Equipment

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 5

5

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

SERVICE BULLETIN

Appendix 01

**CONF ALL

JACKING POINTS

MAX.

PERMIS.

LOADS STEP 1 STEP 2 STEP 3 STEP 4

% OF

TOTAL

LOADS

APPLIED LOADS (Kg)

+/− 10%

FR87 (SAFETY JACK)

 (CONTACT ONLY)

FR17 (2 JACKS)

 (SEE NOTE 2)

FR59 (2 JACKS)

 (SEE NOTE 2)

FR76 (2 JACKS)

 (SEE NOTE 2)

4590 0 0 0 00

16820 2800 5610 8410 11210

8050 530 1060 1580 2110 2

15190 3450 6900 10350 13800 12

WITH TWO JACKS, THE LOAD FOR EACH JACK IS THE APPLIED

LOAD DIVIDED BY TWO).

FRONT JACK

LH MAIN JACK

RH MAIN JACK

MAX.

PERMIS.

LOADS

12540

75130

75130

FOR INFORMATION

FOR INFORMATION

FOR INFORMATION

SUPPORT POINTS REMAINING LOADS (Kg)

11200

38100

38100

10

33

33

CORRESPONDING WEIGHT OF THE AIRCRAFT: 114400 (INCLUDING BALLASTS IF ANY)

10

ACTUAL

LOADS

(SEE NOTE 1)

APPLIED LOADS ARE TOTAL LOADS PER STATION (FOR A STATION

TO INSTALL KIT A01 (REFER TO ACCOMPLISHEMENT INSTRUCTION,

PARAGRAPH 3.C.), MAKE SURE THAT THE ACTUAL LOADS ARE

IN A TOLERANCE OF +/− 10% OF THE VALUES GIVEN IN STEP 4.

NOTE 1:

NOTE 2:

G_SB_533143_5_AJAA_01_01

Figure A-FAJAA - Sheet 01

Jacking Procedure

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 6

5

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

SERVICE BULLETIN

Appendix 02

**CONF ALL

The following chart is only a proposal. Operators may determine that another way to do the work is

more suitable for them.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

5

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

SERVICE BULLETIN

Appendix 02

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A330−53−3143

SB ELAPSED TIME

(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

327.00

74.50

STEPS

66.50 33.25

0 5 10 15 20 75

ON THE FUSELAGE SKIN, BETWEEN 60.00 4.00

60.00 4.00

60.00 4.00

8.00 2.00

TEST 3.00 1.00

CLOSE−UP 66.50 33.25

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

NOTE:

PER

2

15

15

15

4

3

2

:

:

INSTALL THE BUTT STRAP AT FR53.3

LH AND RH STRG5

ON THE FUSELAGE SKIN, BETWEEN

INSTALL THE BUTT STRAP AT FR53.3

LH STRG5 AND LH STRG13

ON THE FUSELAGE SKIN, BETWEEN

INSTALL THE BUTT STRAP AT FR53.3

RH STRG5 AND RH STRG13

PAINT THE MODIFIED AREA

25 30 35 40 45 50 55 60 65 70

3.00 1.00 3 AROUNT THE BUTT STRAPS

APPLY A BEAD OF 09−016 SEALANT

G_SB_533143_5_AKAA_01_00

Figure A-FAKAA - Sheet 01

Elapsed Time Assumption

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 2

5

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE CIRCUMFERENTIAL

JOINT FR 53.3,STR 13 LH TO STR 13 RH - FATIGUE LIFE

IMPROVEMENT.

MODIFICATION No.: 49403S16334

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: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

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

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

improve the quality of our Service Bulletins.

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

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

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Comments:

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Please return this form to:

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FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143

REVISION No.: 05 - May 29/12 Page: 1

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