# Airbus Service Bulletin A330-53-3144 Copy: Revision 04 ("A330-53-3144 R04"), 99 pages: PDF https://openairdocs.org/files/sha256/d0/54/d05487feaaecf33c69da21408d094b441cd662a06482e3c490de76136d2ee78d; text https://openairdocs.org/service-documents/airbus/a330-53-3144/file/d05487feaaec.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0318, the docket of AD 2019-19-09. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Service Bulletin) - Number: A330-53-3144 - Latest revision known: A330-53-3144, Revision 04, dated November 23, 2015 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a330-53-3144 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a330-53-3144/proposed.md). ## Text (99 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0318, the docket of AD 2019-19-09. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - CENTER FUSEL AGE - CIRCUMFERENTIAL JOINTS AT FRAME 45 AND 54 FATIGUE LIFE IMPROVEMENT. MODIFICATION No.: 52911S16337 This page transmits Revision No.04 of Service Bulletin No.A330-53-3144 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 04 issued to inform the operators that this Service Bulletin is rendered mandatory. Further to the issuance in 2015 of Modification Service Bulletins related to Widespread Fatigue Damage (WFD), compliance thresholds have been adjusted or refined per A/C Weight Variants (WV) Group in order not to penalize all the fleet with the lowest global modification embodiment threshold. CHANGES The main changes of this revision are: - effectivity updated, - compliance classification becomes mandatory and accomplishment timescale updated, - kits 533144A01 and 533144A02 updated, - kits procurement address updated, - minor changes applied. SUMMARY GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED MATERIAL SET QUANTITY UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED MATERIAL SET QUANTITY UPDATED R COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL AVAILABILITY UPDATED MATERIAL PRICE UPDATED MATERIAL SET UPDATED R INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R LIST OF COMPONENTS Kit 533144A01R04 PART MATERIAL SET UPDATED MATERIAL SET LABEL UPDATED PART NUMBER UPDATED KEYWORD UPDATED R Kit 533144A02R03 PART MATERIAL SET UPDATED MATERIAL SET LABEL UPDATED PART NUMBER UPDATED KEYWORD UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 533144- 831-801-001- MODIFICATION TASK SOLUTION UPDATED NOTE UPDATED R Subtask 533144-831-005-002 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 533144-831-006-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-007-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-008-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-009-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-010-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-005-002 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-006-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-007-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Subtask 533144-831-008-001 SUBTASK SOLUTION UPDATED PART NUMBER UPDATED KEYWORD UPDATED MATERIAL LIST UPDATED R Fig. A-FBAAA Fig. A-FBAAA Sheet 04 SHEET UPDATED R Fig. A-FBAAA Sheet 07 SHEET UPDATED R Fig. A-FBBAA Fig. A-FBBAA Sheet 03 SHEET UPDATED R Fig. A-FBBAA Sheet 06 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. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET HISTORY OF PREVIOUS REVISIONS Revision No. 01 issued to integrate the increase of the number of holes to be oversized and cold worked on each circumferential joints. Revision 02 of this Service Bulletin issued to correct the part number of some bolts. Revision No. 03 of this Service Bulletin is issued to update the Accomplishment Timescale. REVISION SEQUENCE ORIGINAL: Aug 23/05 REVISION No. : 02 - Apr 20/11 REVISION No. : 03 - Jan 15/15 REVISION No. : 04 - Nov 23/15 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A330 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - CENTER FUSEL AGE - CIRCUMFERENTIAL JOINTS AT FRAME 45 AND 54 FATIGUE LIFE IMPROVEMENT. **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 52911S16337 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 Several damages occurred at FR45, FR53.3 and FR54 circumferential junctions on A330/A340 aircraft fatigue test specimen. Several modifications have been introduced in production line to increase the lateral and upper circumferential straps thickness. A further production modification No. 49202 adds external circumferential straps at FR45, FR53.3 and FR54 for A330 and A340 aircraft. A retrofit modification No. 49403 has also been defined for A330 aircraft pre-mod. No. 49202, consisting in adding external circumferential straps at FR53.3 with fasteners oversizing, through mandatory Service bulletin No. A330-53-3127 and A330-53-3143. Inspection by rototest of circumferential junctions lapping areas is too penalizing (removal of fasteners at each inspection and re-installation with possible hole oversizing) and alternative method by X-ray is also a heavy task with much lower intervals in the Maintenance Review Board (MRB). Therefore operators have asked for a terminative action when removing the fasteners for rototest inspection. In order to cancel this task, new retrofit modification No. 52911 has been defined for A330-200/-300 aircraft premod No. 49202 (at FR45) and A330-301/321/322/341/342 aircraft premod No. 41652 (at FR54). This modification consists in oversizing fastener holes to next nominal diameter and fastening with cold working and high interference fit. This Service Bulletin recommends oversizing to next nominal diameter and fastening with cold working and high interference fit of four fasteners rows holes between STGR3 and 5 and between STGR11 and 13 for FR45, and between STGR 4 and 5 for FR54. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A330 SERVICE BULLETIN SUMMARY Accomplishment of this Service Bulletin improves the fatigue life in this area and cancels the inspection requirements of MRB - Airworthiness Limitation Items (ALI) 53-30-09 and Airworthiness Limitation Items (ALI) 53-30-41 (previously Airworthiness Limitation Items (ALI) 53-30-12) for A330 aircraft premod No. 41652 (at FR54) and premod No. 49202 (at FR45) when applicable. Accomplishment of this Service Bulle tin will reduce the maintenance tasks. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 533144A02R03 1 2,250.00 Bolts, nuts Kit 533144A01R04 1 5,100.00 Bolts, nuts TOTAL 7,350.00 Standard tool TOOLA01 1 See SB **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 533144A01R04 1 5,100.00 Bolts, nuts Standard tool TOOLA01 1 See SB EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 38W ABD ACA ACI AEA AFR AIB ALK ARG AZA AZU BEL BER BGH CPA CRL CSA DGA EDW EIN EZX FWI G8E GFA GIA GRL HDA HFY HVN KAL MAS MLM MON OHY PAL QAF QFA QTR RSY SAI SAS TAE TAM TAP TCX THA THY TSC UAE USA VKG WRC XAX XLF DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A330 SERVICE BULLETIN SUMMARY CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None ISI None LINE MAINTENANCE AFFECTED No LIFE LIMIT None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 533144-831-801-001: MODIFICATION TOTAL MANHOURS 162.00 ELAPSED TIME (HOURS) 66.00 **CONF 002 Task 533144-831-801-001: MODIFICATION TOTAL MANHOURS 114.00 ELAPSED TIME (HOURS) 66.00 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumption DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A330 SERVICE BULLETIN SUMMARY **CONF ALL STGR5RH A BEFORE/AFTER LH SIDE SHOWN RH SIDE SYMMETRICAL A/C CL B STGR3 DEVELOPED VIEW STGR4 STGR5 STGR11 STGR12 STGR13 C FR46 FR45 FR44 FR53.3 FR45 STGR5LH STGR13LH A FR45 ANDB C STGR3 AND STGR11 STGR4 AND STGR12 STGR5 AND STGR13 REPLACEMENT OF THE FASTENERS BETWEEN STGR3 AND STGR5 AND BETWEEN STGR11 AND STGR13 WITH COLD EXPANSION OF THE HOLES. G_SB_533144_5_SUAA_01_01 Figure A-FSUAA - Sheet 01 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A330 SERVICE BULLETIN SUMMARY **CONF 001 A/C STGR5LH STGR5RH FR58 FR54 A A BEFORE/AFTER LH SIDE SHOWN RH SIDE SYMMETRICAL FR55 FR54 FR53.9 RH STGR1 LH STGR1 STGR4 STGR5 A/C CL CL B DEVELOPED VIEW FR54 STGR4 STGR5 B REPLACEMENT OF THE FASTENERS WITH COLD EXPANSION OF THE HOLES. G_SB_533144_5_SVAA_01_01 Figure A-FSVAA - Sheet 01 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A330 SERVICE BULLETIN SUMMARY This Page Intentionally Left Blank DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A330 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - CENTER FUSEL AGE - CIRCUMFERENTIAL JOINTS AT FRAME 45 AND 54 FATIGUE LIFE IMPROVEMENT. MODIFICATION No.: 52911S16337 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 : Modification. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) is embodied before delivery on aircraft with Manufacturer Serial Number (MSN) 0511 , 0513 , 0515 , 0516 , 0518 , 0519 , 0521 , 0524 and subsequent. NOTE : Modification. No. 41652S11927 (FUSELAGE - SECTION 15 - PROVIDE COMMON STRUCTURAL REINFORCEMENTS AND DEFINE REPERCUSSIONS ON SYSTEMS) is embodied before delivery on aircraft with Manufacturer Serial Number (MSN) 0113 and subsequent. (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 0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0065 0070-0072 0082-0083 0086-0087 0095-0096 0098-0099 0102 0106 0109 0111-0113 0116 0118 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A330 SERVICE BULLETIN 0120-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172 0177 0181 0189 0195 0198 0200 0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 0253-0256 0258-0259 0261-0262 0265-0267 0269 0271-0272 0275-0277 0279 0281 0283-0288 0290-0291 0293-0296 0299-0301 0303 0305-0306 0308-0309 0311-0317 0320 0322-0324 0326 0328 0330 0333-0334 0337-0340 0342-0346 0348-0351 0353 0356-0358 0361-0362 0364-0366 0368-0370 0372 0375 0380 0382 0384 0386 0388-0389 0392-0393 0396-0398 0400-0401 0403-0405 0407-0409 0412 0418-0423 0425 0427-0428 0432 0437 0439 0441 0443-0444 0448 0451-0452 0454-0456 0458 0461-0463 0465-0466 0469 0472-0473 0476-0477 0479-0481 0484 0486-0487 0489-0491 0493-0494 0496-0498 0500-0510 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 38W 0401 ABD 0343 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AEA 0461 0505 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 AIB 0345 0437 ALK 0303 0306 0311 0313 0404 0456 ARG 0290 0300 0358 0364 AZA 0272 0339 AZU 0365 0372 0462 0494 BEL 0030 0037 0045 0082 0095 0229 0249 0324 BER 0288 0322 0403 0432 0444 0454 0469 0476 0493 BGH 0255 CPA 0102 0113 0121 0386 0389 0393 0418 0420 0421 0423 0439 CRL 0285 0320 CSA 0425 DGA 0240 EDW 0291 EIN 0269 0330 0397 EZX 0261 FWI 0253 G8E 0189 0200 GFA 0276 0281 0286 0287 0334 0340 GIA 0138 0140 0144 0148 0153 0165 GRL 0230 HDA 0012 0017 0071 0083 0099 0106 0109 0118 0155 0234 0244 0405 0479 0512 HFY 0096 0127 0211 0262 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A330 SERVICE BULLETIN OPERATOR MSN HVN 0275 0294 0299 0366 KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0428 0484 0490 MAS 0116 MLM 0451 MON 0265 OHY 0072 0087 0098 0143 0353 0362 PAL 0198 QAF 0487 QFA 0506 0508 0522 QTR 0441 0473 0489 RSY 0120 0171 SAI 0055 0070 0086 SAS 0496 0497 TAE 0348 TAM 0232 0238 0247 0259 0361 0466 0472 TAP 0181 0195 0223 0305 0308 0312 0317 0477 0486 TCX 0254 0266 0301 0398 THA 0050 0060 0062 0064 0065 0112 0122 0209 0224 0231 0346 THY 0463 0504 TSC 0111 0132 0177 0250 0271 0369 0407 0427 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0382 0384 0392 0396 0409 0452 0455 0491 0509 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0309 0349 0356 0357 WRC 0296 XAX 0054 XLF 0501 (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064 0065 0070 0071 0072 0082 0083 0086 0087 0095 0096 0098 0099 0102 0106 0109 0111 0112 001 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A330 SERVICE BULLETIN MSN CONFIGURATION 0113 0116 0118 0120 0121 0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162 0165 0171 0172 0177 0181 0189 0195 0198 0200 0206 0209 0211 0219 0222 0223 0224 0226 0229 0230 0231 0232 0234 0238 0240 0241 0244 0247 0248 0249 0250 0251 0253 0254 0255 0256 0258 0259 0261 0262 0265 0266 0267 0269 0271 0272 0275 0276 0277 0279 0281 0283 0284 0285 0286 0287 0288 0290 0291 0293 0294 0295 0296 0299 0300 0301 0303 0305 0306 0308 0309 0311 0312 0313 0314 0315 0316 0317 0320 0322 0323 0324 0326 0328 0330 0333 0334 0337 0338 0339 0340 0342 0343 0344 0345 0346 0348 0349 0350 0351 0353 0356 0357 0358 0361 0362 0364 0365 0366 0368 0369 0370 0372 0375 0380 0382 0384 0386 0388 0389 0392 0393 0396 0397 0398 0400 0401 0403 0404 0405 0407 0408 0409 0412 0418 0419 0420 0421 0422 0423 0425 0427 0428 0432 0437 0439 0441 0443 0444 0448 0451 0452 0454 0455 0456 0458 0461 0462 0463 0465 0466 0469 0472 0473 0476 0477 0479 0480 0481 0484 0486 0487 0489 0490 0491 0493 0494 0496 0497 0498 0500 0501 0502 0503 0504 0505 0506 0507 0508 0509 0510 0512 0522 002 (5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which Mod. No. 49202S16307 and Mod. No. 41652S11927 are not embodied. **CONF 002 Config. 002 is valid for aircraft on which Mod. No. 49202S16307 is not embodied and Mod. No. 41652S11927 is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 533144A02R03 1 Kit 533144A01R04 1 Consumable CMLA01 As required Standard tool TOOLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 533144A01R04 1 Consumable CMLA01 As required Standard tool TOOLA01 1 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A330 SERVICE BULLETIN **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History Several damages occurred at FR45, FR53.3 and FR54 circumferential junctions on A330/A340 aircraft fatigue test specimen. Several modifications have been introduced in production line to increase the lateral and upper circumferential straps thickness. A further production modification No. 49202 adds external circumferential straps at FR45, FR53.3 and FR54 for A330 and A340 aircraft. A retrofit modification No. 49403 has also been defined for A330 aircraft pre-mod. No. 49202, consisting in adding external circumferential straps at FR53.3 with fasteners oversizing, through mandatory Service bulletin No. A330-53-3127 and A330-53-3143. Inspection by rototest of circumferential junctions lapping areas is too penalizing (removal of fasteners at each inspection and re-installation with possible hole oversizing) and alternative method by X-ray is also a heavy task with much lower intervals in the Maintenance Review Board (MRB). Therefore operators have asked for a terminative action when removing the fasteners for rototest inspection. In order to cancel this task, new retrofit modification No. 52911 has been defined for A330-200/-300 aircraft premod No. 49202 (at FR45) and A330-301/321/322/341/342 aircraft premod No. 41652 (at FR54). This modification consists in oversizing fastener holes to next nominal diameter and fastening with cold working and high interference fit. (2) Objective/Action This Service Bulletin recommends oversizing to next nominal diameter and fastening with cold working and high interference fit of four fasteners rows holes between STGR3 and 5 and between STGR11 and 13 for FR45, and between STGR 4 and 5 for FR54. (3) Advantages Accomplishment of this Service Bulletin improves the fatigue life in this area and cancels the inspection requirements of MRB - Airworthiness Limitation Items (ALI) 53-30-09 and Airworthiness Limitation Items (ALI) 53-30-41 (previously Airworthiness Limitation Items (ALI) 53-30-12) for A330 aircraft premod No. 41652 (at FR54) and premod No. 49202 (at FR45) when applicable. (4) Operational/Maintenance Consequences Accomplishment of this Service Bulle tin will reduce the maintenance tasks. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A330 SERVICE BULLETIN **CONF 001 Task 533144-831-801-001: MODIFICATION (1) Replace the fasteners from fuselage at FR45 between LH STGR3 and LH STGR5. (2) Replace the fasteners from fuselage at FR45 between LH STGR11 and LH STGR13. (3) Replace the fasteners from fuselage at FR45 between RH STGR3 and RH STGR5. (4) Replace the fasteners from fuselage at FR45 between RH STGR11 and RH STGR13. (5) Replace the fasteners from fuselage at FR54 between LH STGR4 and LH STGR5. (6) Replace the fasteners from fuselage at FR54 between RH STGR4 and RH STGR5. **CONF 002 Task 533144-831-801-001: MODIFICATION (1) Replace the fasteners from fuselage at FR45 between LH STGR3 and LH STGR5. (2) Replace the fasteners from fuselage at FR45 between LH STGR11 and LH STGR13. (3) Replace the fasteners from fuselage at FR45 between RH STGR3 and RH STGR5. (4) Replace the fasteners from fuselage at FR45 between RH STGR11 and RH STGR13. **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds given but reference should be made to the AD for confirmation of the mandated accomplishment timescale. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A330 SERVICE BULLETIN Aircraft Series Weight Variant (WV) Group See NOTE (*) Weight Variant (WV) Aircraft utilization See NOTE (**) See NOTE (***) Threshold Short Range (SR) 32500 Flight Cycles (FC) / 113000 Flight Hours (FH) A330-200 GR32A 020, 021, 022, 023, 024, 025, 026 and 027 Long Range (LR) 26600 FC / 173000 FH SR 23770 FC / 71330 FH GR33A 000, 001, 002, 003 and 004 LR 20410 FC / 122460 FH SR 27600 FC / 83000 FH GR33B 010, 011, 012, 013 and 014 LR 23700 FC / 142000 FH SR 23300 FC / 70000 FH GR33C 020, 024, 025, 026 and 027 LR 20000 FC / 120000 FH SR 22700 FC / 68300 FH A330-300 GR33D 022 LR 19500 FC / 117200 FH NOTE (*): For definition of the aircraft Weight Variants (WV) Groups, refer to Airworthiness Limitation Section (ALS) Part 2 NOTE (**): SR = FC-optimized set for aircraft in Short Range operations, refer to Airworthiness Limitation Section (ALS) Part 2 NOTE (***): LR = FH-optimized set for aircraft in Long Range operations, refer to Airworthiness Limitation Section (ALS) Part 2 F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 7 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A330 SERVICE BULLETIN **CONF 001 Task 533144-831-801-001: MODIFICATION Get Access 8.00 On Aircraft Replace the fasteners from fuselage at FR45 between LH STGR3 and LH STGR5. 24.00 Replace the fasteners from fuselage at FR45 between LH STGR11 and LH STGR13. 24.00 Replace the fasteners from fuselage at FR45 between RH STGR3 and RH STGR5. 24.00 Replace the fasteners from fuselage at FR45 between RH STGR11 and RH STGR13. 24.00 Replace the fasteners from fuselage at FR54 between LH STGR4 and LH STGR5. 24.00 Replace the fasteners from fuselage at FR54 between RH STGR4 and RH STGR5. 24.00 Tests 1.00 Close-Up 9.00 TOTAL MANHOURS 162.00 ELAPSED TIME (HOURS) 66.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumption . **CONF 002 Task 533144-831-801-001: MODIFICATION Get Access 8.00 On Aircraft Replace the fasteners from fuselage at FR45 between LH STGR3 and LH STGR5. 24.00 Replace the fasteners from fuselage at FR45 between LH STGR11 and LH STGR13. 24.00 Replace the fasteners from fuselage at FR45 between RH STGR3 and RH STGR5. 24.00 Replace the fasteners from fuselage at FR45 between RH STGR11 and RH STGR13. 24.00 Tests 1.00 Close-Up 9.00 TOTAL MANHOURS 114.00 ELAPSED TIME (HOURS) 66.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAB given in Appendix 01 - Elapsed Time Assumption . DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 8 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A330 SERVICE BULLETIN **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 53-30-12 Airworthiness Limitation Items (ALI) 53-30-41 Airworthiness Limitation Items (ALI) 53-30-09 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24 20-21-11 21-20-00 21-21-64 23-73-46 25-23-41 25-80-00 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 A330-53-3143 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 51-75-12 **CONF 002 Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 53-30-12 Airworthiness Limitation Items (ALI) 53-30-41 Airworthiness Limitation Items (ALI) 53-30-09 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 12-34-24 20-21-11 21-20-00 21-21-64 23-73-46 25-23-41 25-80-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 9 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A330 SERVICE BULLETIN Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-53-3127 A330-53-3143 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 51-75-12 **CONF ALL K. PUBLICATION AFFECTED Airworthiness Limitation Section (ALS) Part 2 Maintenance Planning Document (MPD) 533009-01-1 533009-01-2 533009-01-3 533009-01-4 533009-02-1 533009-02-2 533009-02-3 533009-02-4 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 10 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @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 533144A01R04 Kit 533144A02R03 AIRBUS Material, Logistics and Suppliers ATP II B, Hein-Sass Weg 14 21129 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by E-mail: airbus.kit@airbus.com Telephone Hotlines: A350/A380: +49 40 743 51775 A330/340, A300/310: +49 40 743 51616 A318/319/320/321: +49 40 743 51660 (2) Price and Availability Kit 533144A01R04 Cost 5,100.00 USD Availability 60 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 533144A02R03 Cost 2,250.00 USD Availability 60 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 11 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A330 SERVICE BULLETIN This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France T e l:( 3 3 )56 71 90 62 2 E-mail : monitored.retrofit@airbus.com F a x:( 3 3 )56 19 32 74 5 C. LIST OF COMPONENTS Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 10 EN6114V5-8 16 BOLT 11 EN6114V5-9 42 BOLT 12 EN6114V5-10 40 BOLT 13 EN6114V5-11 46 BOLT 15 ASNA2531-5 160 NUT 20 EN6114V5-6 16 BOLT NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 533144A02R03 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 1 EN6114V4-7 14 BOLT 2 EN6114V4-8 8 BOLT 3 EN6114V4-9 16 BOLT 4 EN6114V4-10 20 BOLT 6 ASNA2531-4 80 NUT 21 EN6114V4-4 2 BOLT 22 EN6114V4-5 6 BOLT 23 EN6114V4-6 14 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. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 12 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A330 SERVICE BULLETIN D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-External Structure 04JAA3 As required Top Coat Polyurethane-Decorative External Structure 04JMD3 As required Top Coat Polyurethane-Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner-General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Operators interested in obtaining the FTI tool kits should contact: Standard tool TOOLA01 Fatigue Technology Inc. 401 Andover Park East SEATTLE, WA 98188-7605 USA Internet: http://www.fatiguetech.com Phone: (206) 2462010 Fax: (206) 2449886 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 13 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A330 SERVICE BULLETIN (b) Price and Availability Standard tool TOOLA01 Procurement to be negotiated directly with FTI. (2) Tools To accomplish this Service Bulletin it is necessary to use the tools listed in the subsequent referenced NTM task: - Equipment and materials for check of holes as per NTM 51-10-01, Part 6, Procedure A. Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. (3) Special Tools None DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 14 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A330 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 533144-831-801-001 - 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).W HEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE : The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE : Discarded parts must be managed at the operator’s discretion. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 15 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A330 SERVICE BULLETIN Task Associated Data **CONF 001 Zone 250 260 Manpower TOTAL MANHOURS 162.00 ELAPSED TIME (HOURS) 66.00 **CONF 002 Zone 250 Manpower TOTAL MANHOURS 114.00 ELAPSED TIME (HOURS) 66.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 533144-831-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 51-75-12 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (c) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (d) Remove and install fasteners in accordance with SRM 51-42-00. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 16 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A330 SERVICE BULLETIN (e) Do the cold expansion of the fastener holes in accordance with SRM 51-48-00. (f) Countersink the holes in accordance with SRM 51-46-11. (g) Protect the areas to prevent damage to the equipment and structure and all the parts. (h) Apply sealant in accordance with SRM 51-24-00. (i) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (k) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (l) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00’Mating Part’ column. (m) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (n) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 533144-900-002-001 - Documentation Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 533144-831-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 17 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A330 SERVICE BULLETIN References Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 51-75-12 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (c) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material List (CML). (d) Remove and install fasteners in accordance with SRM 51-42-00. (e) Do the cold expansion of the fastener holes in accordance with SRM 51-48-00. (f) Countersink the holes in accordance with SRM 51-46-11. (g) Protect the areas to prevent damage to the equipment and structure and all the parts. (h) Apply sealant in accordance with SRM 51-24-00. (i) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (k) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (l) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00’Mating Part’ column. (m) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (n) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 533144-900-002-001 - Documentation Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 18 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A330 SERVICE BULLETIN **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 533144-831-003-001 - Preparation Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 21-20-00-010-801 Task 23-73-46-000-801 Task 25-23-41-000-801 Task 25-80-00-000-801 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put an access platform in position at zone 250 and zone 260. (c) Remove the ceiling panels 251JC for LH side and 252JC for RH side, refer to AMM Task 25-23-41-000-801. (d) Remove the ceiling panels 261CC and 261DC for LH side and 262CC and 262DC for RH side, refer to AMM Task 25-23-41-000-801. (e) Remove the air distribution ducts for an easier access to the work areas, refer to AMM Task 21-20-00-010-801. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 19 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A330 SERVICE BULLETIN (f) Disengage the electrical wires and the insulation blankets from the work area, refer to AMM Task 25-80-00-000-801. NOTE : If necessary, disengage the support plates of the decoder/encoder units 200RH11 and 200RH12 to get access to the work area. Hold the support plates because you must not pull the electrical wires. Retain the fasteners. (Refer to AMM Task 23-73-46-000-801) **CONF 002 (1) Subtask 533144-831-003-002 - Preparation Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 21-20-00-010-801 Task 23-73-46-000-801 Task 25-23-41-000-801 Task 25-80-00-000-801 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put an access platform in position at zone 250. (c) Remove the ceiling panels 251JC for LH side and 252JC for RH side, refer to AMM Task 25-23-41-000-801. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 20 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A330 SERVICE BULLETIN (d) Remove the air distribution ducts for an easier access to the work areas, refer to AMM Task 21-20-00-010-801. (e) Disengage the electrical wires and the insulation blankets from the work area, refer to AMM Task 25-80-00-000-801. NOTE : If necessary, disengage the support plates of the decoder/encoder units 200RH11 and 200RH12 to get access to the work area. Hold the support plates because you must not pull the electrical wires. Retain the fasteners. (Refer to AMM Task 23-73-46-000-801)) **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 533144-831-005-002 - Replace the f asteners from fuselage at FR45 between LH STGR3 and LH STGR5. Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 45 from Stringer 3 to Stringer 5 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V5-8 4 BOLT 11 EN6114V5-9 11 BOLT 12 EN6114V5-10 9 BOLT 13 EN6114V5-11 12 BOLT 15 ASNA2531-5 40 NUT 20 EN6114V5-6 4 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 21 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A330 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Top Coat Polyurethane- External Structure 04JAA3 As required Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 22 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A330 SERVICE BULLETIN References Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 51-48-00 51-75-12 Fig. A-FBAAA Replacement of the fasteners between STGR3 and STGR5 and between STGR11 and STGR13 on FR45. Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 (a) Remove the fasteners of the holes No. 1 thru 40. CAUTION : PERFORM THE REPAIR ON ONE SIDE ONLY AT A TIME. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 In accordance with SRM 51-42-00 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Do a check of the actual hole diameter and the length of the removed fasteners. Compare these with the values given in the figure Fig. A-FBAAA Sheet 02 . If the values are not the same, contact AIRBUS. 3 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. a If crack is detected : <1> Contact AIRBUS b If no crack is detected : <1> Do the operations described below. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 23 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A330 SERVICE BULLETIN (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 04 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 7.19 mm (0.283 in.) and 7.26 mm (0.286 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 7.815 mm (0.308 in.) and 7.849 mm (0.309 in.) 5 Deburr the holes. 6 Countersink the holes in accordance with SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 40. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 04 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 NOTE : Clean the surface to seal with: Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 24 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A330 SERVICE BULLETIN Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 4 Bolt EN6114V5-6 Item 20 12 Bolt EN6114V5-11 Item 13 9 Bolt EN6114V5-10 Item 12 11 Bolt EN6114V5-9 Item 11 4 Bolt EN6114V5-8 Item 10 40 Nut ASNA2531-5 Item 15 (d) Renew the protective finish in accordance with SRM 51-75-12 with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , Top Coat Polyurethane- External Structure 04JAA3 As required or Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 25 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A330 SERVICE BULLETIN (2) Subtask 533144-831-006-001 - Replace the f asteners from fuselage at FR45 between LH STGR11 and LH STGR13. Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 45 from Stringer 11 to Stringer 13 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V5-8 4 BOLT 11 EN6114V5-9 10 BOLT 12 EN6114V5-10 11 BOLT 13 EN6114V5-11 11 BOLT 15 ASNA2531-5 40 NUT 20 EN6114V5-6 4 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 26 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A330 SERVICE BULLETIN Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 Fig. A-FBAAA Replacement of the fasteners between STGR3 and STGR5 and between STGR11 and STGR13 on FR45. Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 27 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A330 SERVICE BULLETIN Replace the fasteners from fuselage at FR45 between LH STGR11 and LH STGR13. Refer to Kit 533144A01R04 Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 05 thru Fig. A-FBAAA Sheet 07 (a) Remove the fasteners of the holes No. 1 thru 40. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 05 In accordance with SRM 51-42-00 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Do a check of the actual hole diameter and the length of the removed fasteners. Compare these with the values given in the figure Fig. A-FBAAA Sheet 05 . If the values are not the same, contact AIRBUS. 3 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. a If crack is detected : <1> Contact AIRBUS b If no crack is detected : <1> Do the operations described below. (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 07 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 28 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A330 SERVICE BULLETIN NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 7.19 mm (0.283 in.) and 7.26 mm (0.286 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 7.815 mm (0.308 in.) and 7.849 mm (0.309 in.) 5 Deburr the holes. 6 Countersink the holes in accordance with SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 40. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 07 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 NOTE : Clean the surface to seal with: Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 11 Bolt EN6114V5-11 Item 13 11 Bolt EN6114V5-10 Item 12 10 Bolt EN6114V5-9 Item 11 4 Bolt EN6114V5-8 Item 10 4 Bolt EN6114V5-6 Item 20 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 29 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A330 SERVICE BULLETIN 40 Nut ASNA2531-5 Item 15 (d) Renew the protective finish with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , Top Coat Polyurethane- External Structure 04JAA3 As required or Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. (3) Subtask 533144-831-007-001 - Replace the f asteners from fuselage at FR45 between RH STGR3 and RH STGR5. Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 45 from Stringer 3 to Stringer 5 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 30 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A330 SERVICE BULLETIN Material necessary to do the job Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V5-8 4 BOLT 11 EN6114V5-9 11 BOLT 12 EN6114V5-10 9 BOLT 13 EN6114V5-11 12 BOLT 15 ASNA2531-5 40 NUT 20 EN6114V5-6 4 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 31 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A330 SERVICE BULLETIN The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 Fig. A-FBAAA Replacement of the fasteners between STGR3 and STGR5 and between STGR11 and STGR13 on FR45. Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Replace the fasteners from fuselage at FR45 between RH STGR3 and RH STGR5. Refer to Kit 533144A01R04 Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 04 (a) Remove the fasteners of the holes No. 1 thru 40. CAUTION : PERFORM THE REPAIR ON ONE SIDE ONLY AT A TIME. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 In accordance with SRM 51-42-00 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 32 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A330 SERVICE BULLETIN 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Do a check of the actual hole diameter and the length of the removed fasteners. Compare these with the values given in the figure Fig. A-FBAAA Sheet 02 . If the values are not the same, contact AIRBUS. 3 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. a If crack is detected : <1> Contact AIRBUS b If no crack is detected : <1> Do the operations described below. (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBAAA Sheet 03 and Fig. A-FBAAA Sheet 04 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 7.19 mm (0.283 in.) and 7.26 mm (0.286 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 7.815 mm (0.308 in.) and 7.849 mm (0.309 in.) DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 33 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A330 SERVICE BULLETIN 5 Deburr the holes. 6 Countersink the holes in accordance SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 32. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 04 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 NOTE : Clean the surface to seal with: Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 4 Bolt EN6114V5-6 Item 20 12 Bolt EN6114V5-11 Item 13 9 Bolt EN6114V5-10 Item 12 11 Bolt EN6114V5-9 Item 11 4 Bolt EN6114V5-8 Item 10 40 Nut ASNA2531-5 Item 15 (d) Renew the protective finish with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 34 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A330 SERVICE BULLETIN Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , Top Coat Polyurethane- External Structure 04JAA3 As required or Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. (4) Subtask 533144-831-008-001 - Replace the f asteners from fuselage at FR45 between RH STGR11 and RH STGR13. Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 45 from Stringer 11 to Stringer 13 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V5-8 4 BOLT 11 EN6114V5-9 10 BOLT 12 EN6114V5-10 11 BOLT 13 EN6114V5-11 11 BOLT 15 ASNA2531-5 40 NUT 20 EN6114V5-6 4 BOLT DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 35 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A330 SERVICE BULLETIN Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 36 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A330 SERVICE BULLETIN The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 Fig. A-FBAAA Replacement of the fasteners between STGR3 and STGR5 and between STGR11 and STGR13 on FR45. Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Replace the fasteners from fuselage at FR45 between RH STGR11 and RH STGR13. Refer to Kit 533144A01R04 Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 thru Fig. A-FBAAA Sheet 07 (a) Remove the fasteners of the holes No. 1 thru 40. Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 05 and Fig. A-FBAAA Sheet 07 In accordance with SRM 51-42-00 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Do a check of the actual diameter. Compare with the value given in the figure , Fig. A-FBAAA Sheet 05 which gives the diameter of the holes that you must found. If the values are not the same, contact AIRBUS. 3 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 37 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A330 SERVICE BULLETIN a If crack is detected : <1> Contact AIRBUS b If no crack is detected : <1> Do the operations described below. (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 06 and Fig. A-FBAAA Sheet 07 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 7.19 mm (0.283 in.) and 7.26 mm (0.286 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 7.815 mm (0.308 in.) and 7.849 mm (0.309 in.) 5 Deburr the holes. 6 Countersink the holes in accordance with SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 40. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 07 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 38 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A330 SERVICE BULLETIN NOTE : Clean the surface to seal with: Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 11 Bolt EN6114V5-11 Item 13 11 Bolt EN6114V5-10 Item 12 10 Bolt EN6114V5-9 Item 11 4 Bolt EN6114V5-8 Item 10 4 Bolt EN6114V5-6 Item 20 40 Nut ASNA2531-5 Item 15 (d) Renew the protective finish with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , Top Coat Polyurethane- External Structure 04JAA3 As required or DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 39 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A330 SERVICE BULLETIN Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. (5) Subtask 533144-831-009-001 - Replace the f asteners from fuselage at FR54 between LH STGR4 and LH STGR5. Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 54 from Stringer 4 to Stringer 5 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A02R03 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 1 EN6114V4-7 7 BOLT 2 EN6114V4-8 4 BOLT 3 EN6114V4-9 8 BOLT 4 EN6114V4-10 10 BOLT 6 ASNA2531-4 40 NUT 21 EN6114V4-4 1 BOLT 22 EN6114V4-5 3 BOLT 23 EN6114V4-6 7 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 40 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A330 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 41 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A330 SERVICE BULLETIN References Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 Fig. A-FBBAA Replacement of the fasteners between STGR4 and STGR5 on FR54 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Replace the fasteners from fuselage at FR54 between LH STGR4 and LH STGR5. Refer to Kit 533144A02R03 Refer to Fig. A-FBBAA Sheet 01 thru Fig. A-FBBAA Sheet 04 (a) Remove the fasteners of the holes No. 1 thru 40. CAUTION : PERFORM THE REPAIR ON ONE SIDE ONLY AT A TIME. Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 In accordance with SRM 51-42-00 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Do a check of the actual hole diameter and the length of the removed fasteners. Compare these with the values given in the figure Fig. A-FBBAA Sheet 02 . If the values are not the same, contact AIRBUS. 3 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. a If crack is detected : <1> Contact AIRBUS DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 42 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A330 SERVICE BULLETIN b If no crack is detected : <1> Do the operations described below. (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBBAA Sheet 01 , Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 5.715 mm (0.225 in.) and 5.791mm (0.228 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 6.227mm (0.24516 in.) and 6.262 mm (0.24654 in.) 5 Deburr the holes. 6 Countersink the holes in accordance with SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 40. Refer to Fig. A-FBBAA Sheet 01 , Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 NOTE : Clean the surface to seal with: DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 43 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A330 SERVICE BULLETIN Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 7 Bolt EN6114V4-7 Item 1 8 Bolt EN6114V4-9 Item 3 10 Bolt EN6114V4-10 Item 4 4 Bolt EN6114V4-8 Item 2 1 Bolt EN6114V4-4 Item 21 3 Bolt EN6114V4-5 Item 22 7 Bolt EN6114V4-6 Item 23 40 Nut ASNA2531-4 Item 6 (d) Renew the protective finish with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 44 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A330 SERVICE BULLETIN Top Coat Polyurethane- External Structure 04JAA3 As required or Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. (6) Subtask 533144-831-010-001 - Replace the f asteners from fuselage at FR54 between RH STGR4 and RH STGR5. Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 54 from Stringer 4 to Stringer 5 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A02R03 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 1 EN6114V4-7 7 BOLT 2 EN6114V4-8 4 BOLT 3 EN6114V4-9 8 BOLT 4 EN6114V4-10 10 BOLT 6 ASNA2531-4 40 NUT 21 EN6114V4-4 1 BOLT 22 EN6114V4-5 3 BOLT 23 EN6114V4-6 7 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 45 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A330 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Top Coat Polyurethane- Decorative External Structure 04JMD3 As required Top Coat Polyurethane- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner- General 08BAA9 As required Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA330533144-1 Durable Tooling 1 (1) EKA330533144-1 Expendable Tooling 1 (2) FTIA330533144-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to SIL 51-012. NOTE (1) : Durable tooling: Ref. DK-A330-53-3144-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : Expendable tooling: Ref. EK-A330-53-3144-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : Capital tooling: Ref. FTI-A330-53-3144-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Procedure A DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 46 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A330 SERVICE BULLETIN References Structural Repair Manual (SRM) 51-21-11 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-46-11 51-48-00 Fig. A-FBBAA Replacement of the fasteners between STGR4 and STGR5 on FR54 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Replace the fasteners from fuselage at FR54 between RH STGR4 and RH STGR5. Refer to Kit 533144A02R03 (a) Remove the fasteners of the holes No. 1 thru 40. CAUTION : PERFORM THE REPAIR ON ONE SIDE ONLY AT A TIME. Refer to Fig. A-FBBAA Sheet 01 thru Fig. A-FBBAA Sheet 04 In accordance with SRM 51-42-00 1 Remove : 40 screw Discard 40 nut Discard NOTE : Be careful not to damage the holes. 2 Refer to Fig. A-FBBAA Sheet 02 3 Do a check of the actual hole diameter and the length of the removed fasteners. Compare these with the values given in the figure Fig. A-FBBAA Sheet 02 . If the values are not the same, contact AIRBUS. 4 Do a rotating probe inspection of the holes No. 1 thru 40. Refer to NTM 51-10-01 Part 6 Procedure A. a If crack is detected : <1> Contact AIRBUS DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 47 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A330 SERVICE BULLETIN b If no crack is detected : <1> Do the operations described below. (b) Do the cold expansion of the 40 holes. Refer to Fig. A-FBBAA Sheet 01 , Fig. A-FBBAA Sheet 03 and Fig. A-FBBAA Sheet 04 In accordance with SRM 51-48-00 and SRM 51-46-11 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. Use FTI tool list No. DKA330533144-1 Durable Tooling 1 EKA330533144-1 Expendable Tooling 1 FTIA330533144-1 Capital Tooling 1 NOTE (02) : For a better access, the work should be realized from the outside of the aircraft. 1 Ream the 40 holes to the start hole diameter comprised between 5.715 mm (0.225 in.) and 5.791mm (0.228 in.) 2 Deburr the holes 3 Do the cold expansion of the holes in the fuselage in accordance with SRM 51-48-00. 4 Ream the 40 cold expanded holes to the final hole diameter comprised between 6.227mm (0.24516 in.) and 6.262 mm (0.24654 in.) 5 Deburr the holes. 6 Countersink the holes in accordance with SRM 51-46-11. (c) Install the new fasteners in the holes No. 1 thru 40. Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 04 In accordance with SRM 51-24-00, SRM 51-40-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 Refer to AMM Task 20-21-11-911-801 1 NOTE : Clean the surface to seal with: DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 48 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A330 SERVICE BULLETIN Non Aqueous Cleaner-General 08BAA9 As required NOTE : Apply Polysulfide Sealant- General Purpose Brushable 06AAA1 As required to the countersunk holes before fastener installation. 2 Install : 7 Bolt EN6114V4-7 Item 1 8 Bolt EN6114V4-9 Item 3 10 Bolt EN6114V4-10 Item 4 4 Bolt EN6114V4-8 Item 2 1 Bolt EN6114V4-4 Item 21 3 Bolt EN6114V4-5 Item 22 7 Bolt EN6114V4-6 Item 23 40 Nut ASNA2531-4 Item 6 (d) Renew the protective finish with: Surface Pretreatment-Light Alloys Chemical Conversion 10ABC1 As required Wash Primer- Structure 04CMA2 As required , Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required , Top Coat Polyurethane-Grey Internal Structure 04JME4 As required , DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 49 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A330 SERVICE BULLETIN Top Coat Polyurethane- External Structure 04JAA3 As required or Top Coat Polyurethane- Decorative External Structure 04JMD3 As required in accordance with SRM 51-21-11 and SRM 51-23-11. **CONF 002 (1) Subtask 533144-831-005-002 - Replace the f asteners from fuselage at FR45 between LH STGR3 and LH STGR5. Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 45 from Stringer 3 to Stringer 5 Manpower Resources Manhours 24.00 Minimum number of person 1 Subtask elapsed time 24.00 Skills NON SPECIFIC Material necessary to do the job Kit 533144A01R04 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V5-8 4 BOLT 11 EN6114V5-9 11 BOLT 12 EN6114V5-10 9 BOLT 13 EN6114V5-11 12 BOLT 15 ASNA2531-5 40 NUT 20 EN6114V5-6 4 BOLT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane- External Structure 04JAA3 As required DATE: Aug 23/05 SERVICE BULLETIN No.: A330-53-3144 REVISION No.: 04 - Nov 23/15 Page: 50 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a330-53-3144/file/d05487feaaec.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.