# @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 - REAR FUSELAGE - INSPECTION OF LONGITUDINAL DOUBLER AT VTP ATTACHMENT CUT OUT MODIFICATION No.: None This page transmits Revision No.02 of Service Bulletin No.A330-53-3168 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 02 issued to update the Flight Cycles (FC) and Flight Hours (FH). CHANGES SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Minor editorial or document structure change N GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-GSAAA Minor editorial or document structure change N Fig. A-GSAAA Sheet 01 Minor editorial or document structure change N

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 1 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N CONF 002 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Minor editorial or document structure change N Objective/Action Minor editorial or document structure change N Advantages Minor editorial or document structure change N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Minor editorial or document structure change N Classification Minor editorial or document structure change N Accomplishment Timescale Threshold and interval are changed. N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N LIST OF COMPONENTS Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N Tooling - Price and Availability Minor editorial or document structure change N
DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 2 6

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Tools Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 533168- 832-848-001-INSPECTION Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Subtask 533168-832-201-001 Minor editorial or document structure change N Subtask 533168-839-201-001 Minor editorial or document structure change N Subtask 533168-832-201-001 Minor editorial or document structure change N Subtask 533168-839-201-001 Minor editorial or document structure change N Subtask 533168-832-203-001 Minor editorial or document structure change N Subtask 533168-832-203-001 Minor editorial or document structure change N Subtask 533168-832-204-001 Minor editorial or document structure change N Subtask 533168-832-205-001 Minor editorial or document structure change N Subtask 533168-832-207-001 Minor editorial or document structure change N Subtask 533168-832-207-001 Minor editorial or document structure change N Fig. A-GBAAA Minor editorial or document structure change N Fig. A-GBAAA Sheet 01 Minor editorial or document structure change N Fig. A-GFAAA Minor editorial or document structure change N Fig. A-GFAAA Sheet 01 Minor editorial or document structure change N Fig. A-GFAAB Minor editorial or document structure change N Fig. A-GFAAB Sheet 01 Minor editorial or document structure change N Fig. A-GFBAA Minor editorial or document structure change N Fig. A-GFBAA Sheet 01 Minor editorial or document structure change N Fig. A-GFBAB Minor editorial or document structure change N Fig. A-GFBAB Sheet 01 Minor editorial or document structure change N 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 SEQUENCE ORIGINAL: Sep 19/07 REVISION No. : 02 - Dec 21/11

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# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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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 - REAR FUSELAGE - INSPECTION OF LONGITUDINAL DOUBLER AT VTP ATTACHMENT CUT OUT **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During long life structure tests on the A340-600, damage was found in the upper shell structure between FR80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no action is required. Nevertheless, due to the higher DSG of 33000/40000 FC and different design (e.g. doubler thickness) for A330-300 aircraft, this damage is considered relevant for these models. This Service Bulletin has been issued to inform the operator to do an eddy current high frequency inspection of the upper shell structure between FR80 and FR86. The accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will ensure the structural integrity of the upper shell structure between FR80 and FR86. Airbus strongly recommended to perform the modification at the next convenient opportunity after the first inspection to avoid larger repairs especially in case of crack findings. Accomplishment of modification Service Bulletin 53-3159 cancels the inspection required by this inspection Service Bulletin up to the DSG of 33000/40000 FC for A330-300. 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 DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 1 6

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# @A330 SERVICE BULLETIN SUMMARY EVALUATION TABLE COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

AAR ACA CAL CPA DAL DLH HDA IWD KAL PAL QFA QTR SAS THA TSC USA VKG CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT Yes OTHERS SB A330-53-3159, OIT SE999.0124/06, EASA AD No. 2007-0284 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 533168-832-848-001: INSPECTION TOTAL MANHOURS 16.00 ELAPSED TIME (HOURS) 16.00 **CONF 002 Task 533168-832-848-001: INSPECTION TOTAL MANHOURS 16.00 DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 2 6

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# @A330 SERVICE BULLETIN SUMMARY Task 533168-832-848-001: INSPECTION ELAPSED TIME (HOURS) 16.00 APPENDICES **CONF ALL None

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 3 6

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# @A330 SERVICE BULLETIN SUMMARY

**CONF ALL

FR91 Z310 Z270



### A



## A FR80 FR84 FR86

G_SB_533168_6_SAAA_01_00 INSPECTION AREA A

INSPECTION AREA B INSPECTION AREA C

Figure A-GSAAA - Sheet 01
DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 4 6

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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 - REAR FUSELAGE - INSPECTION OF LONGITUDINAL DOUBLER AT VTP ATTACHMENT CUT OUT MODIFICATION No.: None 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: Aircraft with mod. 53223D44586 or 52974D44611 embodied in production before delivery are not concerned by this Inspection Service Bulletin. Aircraft without mod 44205D40465 embodied in production before delivery are not concerned by this Inspection Service Bulletin. (1) Models 330-301 330-302 330-303 330-322 330-323 330-342 330-343 (2) Effectivity by MSN 0198 0200 0203 0206 0209 0219 0224 0231 0234 0241 0244 0256 0267 0277 0279 0284 0315 0323 0333 0337-0338 0342 0344 0346 0349-0351 0356-0357 0368 0370 0375 0380 0386 0388-0389 0393 0400 0405 0407-0408 0412 0418-0421 0423 0425 0428 0439 0479 0484 0490 0496-0497 0512 0515 0524 0533 0539 0542 0548-0550 0552-0553 0558 0564-0565 0568 0570 0574 0576 0578-0579 0581 0588 0591 0593 0595 0602-0603 0607 0623 0629 0636-0637 0640-0642 0645 0648 0654 0659 0662-0663 0669-0671 0673-0676

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# @A330 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN AAR 0640 0676 ACA 0277 0279 0284 0344 0400 0408 0412 0419 CAL 0602 0607 0641 0671 0675 CPA 0244 0386 0389 0393 0418 0420 0421 0423 0439 0539 0548 0565 0669 0673 DAL 0524 0533 0542 0549 0552 0578 0588 0591 0663 0674 DLH 0570 0576 0579 0629 0636 0642 0645 0648 HDA 0234 0405 0479 0512 0581 0654 0662 IWD 0670 KAL 0206 0219 0241 0256 0267 0338 0350 0351 0368 0425 0428 0484 0490 0550 PAL 0198 0200 0203 QFA 0553 0558 0564 0574 0593 0595 0603 QTR 0623 0637 0659 SAS 0496 0497 0515 0568 THA 0209 0224 0231 0346 TSC 0407 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0349 0356 0357 (4) Configuration by MSN MSN CONFIGURATION 0198 0200 0203 0206 0209 0219 0224 0231 0234 0241 0244 0256 0267 0277 0279 0284 0315 0323 0333 0337 0338 0342 0344 0346 0349 0350 0351 0356 0357 0368 0370 0375 0380 0386 0388 0389 0393 0400 0405 0407 0408 0412 0418 0419 0420 0421 0423 0425 0428 0439 0479 0484 0490 0496 0497 0512 0515 0539 0548 0550 0565 0568 0581 001

0524 0533 0542 0549 0552 0553 0558 0564 0570 0574 0576 0578 0579 0588 0591 0593 0595 0602 0603 0607 0623 0629 0636 0637 0640 0641 0642 0645 0648 0654 0659 0662 0663 0669 0670 0671 0673 0674 0675 0676 002

(5) Configuration definition **CONF 001 Config.01 is applicable for aircraft which have weight variant (WV) 010 thru 025 with the relevant thresholds and intervals. **CONF 002 Config.02 is applicable for aircraft which have weight variant (WV) 050 thru 053 with the relevant thresholds and intervals. DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 2 6

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# @A330 SERVICE BULLETIN (6) Material Effectivity No Material Set B. CONCURRENT REQUIREMENTS None C. REASON (1) History During long life structure tests on the A340-600, damage was found in the upper shell structure between FR80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no action is required. Nevertheless, due to the higher DSG of 33000/40000 FC and different design (e.g. doubler thickness) for A330-300 aircraft, this damage is considered relevant for these models. (2) Objective/Action This Service Bulletin has been issued to inform the operator to do an eddy current high frequency inspection of the upper shell structure between FR80 and FR86. (3) Advantages The accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will ensure the structural integrity of the upper shell structure between FR80 and FR86. Airbus strongly recommended to perform the modification at the next convenient opportunity after the first inspection to avoid larger repairs especially in case of crack findings. Accomplishment of modification Service Bulletin 53-3159 cancels the inspection required by this inspection Service Bulletin up to the DSG of 33000/40000 FC for A330-300. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 533168-832-848-001: INSPECTION (1) Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV010 - WV025 DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 3 6

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# @A330 SERVICE BULLETIN
**CONF 002 Task 533168-832-848-001: INSPECTION (1) Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV050 - WV053 **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified 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 mandated accomplishment timescale. NOTE: Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long Range, Threshold/Interval (LR)) have been established. Both sets ensure continued airworthiness and could be used to cover any type of A/C utilization. This approach is an equivalent damage approach corresponding to trade of between FC/FH to better suit fleet utilization. As the both sets of thresholds/intervals ensure continued airworthiness and could be used any type of utilization, for 1st inspection and repetitive ones, operators may select either SR (Threshold or Interval) or LR (Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal set of threshold/interval is selected, airworthiness will be ensured, but will penalize the operator because the inspection will be performed sooner than necessary as a consequence, the selection of SR or LR threshold and subsequent intervals can be change whenever. Threshold and Interval are whichever occurs first between FC and FH for selected set of threshold/interval between SR and LR. This means that the set FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa). Inspection Sequence Type Config. 01 A330-300 WV010 thru WV025 Short Range (SR) Config. 01 A330-300 WV010 thru WV025 Long Range (LR) Config. 02 A330-300 WV050 thru WV053 Short Range (SR) Config. 02 A330-300 WV050 thru WV053 Long Range (LR) 1 Threshold 25400 FC or 76300 FH 19600 FC or 117700 FH 21600 FC or 64900 FH 16600 FC or 100100 FH 2 crack finding ? repeat inspections acc. to intervals below and contact AIRBUS for repair instruction. repeat inspections acc. to intervals below and contact AIRBUS for repair instruction.

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 4 6

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# @A330 SERVICE BULLETIN

3 no crack finding interval 4500 FC or 13500 FH or accomplish SB 53-3159 3600 FC or 21900 FH or accomplish SB 53-3159 4000 FC or 12100 FH or accomplish SB 53-3159 3200 FC or 19600 FH or accomplish SB 53-3159 4 detected crack length < 3.0mm interval 1250 FC or 3800 FH and contact AIRBUS for repair. 1000 FC or 6100 FH and contact AIRBUS for repair. 1100 FC or 3400 FH and contact AIRBUS for repair. 900 FC or 5500 FH and contact AIRBUS for repair. 5 3.0mm <= detected crack length < 6.0mm interval 950 FC or 2900 FH and contact AIRBUS for repair. 750 FC or 4700 FH and contact AIRBUS for repair. 850 FC or 2600 FH and contact AIRBUS for repair. 650 FC or 4200 FH and contact AIRBUS for repair. 6 6.0mm <= detected crack length < 10.0mm interval 600 FC or 1900 FH and contact AIRBUS for repair. 500 FC or 3000 FH and contact AIRBUS for repair. 550 FC or 1700 FH and contact AIRBUS for repair. 450 FC or 2700 FH and contact AIRBUS for repair. 7 detected crack length >= 10.0mm contact AIRBUS before next flight contact AIRBUS before next flight contact AIRBUS before next flight contact AIRBUS before next flight
NOTE: Repetitive intervals given here above in case of crack findings should be considered as an allowance in order to prepare the repair/modification scenario due to the specific access and tooling required. It is strongly recommended to contact AIRBUS in case of crack findings in order to define the repair to applied at next interval according to above table. F. APPROVAL The technical content of this document is approved under authority of Design Organisation Approval No.EASA21.J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 533168-832-848-001: INSPECTION Get Access 3.25 DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 5 6

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# @A330 SERVICE BULLETIN
Task 533168-832-848-001: INSPECTION On Aircraft Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV010 - WV025 9.50 Close-Up 3.25 TOTAL MANHOURS 16.00 ELAPSED TIME (HOURS) 16.00 **CONF 002 Task 533168-832-848-001: INSPECTION Get Access 3.25 On Aircraft Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV050 - WV053 9.50 Close-Up 3.25 TOTAL MANHOURS 16.00 ELAPSED TIME (HOURS) 16.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA None J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29 12-34-24 25-33-48 25-33-54 27-51-18 29-00-00 29-14-00 52-10-00 53-45-11 53-55-11 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-62-01 53-51-00 Service Bulletin (SB) A330-53-3159

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# @A330 SERVICE BULLETIN
**CONF 002 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-12-29 12-34-24 25-33-48 25-33-54 27-51-18 29-00-00 29-14-00 52-10-00 53-45-11 53-55-11 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-62-01 53-51-00 Service Bulletin (SB) A330-53-3159 **CONF ALL K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 53-51-00 Non Destructive Test Manual (NTM) 53-51-00 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A330 SERVICE BULLETIN

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION Airbus will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools NOTE: To accomplish this Service Bulletin it is necessary to use tools listed in the NTM 53-51-00 Page Block 601, and pencil probe NFE P/N 2-835-07-6901, refer to NTM 51-62-01 Page Block 601,Type G. (3) Special Tools None

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# @A330 SERVICE BULLETIN

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 533168-832-848-001 - INSPECTION 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 16.00 ELAPSED TIME (HOURS) 16.00 **CONF 002 Manpower TOTAL MANHOURS 16.00 ELAPSED TIME (HOURS) 16.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 533168-832-201-001 Manpower Resources Skills NON SPECIFIC

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# @A330 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 (a) For the identification of access panels, refer to AMM 06-41-53 Page Block 001. (b) For the Station/Frame (STA/FR) identification, refer to AMM 06-31-53 Page Block 001. (2) Subtask 533168-839-201-001 - Administrative Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 533168-832-201-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 (a) For the identification of access panels, refer to AMM 06-41-53 Page Block 001. (b) For the Station/Frame (STA/FR) identification, refer to AMM 06-31-53 Page Block 001. (2) Subtask 533168-839-201-001 - Administrative Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 533168-832-203-001 Manpower Resources Skills AIRFRAME

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# @A330 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 25-33-48, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 52-10-00, Page Block 201 53-45-11, Page Block 401 53-55-11, Page Block 401 (a) Make sure that the aircraft is grounded, refer to AMM 12-34-24 Page Block 201. (b) Put the access platform(s) in position in the REAR fuselage area and at the FWD passenger/crew doors. (c) Open the access door 312AR in the REAR fuselage area. (d) Open the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00 Page Block 201. (e) Depressurize the Green, the Blue and the Yellow hydraulic systems, refer to AMM 29-00-00 Page Block 201. (f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer to AMM 29-14-00 Page Block 201. (g) Put warning notices in position to tell persons not to pressurize the hydraulic systems : 1 in the cockpit on the hydraulic section 40VU of the overhead panel, 2 on the ground service panel of each hydraulic system. (h) Open, safety and tag the circuit breaker(s) which are listed in : 1 AMM 27-51-18 Page Block 401. (i) Remove the Pelmet of the AFT Galley , refer to AMM 25-33-48 Page Block 401 or AMM 25-33-54 Page Block 401. (j) Remove the Dorsal Fin, refer to AMM 53-45-11 Page Block 401 to be able to inspect area B and C from outside. (k) Remove the Fairings 323AR, 323AL, 323BR and 323BL, refer to AMM 53-55-11 Page Block 401. **CONF 002 (1) Subtask 533168-832-203-001 Manpower Resources Skills AIRFRAME DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 13 6

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# @A330 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201 25-33-48, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 52-10-00, Page Block 201 53-45-11, Page Block 401 53-55-11, Page Block 401 (a) Make sure that the aircraft is grounded, refer to AMM 12-34-24 Page Block 201. (b) Put the access platform(s) in position in the REAR fuselage area and at the FWD passenger/crew doors. (c) Open the access door 312AR in the REAR fuselage area. (d) Open the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00 Page Block 201. (e) Depressurize the Green, the Blue and the Yellow hydraulic systems, refer to AMM 29-00-00 Page Block 201. (f) Depressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer to AMM 29-14-00 Page Block 201. (g) Put warning notices in position to tell persons not to pressurize the hydraulic systems : 1 in the cockpit on the hydraulic section 40VU of the overhead panel, 2 on the ground service panel of each hydraulic system. (h) Open, safety and tag the circuit breaker(s) which are listed in : 1 AMM 27-51-18 Page Block 401. (i) Remove the Pelmet of the AFT Galley , refer to AMM 25-33-48 Page Block 401 or AMM 25-33-54 Page Block 401. (j) Remove the Dorsal Fin, refer to AMM 53-45-11 Page Block 401 to be able to inspect area B and C from outside. (k) Remove the Fairings 323AR, 323AL, 323BR and 323BL, refer to AMM 53-55-11 Page Block 401.

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 14 6

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# @A330 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 533168-832-204-001 - Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV010 - WV025 Manpower Resources Manhours 9.50 Minimum number of person 1 Subtask elapsed time 9.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 53-51-00, Page Block 601 Service Bulletin (SB) A330-53-3159 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAA Flow Chart Sheet 01 Fig. A-GFBAA Flow Chart Sheet 01 (a) Do the inspection for WV010 - WV025 SR Mission. 1 Do the eddy current inspection (Refer to NTM 53-51-00, Page Block 601, procedure A and B) and (Refer to Figure Fig. A-GBAAA Sheet 01, View A). 2 In case of no crack finding, accomplish the modification (Refer to A330-53-3159)
or Repeat the inspection every 4500 FC or 13500 FH whichever comes first. 3 In case of crack finding, accomplish the associated actions in accordance with Figure Fig. A-GFAAA Sheet 01, View A). (b) Do the inspection for WV010 - WV025 LR Mission. 1 Do the eddy current inspection (Refer to NTM 53-51-00, Page Block 601, procedure A and B) and (Refer to Figure Fig. A-GBAAA Sheet 01, View A). 2 In case of no crack finding, accomplish the modification Service Bulletin No. A330-53-3159.
or Repeat the inspection every 3600 FC or 21900 FH whichever comes first. DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 15 6

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# @A330 SERVICE BULLETIN
3 In case of crack finding, accomplish the associated actions in accordance with Figure Fig. A-GFBAA Sheet 01, View A). **CONF 002 (1) Subtask 533168-832-205-001 - Do a special detailed inspection of the Area A FR80, Area B FR84, and Area C FR86 for A330-300 WV050 - WV053 Manpower Resources Manhours 9.50 Minimum number of person 1 Subtask elapsed time 9.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 53-51-00, Page Block 601 Service Bulletin (SB) A330-53-3159 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAB Flow Chart Sheet 01 Fig. A-GFBAB Flow Chart Sheet 01 (a) Do the inspection for WV050 - WV053 SR Mission. 1 Do the eddy current inspection (Refer to NTM 53-51-00, Page Block 601 procedure A and B) and (Refer to Figure Fig. A-GBAAA Sheet 01, View A) 2 In case of crack no finding, accomplish the modification (Refer to A330-53-3159)
or Repeat the inspection every 4000 FC or 12100 FH whichever comes first. 3 In case of crack finding, accomplish the associated actions in accordance with Figure Fig. A-GFAAB Sheet 01, View A). (b) Do the inspection for WV050 - WV053 LR Mission. 1 Do the eddy current inspection (Refer to NTM 53-51-00 Page Block 601 procedure A and B) and (Refer to Figure Fig. A-GBAAA Sheet 01, View A) 2 In case of crack no finding, accomplish the modification Service Bulletin No. A330-53-3159.
or Repeat the inspection every 3200 FC or 19600 FH whichever comes first.
DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 16 6

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# @A330 SERVICE BULLETIN
3 In case of crack finding, accomplish the associated actions in accordance with Figure Fig. A-GFBAB Sheet 01, View A). **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 533168-832-207-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301 25-33-48, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 52-10-00, Page Block 201 53-45-11, Page Block 401 53-55-11, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the Fairings 323AR, 323AL, 323BR and 323BL, refer to AMM 53-55-11 Page Block 401. (c) Install Dorsal Fin, refer to AMM 53-45-11 Page Block 401. (d) Install the Pelmet of the AFT Galley , refer to AMM 25-33-48 Page Block 401 or AMM 25-33-54 Page Block 401. (e) Close the access door 312AR in the REAR fuselage area. (f) Remove the access platform(s) from the aircraft REAR section.

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 17 6

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# @A330 SERVICE BULLETIN (g) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer to AMM 29-14-00 Page Block 201. (h) Fill the Green hydraulic tank, refer to AMM 12-12-29 Page Block 301. (i) Pressurize the Green, the Blue and the Yellow hydraulic systems, refer to AMM 29-00-00 Page Block 201. (j) Remove the warning notices : 1 in the cockpit from the hydraulic section 40VU of the overhead panel, 2 on the ground service panel from each hydraulic system. (k) Close the circuit breaker(s) which are listed in : 1 AMM 27-51-18 Page Block 401. (l) Close the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00 Page Block 201. (m) Remove the access platform from the passenger/crew doors. **CONF 002 (1) Subtask 533168-832-207-001 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-12-29, Page Block 301 25-33-48, Page Block 401 25-33-54, Page Block 401 27-51-18, Page Block 401 29-00-00, Page Block 201 29-14-00, Page Block 201 52-10-00, Page Block 201 53-45-11, Page Block 401 53-55-11, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the Fairings 323AR, 323AL, 323BR and 323BL, refer to AMM 53-55-11 Page Block 401. (c) Install Dorsal Fin, refer to AMM 53-45-11 Page Block 401. (d) Install the Pelmet of the AFT Galley , refer to AMM 25-33-48 Page Block 401 or AMM 25-33-54 Page Block 401. (e) Close the access door 312AR in the REAR fuselage area. DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 18 6

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# @A330 SERVICE BULLETIN (f) Remove the access platform(s) from the aircraft REAR section. (g) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer to AMM 29-14-00 Page Block 201. (h) Fill the Green hydraulic tank, refer to AMM 12-12-29 Page Block 301. (i) Pressurize the Green, the Blue and the Yellow hydraulic systems, refer to AMM 29-00-00 Page Block 201. (j) Remove the warning notices : 1 in the cockpit from the hydraulic section 40VU of the overhead panel, 2 on the ground service panel from each hydraulic system. (k) Close the circuit breaker(s) which are listed in : 1 AMM 27-51-18 Page Block 401. (l) Close the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00 Page Block 201. (m) Remove the access platform from the passenger/crew doors.

DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 19 6

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# @A330 SERVICE BULLETIN

**CONF ALL

FR91 Z310 Z270



### A



## A FR80 FR84 FR86 INSPECTION AREA A

INSPECTION AREA B INSPECTION AREA C

G_SB_533168_6_BAAA_01_00 Figure A-GBAAA - Sheet 01 Inspection Area DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 20 6

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# @A330 SERVICE BULLETIN

**CONF 001

INSPECTION AREA A B C

CRACK NO YES

REPEAT THE INSPECTION

REPEAT THE INSPECTION REPEAT THE INSPECTION YES

YES

YES

YES OR REPEAT THE INSPECTION
FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

CONTACT AIRBUS BEFORE NEXT FLIGHT FOR REPAIR AND

AND

AND ACCOMPLISH SB 53−3159 EVERY 1250 FC 3800 FH

EVERY 950 FC 2900 FH

EVERY 600 FC 1900 FH THRESHOLD 25400 FC/ 76300 FH

EVERY 4500 FC 13500 FH A330−300 WV010 − WV025

CRACK CRACK

CRACK NO

NO NO CRACK

= 3.0mm (0.12in.)

= 6.0mm (0.24in.)

= 10.0mm (0.39in.) 3.0mm (0.12in.)

6.0mm (0.24in.)

10.0mm (0.39in.)

NOTE: REPETITIVE INTERVAL GIVEN HERE ABOVE IN CASE OF CRACK FINDINGS, SHOULD BE CONSIDERED AS AN ALLOWANCE, IN ORDER TO PREPARE THE REPAIR/MODIFICATION SCENARIO DUE TO THE SPECIFIC ACCESS AND TOOLING REQUIRED. IT IS STRONGLY RECOMMENDED TO CONTACT AIRBUS IN CASE OF CRACK FINDINGS, IN ORDER TO DEFINE THE REPAIR TO BE APPLIED AT NEXT INTERVAL, ACCORDING TO ABOVE TABLE. THE INSPECTION MUST BE PERFORMED AT WHICHEVER LIMIT (FC OR FH) OCCURS FIRST. REFER NTM 53−51−00 PROCEDURE A AND B

FOUND MISSION SR

G_SB_533168_6_FAAA_01_02 Figure A-GFAAA - Sheet 01 Flow Chart DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 21 6

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# @A330 SERVICE BULLETIN

**CONF 002

INSPECTION AREA A B C

CRACK NO YES

REPEAT THE INSPECTION

REPEAT THE INSPECTION REPEAT THE INSPECTION YES

YES

YES

YES OR REPEAT THE INSPECTION
FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

CONTACT AIRBUS BEFORE NEXT FLIGHT FOR REPAIR AND

AND

AND ACCOMPLISH SB 53−3159 EVERY 1100 FC 3400 FH

EVERY 850 FC 2600 FH

EVERY 550 FC 1700 FH THRESHOLD 21600 FC/ 64900 FH

EVERY 4000 FC 12100 FH A330−300 WV050 − WV053

CRACK CRACK

CRACK NO

NO NO CRACK

= 3.0mm (0.12in.)

= 6.0mm (0.24in.)

= 10.0mm (0.39in.) 3.0mm (0.12in.)

6.0mm (0.24in.)

10.0mm (0.39in.)

NOTE: REPETITIVE INTERVAL GIVEN HERE ABOVE IN CASE OF CRACK FINDINGS, SHOULD BE CONSIDERED AS AN ALLOWANCE, IN ORDER TO PREPARE THE REPAIR/MODIFICATION SCENARIO DUE TO THE SPECIFIC ACCESS AND TOOLING REQUIRED. IT IS STRONGLY RECOMMENDED TO CONTACT AIRBUS IN CASE OF CRACK FINDINGS, IN ORDER TO DEFINE THE REPAIR TO BE APPLIED AT NEXT INTERVAL, ACCORDING TO ABOVE TABLE. THE INSPECTION MUST BE PERFORMED AT WHICHEVER LIMIT (FC OR FH) OCCURS FIRST. REFER NTM 53−51−00 PROCEDURE A AND B

FOUND MISSION SR

G_SB_533168_6_FAAB_01_02 Figure A-GFAAB - Sheet 01 Flow Chart DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 22 6

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# @A330 SERVICE BULLETIN

**CONF 001

INSPECTION AREA A B C

CRACK NO YES

REPEAT THE INSPECTION

REPEAT THE INSPECTION REPEAT THE INSPECTION YES

YES

YES

YES OR REPEAT THE INSPECTION
FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

CONTACT AIRBUS BEFORE NEXT FLIGHT FOR REPAIR AND

AND

AND ACCOMPLISH SB 53−3159 EVERY 1000 FC 6100 FH

EVERY 750 FC 4700 FH

EVERY 500 FC 3000 FH THRESHOLD 19600 FC/ 117700 FH

EVERY 3600 FC 21900 FH A330−300 WV010 − WV025

CRACK CRACK

CRACK NO

NO NO CRACK

= 3.0mm (0.12in.)

= 6.0mm (0.24in.)

= 10.0mm (0.39in.) 3.0mm (0.12in.)

6.0mm (0.24in.)

10.0mm (0.39in.)

NOTE: REPETITIVE INTERVAL GIVEN HERE ABOVE IN CASE OF CRACK FINDINGS, SHOULD BE CONSIDERED AS AN ALLOWANCE, IN ORDER TO PREPARE THE REPAIR/MODIFICATION SCENARIO DUE TO THE SPECIFIC ACCESS AND TOOLING REQUIRED. IT IS STRONGLY RECOMMENDED TO CONTACT AIRBUS IN CASE OF CRACK FINDINGS, IN ORDER TO DEFINE THE REPAIR TO BE APPLIED AT NEXT INTERVAL, ACCORDING TO ABOVE TABLE. THE INSPECTION MUST BE PERFORMED AT WHICHEVER LIMIT (FC OR FH) OCCURS FIRST. REFER NTM 53−51−00 PROCEDURE A AND B

FOUND MISSION LR

G_SB_533168_6_FBAA_01_02 Figure A-GFBAA - Sheet 01 Flow Chart DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 23 6

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# @A330 SERVICE BULLETIN

**CONF 002

INSPECTION AREA A B C

CRACK NO YES

REPEAT THE INSPECTION

REPEAT THE INSPECTION REPEAT THE INSPECTION YES

YES

YES

YES OR REPEAT THE INSPECTION
FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

FOR REPAIR CONTACT AIRBUS

CONTACT AIRBUS BEFORE NEXT FLIGHT FOR REPAIR AND

AND

AND ACCOMPLISH SB 53−3159 EVERY 900 FC 5500 FH

EVERY 650 FC 4200 FH

EVERY 450 FC 2700 FH THRESHOLD 16600 FC/ 100100 FH

EVERY 3200 FC 19600 FH A330−300 WV050 − WV053

CRACK CRACK

CRACK NO

NO NO CRACK

= 3.0mm (0.12in.)

= 6.0mm (0.24in.)

= 10.0mm (0.39in.) 3.0mm (0.12in.)

6.0mm (0.24in.)

10.0mm (0.39in.)

NOTE: REPETITIVE INTERVAL GIVEN HERE ABOVE IN CASE OF CRACK FINDINGS, SHOULD BE CONSIDERED AS AN ALLOWANCE, IN ORDER TO PREPARE THE REPAIR/MODIFICATION SCENARIO DUE TO THE SPECIFIC ACCESS AND TOOLING REQUIRED. IT IS STRONGLY RECOMMENDED TO CONTACT AIRBUS IN CASE OF CRACK FINDINGS, IN ORDER TO DEFINE THE REPAIR TO BE APPLIED AT NEXT INTERVAL, ACCORDING TO ABOVE TABLE. THE INSPECTION MUST BE PERFORMED AT WHICHEVER LIMIT (FC OR FH) OCCURS FIRST. REFER NTM 53−51−00 PROCEDURE A AND B

FOUND MISSION LR

G_SB_533168_6_FBAB_01_03 Figure A-GFBAB - Sheet 01 Flow Chart DATE: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 24 6

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - REAR FUSELAGE - INSPECTION OF LONGITUDINAL DOUBLER AT VTP ATTACHMENT CUT OUT MODIFICATION No.: None 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: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 1 6

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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: Sep 19/07 SERVICE BULLETIN No.: A330-53-3168 REVISION No.: 02 - Dec 21/11 Page: 1 6

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