# @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: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame 40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis led to the issue of the Mandatory Inspection Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)) and the issue of the Recommended Modification Service Bulletin No. A330-57-3098, Modification No. 56467S18944 ( WINGS - CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR40). Accomplishment of the Service Bulletin No. A330-57-3098 cancels the inspection requirements of the Service Bulletin No. A330-57-3081. The accomplishment Instructions in Service Bulletin No. A330-57-3098 must be completed for all aircraft belonging to configuration 002 listed in the effectivity of this Service Bulletin Rev. 01 and Rev. 02. A missing instruction has been detected in the following cases: - Either with a crack indication at hole 5 at time of Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment (Case 1), - or with a bush installed before Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment at hole 5 and without a crack indication at hole 5 at time of Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment (Case 2). CASE 1:

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 1 5

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# @A330 SERVICE BULLETIN SUMMARY In case of crack indication during rototest inspection of fastener hole 5 as per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. CASE 2: In case of bush installation before Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. Doing a rototest inspection before the cold working is considered a standard practice. Nevertheless, two Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and 12-0032 have been issued to inform operators about this occurrence. Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about this occurrence. Eventually this Service Bulletin is issued to settle this matter. This Service Bulletin request a one time ultrasonic inspection of fastener hole 6 in the junction keel beam fitting at FR40 LH/RH side to ensure that no crack was left unrepaired at time of fastener hole cold working. In case of no finding, affected aircraft are inspected as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63 based on interval value. In case of finding, AIRBUS repair department will have to be contacted for further repair instructions. For aircraft which have not accomplished Service Bulletin No. A330-57-3098 at Rev. 01 or Rev. 02, perform repetitive inspection as per Inspection Service Bulletin No. A330-57-3081 or apply Service Bulletin No. A330-57-3098 at Rev. 03 or next when recommended threshold is reached. Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel beam fitting at FR40. 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 NO VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A330 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPA01 1 See SB Nut EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

38W ACA ACI AEA AFR ALK AZA BEL BER BMA BTV CPA CRL CSC DGA EDW EIN FWI GFA GRL HDA HFY HVN I2L IAC IWD JAV JST KAL MAS MON PAL QAF QTR RYN SAS SWR TAM TAP TCX THA THY TSC UAE USA VKG VOZ XLF CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER Operator Information Telex (OIT) No. 999.0082/12 and OIT No. 999.0086/11 OTHER SBIT 11-0041 and SBIT 12-0032 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 573117-832-801-001: Inspection TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 APPENDICES Appendix 01: Inspection Report

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF ALL

HOLE 6 TO BE INSPECTED − Z141 Z142 FR40 FR47



### B **B**



## A **A**

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 VIEW INSIDE CENTER TANK AT FR40 Y−1959 DATUM
Y1959 FR40 DATUM FR40

STGR1 STGR1

**F W**  **D** 

## B **C C** 

G_SB_573117_5_SAAA_01_02 Figure A-FSAAA - Sheet 01

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 4 5

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# @A330 SERVICE BULLETIN

AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 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 (1) Models 330-202 330-203 330-223 330-243 330-301 330-322 330-323 330-342 330-343 (2) Effectivity by MSN 0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 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

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 1 5

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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 38W 0401 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AEA 0505 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 ALK 0303 0306 0311 0313 0404 0456 AZA 0272 0339 BEL 0229 0249 BER 0288 0322 0403 0432 0444 0454 0469 0476 0493 BMA 0398 BTV 0205 0330 CPA 0386 0389 0393 0418 0420 0421 0423 0439 CRL 0285 0320 CSC 0462 DGA 0240 EDW 0291 EIN 0269 0397 FWI 0253 GFA 0276 0281 0286 0287 0334 0340 GRL 0230 HDA 0234 0244 0405 0479 0512 HFY 0211 0262 HVN 0275 0294 0299 0366 I2L 0358 0364 IAC 0353 0362 IWD 0461 JAV 0255 JST 0506 0508 0522 KAL 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 MAS 0290 0296 0300 MON 0261 0265 PAL 0183 0184 0188 0189 0191 0198 0200 0203 QAF 0487 QTR 0441 0473 0489 RYN 0343 SAS 0496 0497 SWR 0324 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 TAP 0181 0195 0223 0305 0308 0312 0317
DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN TCX 0254 0266 0301 THA 0209 0224 0231 0346 THY 0463 0504 TSC 0177 0250 0271 0369 0407 0427 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0382 0384 0392 0396 0409 0437 0451 0452 0455 0491 0494 0509 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0309 0349 0356 0357 VOZ 0365 0372 XLF 0501 (4) Configuration by MSN MSN CONFIGURATION 0177 0181 0183 0184 0188 0189 0191 0195 0198 0200 0203 0205 0206 0209 0211 0219 0222 0223 0224 0226 0229 0230 0231 0232 0234 0238 0240 0241 0244 0247 0248 0249 0250 0251 0253 0254 0255 0256 0258 0259 0261 0262 0265 0266 0267 0269 0271 0272 0275 0276 0277 0279 0281 0283 0284 0285 0286 0287 0288 0290 0291 0293 0294 0295 0296 0299 0300 0301 0303 0305 0306 0308 0309 0311 0312 0313 0314 0315 0316 0317 0320 0322 0323 0324 0326 0328 0330 0333 0334 0337 0338 0339 0340 0342 0343 0344 0345 0346 0348 0349 0350 0351 0353 0356 0357 0358 0361 0362 0364 0365 0366 0368 0369 0370 0372 0375 0380 0382 0384 0386 0388 0389 0392 0393 0396 0397 0398 0400 0401 0403 0404 0405 0407 0408 0409 0412 0418 0419 0420 0421 0422 0423 0425 0427 0428 0432 0437 0439 0441 0443 0444 0448 0451 0452 0454 0455 0456 0458 0461 0462 0463 0465 0466 0469 0472 0473 0476 0477 0479 0480 0481 0484 0486 0487 0489 0490 0491 0493 0494 0496 0497 0498 0500 0501 0502 0503 0504 0505 0506 0507 0508 0509 0510 0512 0522 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPA01 1 B. CONCURRENT REQUIREMENTS None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 3 5

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# @A330 SERVICE BULLETIN

C. REASON (1) History During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame 40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis led to the issue of the Mandatory Inspection Service Bulletin No. A330-57-3081 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT)) and the issue of the Recommended Modification Service Bulletin No. A330-57-3098, Modification No. 56467S18944 ( WINGS - CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL BEAM FITTING AT FR40). Accomplishment of the Service Bulletin No. A330-57-3098 cancels the inspection requirements of the Service Bulletin No. A330-57-3081. The accomplishment Instructions in Service Bulletin No. A330-57-3098 must be completed for all aircraft belonging to configuration 002 listed in the effectivity of this Service Bulletin Rev. 01 and Rev. 02. A missing instruction has been detected in the following cases: - Either with a crack indication at hole 5 at time of Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment (Case 1), - or with a bush installed before Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment at hole 5 and without a crack indication at hole 5 at time of Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment (Case 2). CASE 1: In case of crack indication during rototest inspection of fastener hole 5 as per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. CASE 2: In case of bush installation before Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before the cold working. However, this instruction is missing in the Service Bulletin. Doing a rototest inspection before the cold working is considered a standard practice. Nevertheless, two Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and 12-0032 have been issued to inform operators about this occurrence. Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about this occurrence. Eventually this Service Bulletin is issued to settle this matter.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 4 5

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# @A330 SERVICE BULLETIN
(2) Objective/Action This Service Bulletin request a one time ultrasonic inspection of fastener hole 6 in the junction keel beam fitting at FR40 LH/RH side to ensure that no crack was left unrepaired at time of fastener hole cold working. In case of no finding, affected aircraft are inspected as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63 based on interval value. In case of finding, AIRBUS repair department will have to be contacted for further repair instructions. For aircraft which have not accomplished Service Bulletin No. A330-57-3098 at Rev. 01 or Rev. 02, perform repetitive inspection as per Inspection Service Bulletin No. A330-57-3081 or apply Service Bulletin No. A330-57-3098 at Rev. 03 or next when recommended threshold is reached. (3) Advantages Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel beam fitting at FR40. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 573117-832-801-001: Inspection (1) On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. (2) Inspect one keel beam fastener hole between FR40 and STGR1. (3) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. 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 Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 5 5

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# @A330 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

Perform repetitive inspection as per SB A330-57-3081 A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) Refer to A330-57-3081

OR SB A330-57-3098 at Rev. 01 or Rev. 02 not accomplished.
Apply SB A330-57-3098 at Rev. 03 or next. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) Refer to A330-57-3098

SB A330-57-3098 at Rev. 01 or Rev. 02 accomplished, hole 5 bushed and rototest at hole 6 made before cold working during SB A330-57-3098 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 6 5

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# @A330 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

A330-200 (WV020 serie) - FC optimized set: 5,250FC / 17,100FH or - FH optimized set: 4,650FC / 30,400FH SB A330-57-3098 at Rev. 01 or Rev. 02 accomplished, hole 5 bushed and rototest at hole 6 not made before cold working during SB A330-57-3098 accomplishment Do the preparation procedure (Refer to SUBTASK 573117-941-001 001 Job Set-up ) and do the one time ultrasonic inspection at hole 6 (Refer to SUBTASK 573117-832-002 001 Inspect one keel beam fastener hole between FR40 and STGR1. ) A330-300 (WV010 and WV020 serie) - FC optimized set: 5,800FC / 19,000FH or - FH optimized set: 5,350FC / 36,200FH - 24 months from SB issuance date or - 2,400FC from SB issuance date None

Crack found on hole 6 Contact AIRBUS A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) Before next flight None None

No crack found on hole 6 No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) At the interval given in ALI Task ref. 57-11-63 None None

SB A330-57-3098 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed and no crack found on hole 5 during SB A330-57-3098 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 7 5

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# @A330 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

SB A330-57-3098 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed, crack found on hole 5 and rototest made to hole 6 before cold working during SB A330-57-3098 accomplishment No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) At the threshold given in ALI Task ref. 57-11-63 None None

A330-200 (WV020 serie) - FC optimized set: 5,250FC / 17,100FH or - FH optimized set: 4,650FC / 30,400FH SB A330-57-3098 at Rev. 01 or Rev. 02 accomplished, hole 5 not bushed, crack found on hole 5 and rototest not made to hole 6 before cold working during SB A330-57-3098 accomplishment Do the preparation procedure (Refer to SUBTASK 573117-941-001 001 Job Set-up ) and do the one time ultrasonic inspection at hole 6 (Refer to SUBTASK 573117-832-002 001 Inspect one keel beam fastener hole between FR40 and STGR1. ) A330-300 (WV010 and WV020 serie) - FC optimized set: 5,800FC / 19,000FH or - FH optimized set: 5,350FC / 36,200FH - 24 months from SB issuance date or - 2,400FC from SB issuance date None

Crack found on hole 6 Contact AIRBUS A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) Before next flight None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 8 5

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# @A330 SERVICE BULLETIN
Table 1, Config. 001 - Special Detailed inspection of hole 6 Compliance Time (whichever occurs first) Condition Action Aircraft Model Threshold FC/FH (whichever occurs first) Grace Period (whichever occurs first) Repetitive Interval

No crack found on hole 6 No further action in accordance with this SB. Inspect as per ALI Task 57-11-63. A330-200 (WV020 serie) and A330-300 (WV010 and WV020 serie) At the interval given in ALI Task ref. 57-11-63 None None

NOTE: Threshold to be counted from Service Bulletin No. A330-57-3098 accomplishment. NOTE: For FH and FC optimization on A330 aircraft, operators shall select the set that better suits aircraft operation and utilization, refer to OIT No. 999.086/11. F. APPROVAL The technical content of this document is approved under the authority of Design Organization Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 573117-832-801-001: Inspection Get Access 10.00 On Aircraft On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. 1.00 Inspect one keel beam fastener hole between FR40 and STGR1. 0.50 On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. 1.00 Tests 0.25 Close-Up 10.00
DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 9 5

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# @A330 SERVICE BULLETIN
Task 573117-832-801-001: Inspection TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 57-11-63 Aircraft Maintenance Manual (AMM) 06-31-53 12-34-24 20-21-11 21-20-00 21-53-18 36-12-41 53-35-13 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-11-63 Service Bulletin (SB) A330-57-3081 A330-57-3098 Standards Manual (SM) Structural Repair Manual (SRM) 51-42-00 51-43-00 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 10 5

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# @A330 SERVICE BULLETIN

2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to B/E Aerospace. The address is: Component COMPA01 B/E AEROSPACE INC. CONSUMABLES MANAGEMENT 10000 NW 15th Terrace Miami FL 33172 USA Tel EMEA: +49 (0) 40 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 40 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-Mail: AOGdesk_CMG@beaerospace.com internet: http://www.beconsumables.com or, alternatively any other source on the open market. (2) Price and Availability No AIRBUS kit will be provided. Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. 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 (1) Consumable Materials None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 11 5

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# @A330 SERVICE BULLETIN
(2) Components Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 10 MS21071-3 1 NUT 15 NSA5050-4 2 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 12 5

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# @A330 SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS Task 573117-832-801-001 - 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 Manpower TOTAL MANHOURS 22.75 ELAPSED TIME (HOURS) 22.75 A. GENERAL NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. (1) Subtask 573117-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) To torque tighten the standard fasteners, refer to AMM Task 20-21-11-911-801. (c) Remove and install fasteners in accordance with SRM 51-42-00.
DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 13 5

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# @A330 SERVICE BULLETIN
(d) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (2) Subtask 573117-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 573117-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 21-20-00-010-801 Task 21-53-18-000-801 Task 36-12-41-000-801 Task 53-35-13-000-802 NOTE: Access to aircraft is only necessary to allow the ultrasonic inspection at hole 6. Before this step you have to check your Service Bulletin reports to see if this ultrasonic inspection is necessary. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put access platform(s) in position. (c) Do the preparation procedure as specified in the Removal of the air-conditioning distribution ducts, refer to AMM Task 21-20-00-010-801. (d) Do the preparation procedure as specified in the Removal of the pack discharge temperature-sensor (542HH), refer to AMM Task 21-53-18-000-801. (e) Do the preparation procedure as specified in the Removal of the APU bleed-air ducts, refer to AMM Task 36-12-41-000-801. (f) Remove the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the RH side, refer to AMM Task 53-35-13-000-802. (g) Get access to the work area.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 14 5

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# @A330 SERVICE BULLETIN

C. PROCEDURE (1) Subtask 573117-832-001-001 - On the LH and RH sides, remove (if necessary) the ducts between FR39.1 and FR40, for access. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-53-18-000-801 Task 36-12-41-000-801 Structural Repair Manual (SRM) 51-42-00 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access Sheet 01

Fig. A-FBBAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for access Sheet 01

(a) On RH side, remove the air conditioning duct. Refer to Fig. A-FBAAA Sheet 01 Refer to SRM 51-42-00 1 Remove: 1 Duct Item (8) Retain 1 Insulation Item (9) Retain 1 Nut Item (10) Discard 1 Bolt Item (11) Retain 1 Washer Item (12) Retain 2 Screw Item (13) Retain 2 Washer Item (14) Retain 2 Nut Item (15) Discard 1 Clamp Item (16) Retain

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 15 5

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# @A330 SERVICE BULLETIN
1 Clamp Item (17) Retain NOTE (01): Disconnect and move the rod Items (18) and (19) without removal. NOTE (02): Remove the Insulation Item (9) with associated clamp Item (17) from the duct Item (8) only if necessary. NOTE (03): For the removal of the sensor 542HH, refer to AMM Task 21-53-18-000-801. (b) On RH side, remove the air ventilation duct. Refer to Fig. A-FBBAA Sheet 01 Refer to SRM 51-42-00 1 Remove: 1 Duct Item (20) Retain 4 Clamp Item (21) Retain 8 Clamp Item (22) Retain 1 Sleeve Item (23) Retain 2 Sleeve Item (24) Retain (c) On LH side, remove the necessary APU bleed air system ducts between FR39.1 and FR40, refer to AMM Task 36-12-41-000-801. (d) Put the blanking plugs on the disconnected line ends. (2) Subtask 573117-832-002-001 - Inspect one keel beam fastener hole between FR40 and STGR1. Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI) 57-11-63 Non Destructive Test Manual (NTM) 57-11-63 Service Bulletin (SB) A330-57-3081 A330-57-3098

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 16 5

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# @A330 SERVICE BULLETIN

References Fig. A-FBCAA Inspection of Hole 6 in the junction keel beam Sheet 01 Sheet 02 (a) At the threshold given in the PLANNING INFORMATION paragraph 1.E.(2): Do a special detailed inspection of hole 6 in the junction keel beam fitting at FR40. 1 If Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 is not accomplished:
a Perform repetitive inspection as per Inspection Service Bulletin No. A330-57-3081
or Apply Service Bulletin No. A330-57-3098 at Rev. 03 or next when recommended threshold is reached. 2 If Service Bulletin No. A330-57-3098 Rev. 01 or Rev. 02 is accomplished:
a Do the inspection of the Hole 6. Refer to Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02 <1> Hole 5 has been already bushed before Service Bulletin No. A330-57-3098 accomplishment: <a> If Rototest at Hole 6 was made before cold working during Service Bulletin No. A330-57-3098 accomplishment: [1] No further action for Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [2] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. <b> If Rototest at Hole 6 was not made before cold working during Service Bulletin No. A330-57-3098 accomplishment: [1] Do the preparation procedure, refer to SUBTASK 573117-941-001 001 Job Set-up . [2] Do the one time ultrasonic inspection of the Hole 6, refer to NTM 57-11-63. [3] If crack found on Hole 6: [a] Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 17 5

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# @A330 SERVICE BULLETIN
[4] If crack not found on Hole 6: [a] Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . [b] No further action on Hole 6 in accordance with this Service Bulletin. [c] Re-inspect the Hole 6 as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63, at the task interval, refer to NTM 57-11-63. <2> Hole 5 has not been already bushed before Service Bulletin No. A330-57-3098 accomplishment: <a> Crack not found on Hole 5 during Service Bulletin No. A330-57-3098 accomplishment: [1] No further action on Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [2] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. <b> Crack found on Hole 5 during Service Bulletin No. A330-57-3098 accomplishment: [1] If Rototest at Hole 6 was made before cold working during Service Bulletin No. A330-57-3098 accomplishment: [a] No further action on Hole 6 in accordance with this Service Bulletin (Hole 6 is covered by Airworthiness Limitation Items (ALI) Task ref. 57-11-63). [b] Inspect Hole 6 at the threshold of the Airworthiness Limitation Items (ALI) Task ref. 57-11-63. [2] If Rototest at Hole 6 was not made before cold working during Service Bulletin No. A330-57-3098 accomplishment: [a] Do the preparation procedure, refer to SUBTASK 573117-941-001 001 Job Set-up . [b] Do the one time ultrasonic inspection of the Hole 6, refer to NTM 57-11-63. [c] If crack found on Hole 6: - Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 18 5

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# @A330 SERVICE BULLETIN
[d] If crack not found on Hole 6: - Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . - No further action on Hole 6 in accordance with this Service Bulletin. - Re-inspect the Hole 6 as per Airworthiness Limitation Items (ALI) Task ref. 57-11-63, at the task interval, refer to NTM 57-11-63. (b) Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report . (3) Subtask 573117-832-003-001 - On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40. Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Component COMPA01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 10 MS21071-3 1 NUT 15 NSA5050-4 2 NUT NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Task 21-53-18-400-801 Task 36-12-41-400-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access Sheet 01

Fig. A-FBBAA Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for access Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 19 5

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# @A330 SERVICE BULLETIN
(b) On LH side, install (if removed) the APU bleed air system ducts between FR39.1 and FR40, refer to AMM Task 36-12-41-400-801. (c) On RH side, install (if removed) the air ventilation duct. Refer to Fig. A-FBAAA Sheet 01 Refer to AMM Task 20-21-11-911-801 Refer to SRM 51-42-00 and SRM 51-43-00 1 Install: 1 Duct Item (20) Retained at removal 4 Clamp Item (21) Retained at removal 8 Clamp Item (22) Retained at removal 1 Sleeve Item (23) Retained at removal 2 Sleeve Item (24) Retained at removal (d) On RH side, install (if removed) the air conditioning duct. Refer to Fig. A-FBBAA Sheet 01 Refer to AMM Task 20-21-11-911-801 Refer to SRM 51-42-00 and SRM 51-43-00 1 Install: 1 Duct Item (8) Retained at removal 1 Insulation Item (9) Retained at removal 1 Nut MS21071-3 Item 10 1 Bolt Item (11) Retained at removal 1 Washer Item (12) Retained at removal

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 20 5

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# @A330 SERVICE BULLETIN
2 Screw Item (13) Retained at removal 2 Washer Item (14) Retained at removal 2 Nut NSA5050-4 Item 15 1 Clamp Item (16) Retained at removal 1 Clamp Item (17) Retained at removal NOTE (01): Reconnect the rod Items (18) and (19). NOTE (02): For the installation of the sensor 542HH, refer to AMM Task 21-53-18-400-801. D. TEST (1) Subtask 573117-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802 (a) Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as specified in the Installation of the Belly Fairing Access-Panels, refer to AMM Task 53-35-13-400-802. E. CLOSE-UP (1) Subtask 573117-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-53-18-400-801 Task 36-12-41-400-801 Task 53-35-13-400-802 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the RH side, refer to AMM Task 53-35-13-400-802.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 21 5

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# @A330 SERVICE BULLETIN
(c) Do the Close-up procedure as specified after the Installation of the Belly Fairing Access-Panels, refer to AMM Task 53-35-13-400-802. (d) Do the Close-up procedure as specified after the Installation of the APU bleed-air ducts, refer to AMM Task 36-12-41-400-801. (e) Do the Close-up procedure as specified after the Installation of the pack discharge temperature-sensor (542HH), refer to AMM Task 21-53-18-400-801. (f) Do the Close-up procedure as specified after the Installation of the air-conditioning distribution ducts, refer to AMM Task 21-20-00-410-801. (g) Remove access platform(s). (h) Restore the systems and the aircraft to normal operating condition.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 22 5

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# @A330 SERVICE BULLETIN

**CONF ALL

Z190



## A FR40.2
FR39.2



## B (9) (18)

(15) (17)

(8) (16)

(10) (11) (12) (13) (14) (19) (15) (13) (14)

542HH 

### A **B**

15

15

10

G_SB_573117_5_BAAA_01_01 Figure A-FBAAA - Sheet 01 Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 23 5

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# @A330 SERVICE BULLETIN

**CONF ALL

− Z191 Z192



## A **B**



## C **D C**  **D**

**D** 

## B FR40 FR47

(20) (21) (22) (23) (24) (21) (22) 

### C **D A** 

**C D**  **C D** 

G_SB_573117_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for access

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 24 5

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# @A330 SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN RH SIDE SYMMETRICAL VIEW INSIDE CENTER TANK AT FR40 DATUM
Y1959 − Z141 Z142 FR40 FR47



### B



## A **B**



## B **C** FR40

STGR1 

### A

G_SB_573117_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Inspection of Hole 6 in the junction keel beam

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 25 5

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# @A330 SERVICE BULLETIN

**CONF ALL
Y1959

VIEW SIDE CENTRE TANK AT FR 40

FASTENER NOT AFFECTED HOLE 6

CENTER WING BOX

LOWER PANEL

HOLE TO BE INSPECTED AREA TO BE INSPECTED FR40DATUM

STGR1

**F W**  **D** 

## C

**D D**  KEEL BEAM FITTING STGR1 FR40 

### D

**D**

TYPICAL G_SB_573117_5_BCAA_02_04 Figure A-FBCAA - Sheet 02 Inspection of Hole 6 in the junction keel beam

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 26 5

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# @A330 SERVICE BULLETIN

**CONF ALL

QUESTION
ACTION
FINDING RE−INSPECT THE HOLE 6 AT THE INTERVAL OF THE ALI 57.11.63 CRACK FOUND ON HOLE 6 DO THE ONE TIME ULTRASONIC INSPECTION AT HOLE 6, AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2).

REFER TO SUBTASK 573117−832−002−001 INSPECT THE HOLE 6 AT THE THRESHOLD OF THE ALI 57.11.63 CRACK FOUND ON HOLE 5 DURING SB 57−3098 ACCOMPLISHMENT HOLE 5 ALREADY BUSHED BEFORE SB 57−3098 ACCOMPLISHMENT SB 57−3098 REV. 01 OR REV. 02 EMBODIED
PERFORM REPETITIVE INSPECTION AS REV.03 OR NEXT WHEN RECOMMENDED THRESHOLD IS REACHED DO A SPECIAL DETAILED INSPECTION OF ONE FASTERNER HOLE IN THE

JUNCTION KEEL BEAM FITTING AT FR40 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2). REFER TO SUBTASK 573117−832−002−001

YES CHECK YOUR SERVICE BULLETIN REPORTS AND IF NECESSARY

YES NO NO

PER ISB 57−3081 OR APPLY SB 57−3098 AT

YES NO

NO YES ROTOTEST AT HOLE 6 MADE PRIOR TO COLD WORKING DURING SB 57−3098 ACCOMPLISHMENT

NO FURTHER ACTION HOLE 6 REFER TO SUBTASK 573117−941−001−001 DO THE PREPARATION PROCEDURE

YES NO

CONTACT AIRBUS BEFORE NEXT FLIGHT

NO FURTHER ACTION HOLE 6 G_SB_573117_5_FAAA_01_02 Figure A-FFAAA - Sheet 01 Flow Chart

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 27 5

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# @A330 SERVICE BULLETIN

This Page Intentionally Left Blank

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# @A330 SERVICE BULLETIN Appendix 01: Inspection Report **CONF ALL (1) The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUS Department SEES1, on the attached inspection report sheet.

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 1 5

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# @A330 SERVICE BULLETIN Appendix 01: Inspection Report

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3117

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED INSPECTION CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: structure.sbinspectionresult@airbus.com FAX +33 (0)5 61 93 36 14

YES NO YES NO YES NO YES NO SIDE
HOLE 6 HOLE 6 LH RH ULTRASONIC CRACK FOUND ? INSPECTION ?

G_SB_573117_5_RAAA_01_02 Figure A-FRAAA - Sheet 01 Inspection Report

DATE: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 2 5

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40 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: Jan 25/13 SERVICE BULLETIN No.: A330-57-3117 REVISION No.: 00 - Jan 25/13 Page: 1 5

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

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

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