# @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



# MANDATORYMANDATORYMANDATORY 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 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 2 5

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# @A330 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 5

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# @A330 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 5

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# @A330 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY 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 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 2 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY
**CONF ALL

FR54

FR38 FR53.3 STGR5STG R5

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 5

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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



# MANDATORYMANDATORYMANDATORY 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 REVISION No.: 05 - May 29/12 Page: 1 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 2 5

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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 REVISION No.: 05 - May 29/12 Page: 3 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 4 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 5 5

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# @A330 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). COMPLIANCE TIME (whichever occurs later) A/C TYPE 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 REVISION No.: 05 - May 29/12 Page: 6 5

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# @A330 SERVICE BULLETIN COMPLIANCE TIME (whichever occurs later) A/C TYPE 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 REVISION No.: 05 - May 29/12 Page: 7 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 8 5

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# @A330 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 REVISION No.: 05 - May 29/12 Page: 9 5

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# @A330 SERVICE BULLETIN 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

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 10 5

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# @A330 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 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 REVISION No.: 05 - May 29/12 Page: 11 5

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# @A330 SERVICE BULLETIN
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 DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 12 5

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# @A330 SERVICE BULLETIN
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 DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 13 5

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# @A330 SERVICE BULLETIN (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 REVISION No.: 05 - May 29/12 Page: 14 5

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# @A330 SERVICE BULLETIN (3) Special Tools None

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 15 5

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# @A330 SERVICE BULLETIN

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DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 16 5

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# @A330 SERVICE BULLETIN
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.
DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 17 5

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# @A330 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). (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 REVISION No.: 05 - May 29/12 Page: 18 5

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# @A330 SERVICE BULLETIN 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).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 19 5

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# @A330 SERVICE BULLETIN (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).
DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 20 5

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# @A330 SERVICE BULLETIN (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).

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 21 5

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# @A330 SERVICE BULLETIN (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 DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 22 5

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# @A330 SERVICE BULLETIN
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.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 23 5

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# @A330 SERVICE BULLETIN (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.
DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 24 5

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# @A330 SERVICE BULLETIN (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

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 25 5

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# @A330 SERVICE BULLETIN
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 5

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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 5

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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 04with : 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 5

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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 5

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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 5

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

# @A330 SERVICE BULLETIN (n) Attach the Butt Strap Item 17 and the Shim Item 19, refer to Fig. A-FCAAA Sheet 04with : 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 5

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

# @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 5

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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 5

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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 5

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

# @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

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

# @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

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

# @A330 SERVICE BULLETIN (n) Attach the Butt Strap Item 16 and the Shim Item 18, refer to Fig. A-FCAAB Sheet 04with : 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

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

# @A330 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required 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 04with : 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

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

# @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

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

# @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 001LA/C C

FR53.3 FR54

FR38 FR53.3 STGR5STGR5 STGR13

STGR5 STGR9 STGR13 STGR5STGR9 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 ITEM PN 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 C L

**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:

**B D D**  **C C**  **A**

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 ITEM PN 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 STGR11STGR13



## 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

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

# @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 17LH RH



## B **B**

LH RH 18 19 16 17LH RH FR53.3



## 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 002LA/C C

FR53.3 FR54

FR38 FR53.3 STGR5STGR5 STGR13

STGR5 STGR9 STGR13 STGR5STGR9 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 ITEM PN

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 C L

**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:

**B D D**  **C C**  **A**

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 ITEM PN 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 STGR11STGR13



## 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 17LH RH



## B **B**

LH RH 18 19 16 17LH RH FR53.3



## 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

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# @A330 SERVICE BULLETIN Appendix 01
**CONF ALL

ITEM DESIGNATION RECOMMEND PN HOIST TRIPOD 6 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 343A63KN2 LOAD CELL 343A100KN2 LOAD CELL 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

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# @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 REMAINING LOADS (Kg) SUPPORT POINTS
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

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# @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

5 10 15 20 75 0 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

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# @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 5

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# @A330 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Dec 24/04 SERVICE BULLETIN No.: A330-53-3143 REVISION No.: 05 - May 29/12 Page: 1 5

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